NASA SP-7037 (08)
AERONAUTICAL ENGINEERING
A Special Bibliography
Supplement 8
A selection of annotated references to unclas- sified reports and journal artictes that were introduced into the NASA scientific and tech- nical information system and announced in July 1971 in Scientific and Technical Aerospace Reports (STAR)
4 International Aerospace Abst#aacts (MA).
Sckt11$2aid Twh~ricaltuforniatioir Ojiw OFFICE OF INDUSTRY AF.FAIRS AND TECHNOLOGY LJTlLlZATlON 19ir NATIONAL AERONAUTICS AND SPACE ADMINlSIltATION This document is available from the National Technical Information Service (NTIS), Springfield, Virginia, 221 51, for$3.00. INTRODUCTION
Under the terms of an interagency agreement with the Federal Aviation Admin- istration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. This supplement to Aeronautical Eiigiiieering-A Special Bibliography (NASA SP-7037) lists 540 reports, journal articles, and other documents originally announced in July 1971 in Scieiitific aiid Techiiical Aerospace Reports (STAR) or in Iiitertiatioiial Aerospace Abstracts (ZAA). For previous bibliographies in this series, see inside of front cover. The coverage includes documents on the engineering and theoretical aspects ?f design, construction, evaluation, testing, operation, and performance of aircraft (includ- ing aircraft engines) and associated components, equipment, and systems. It also in- cludes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accom- panied by an abstract. The listing of the entries is arranged in two major sections, IAA Eiitries and STAR Eiitries in that order. The citations and abstracts are reproduced exactly as they appeared originally in IAA or STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes-subject, personal author, and contract number-are included. An annual cumulative index wiii >e published.
iii AVAILABILITY OF CITED PUBLICATIONS
IAA ENTRIES (A71-'10000 Series)
All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc., (AIAA), as follows: Paper copies are available at $5.00 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., A71 -10613, when requesting publications.
STAR ENTRIES (N71-10000Series)
A source from which a publication abstracted in this Section is available to the public is ordinarily given on the last line of the citation, e.g., Avail: NTIS. The following are the most commonly indicated sources (full addresses of these organizations are listed at the end of this introductiofi): 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. Docu- ments exceeding 900 pages are priced by NTIS on an individial basis. These prices apply retroactively to all documents in the NTlS cotlection, but in addition, documents of 300 pages or less that are over two years old (from date of an- nouncement in Government 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 su.rcharge 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.g., N71-1041 I#)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 filed at the SOD price if hard copy is requested. NTlS will also fill microfiche requests, at the standard 95 cent price, for those documents identified by a # symbol.) 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. OrgahizatiOns in U.S. cities and abroad that main- tain 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 ill a booklet, Science Information Available from the Atomic Energy Commission (TlD-4550). which may be obtained without charge from the USAEC Division of Technical Information. Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts, and ark sold by University Microfilms as xerographic copy (HC) at $10.00 each and microfilm at $4.00 each,' regardless of the length of the manuscript Handing and Shipping charges are additional. All requests should cite the author and.the Order Number as they appear in the cifation.
(1) A mrarofiche is a transparent sheet of film. 105 x 148 mm Imslze. contalntng up to 72 pages of information reduced to micro images (not to exceed 20 1 reduction)
iv Avail: HMSO. Publications of Her Majesty's StationePy Office ate sold in the U.S. by British Information Services (SlS), New York City. The U.S.price (including a serv- ice 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 NCL.) Avail: ZLDI. Sold by the Aentralstelle fdr Luftfahrtdokunentatiqn 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 dpcument. Avail: U.S. Patent Office. Sold by Commissioner of Patents, U.S. Patent Office, at the standard price of $30 each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line.
GENERAL AVAl LAB I LlTY
All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliog- raphy 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.
SU BSCRl PTI ON AVAlLAB I LlTY
This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements, excluding the annual cumulative index, is $18.00. All questions relating to subscriptions should be FefeFred to the NTI S. ADDRESSES OF ORGANIZATIONS
American Institute of Aeronautics National Lending Library for Science and Astronautics and Technology Technical Information Service Boston Spa, Yorkshire, England 750 Third Ave. New York, N.Y. 10017 National Technical Information Service Springfield, Virginia 22151
British Information Service 845 Third Ave. Superintendent of Documents New York, N.Y. 10022 U.S. Government Printing Office Washington, D.C. 20402
Commissioner of Patents U.S. Patent Office University Microfilms, Inc. Washingto;, D.C. 2023 1 A Xerox Company 300 North Zeeb Road Ann Arbor, Michigan 48106 ESRO/ELDO Space Documentation Service European Space Research Organization 1 14, av. de Neuilly University Microfilms, Inc. 92-Neuilly-sur-Seine, France Tylers Green London, England Her Majesty's Stationery Office P.O. Box 569, S.E. 1 London, England US. Atomic Energy Commission Division of Technical Information NASA Scientific and Technical Information P.O. Box 62 Facility Oak Ridge, Tennessee 37830 P.O. Box 33 College Park, Maryland 20740 Zentralstelle fur Luftfahrtdoku- mentation und-Information National Aeronautics and Space 8 Munchen 86 Adm in ist rat ion Postfach 880 Scientific and Technical Information Federal Republic of Germany Office (KSI) Washington, D.C. 20546
vi TABLE OF CONTENTS
Page
IAAEntries ...... 403 STAR Entries ...... 455
Subject Index ...... A- 1 Personal Author Index ...... B-1 Contract Number Index ...... c-1
TYPICAL CITATION AND ABSTRACT FROM STAR
NASA SPONSORED AVAILABLE ON DOCUMENT '-7 tMICROFICHE
ACCEISlON NUMBER- N71-12035*# Pratt and Whitney Aircraft, East Hartford. Conn. CORPORATE DEVELOPMENT OF MAINSHAFT SEALS FOR ADVANCED SOURCE AIR BREATHING PROPULSION SYSTEMS, PHASE 2 Final TITLE 2Report PUBLICATION V. P. Povinelli and A. H. McKibbin 23 Jun5970 122 p refs DATE (Contract NAS3-7609) AUTHORS COSATI gas-turbine engines were designed, fabricated, and tested. The seal CODE CONTRACT concepts incorporated lift geometries which used the relative 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. AVAl LABILITY REPORT SOURCE NUMBER The other design (hydrodynamic) with a spiral groove geometry operated with ."-film separation. Tests of the gas-film seal demonstrated the feasibility of operation at gas temperatures to 1200 F, pressure differentials to 250 psi, and sliding speeds to 450 h/sec. Excellent correlations with analytically predicted performance. parameters were obtained. Face wear was less than 0.1 mil after 320 hours at an air temperature of 1000 F. a pressure differential of 200 psi, and a sliding speed of 400 h/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 AVAI~BLEON DOCUMENT MICROFICHE
ACCESSION -A71-10969 * # Sphere drag in near-free-molecule hypersonic TITLE NUMBER flow. M. I. Kussoy, D. A. Stewart, and C. C. Horstman (NASA, Ames Research Cezer, Moffett Field, Calif.). AlAA Journal, vol. 8. Nov. AUTHORS 1970, p. 2104, 2105. 9 refs. 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-flight technique in PUBLICATION the Ames 42-in. shock tunnel are tabulated, shown graphically, and DATE dixussed. O.H.
vii AERONAUTICAL ENGINEERING
A Special Bibliography (Suppl. 8) AUGUST 1971
frequency (to 1000 Hz) pressure fluctuations. A second analog device instantaneously sums the inputs of a select number of compressor face probes. Its output signal is used as an index to establish the degree to which the compressor face pulsations are one-dimensional. Data from a recently conducted inlet-engine test program are used to illustrate the operation of both devbes. (Author) IAA ENTRIES
A7128033 # Vortex wakes behind high-lift wings. J. E. Hackett and M. R. Evans (Lockheed-Georgia Co., Marietta, Ga.). Journal of Aircraft, vol. 8, May 1971, p. 334-340. 17 refs. At high wing lift coefficients pertinent to STOL.operation, the A7127819 # Fatigue strength of aircraft skin elements conventional neglect of vortex roll-up effects can lead to errors when affected by corrosion (Soprotivlenie ustalosti elementov obshivki calculating downwash at the tail plane and in the presence of ground samoleta, porazhennykh korroziei). A. V. Karlashov, A. I. or wind-tunnel walls. A classical unsteady treatment in the cross-flow Radchenko, A. la. Zaika, and N. F. Voronkin (Kievskii lnstitut plane, which calculates the roll-up of an initial spanwise row of point lnzhenerov Grazhdanskoi Aviatsii, Kiev, Ukrainian SSR). Fiziko- vortices, has been modified to allow for the influence of the wing. Khimicheskaia Mekhanika Materialo'v, vol. 7, no. 1, 1971, p. 53-56. Additional meaning is thereby given to the streamwise length In Russian. dimension and hence to aspect ratio and sweep. The effects of Study of the effect of a series of artificial corrosiori pits, height-above-ground and of various tunnel heights and widths are s.imulating local corrosion of the aircraft skin, on the fatigue discussed. Under certain limited conditions, notably with part-span durability of smooth samples and structural elements of duralu- flaps or too narrow a tunnel, part or all of the trailinqvortex system minum. It is shown that in the estimation of aircraft skin corrosion, may move upwards. Consequent changes in the vertical velocity field the most important factor is the pitting density. Allowance muq+ also are additional to conventional estimates involving only the appro- be made for the effect of stress raisers formed by structural elements. priate image system. (Author) This effect in many cases is much more important to the fatigue strength of the aircraft skin than are corrosion pits. Z.W. A7128145 Vacuum heat treating of jet engine compo- nents. R. F. Latchaw and D. J. Spillane (General Electric Co., A7127838 # VTOL propulsion - 1970 perspective. E. P. Aircraft Engine Group, Evendale, Ohio). Metals Engineering Quarter- Cockshutt (National Research Council, Ottawa, Canada). (Canadian ly, vol. 11, May 1971, p. 24-26. Aeronautics and Space Institute, Annual General Meeting, Ottawa, Vacuum heat treating of jet engine components is described Canada, May 18, 19, 1970.1 Canadian Aeronautics and Space with examples of some brazed and activated-diffusion-bonded Journal,vol. 17,Apr. 1971,~.117-129. 15refs. hardware, including sheet-metal vanes, cast vanes, and blades. The Review of the evolution of gas turbine technology over the past problems connected with maintenance of the vacuum equipment are 15 years, with emphasis on the trends in pressure ratio, turbine inlet briefly reviewed with special reference to the problem of localized temperature, and weight as they bear on VTOL propulsion. A general surface melting of RenB 80 high-pressure turbine blades during system for cataloging VTOL powerplant systems based on a common activated diffusion bonding. Z.W. gas generator is suggested, and the emerging predominance of lifting-fan systems is noted. It is shown that even high-bypass fans produce excess thrust under cruising conditions, hence some of the engines should be shut down in cruise. It is also shown that if A7 1-28158 A miniature turbulence gahge utilizing aero- high-bypass fans are to be used both in hover and cruise, then some dynamic lift. Thomas E. Siddon (British Columbia, University, form of variable geometry is needed to cope with the different Vancouver, Canada). Review of Scientific Instrummts, vol. 42, May operating conditions. It is considered that acceptable airworthiness 1971, P. 653-656. for VTOL aircraft will only be achieved by significant engine reserve An advanced version of the aerofoil probe turbulence gauge is capacity to produce engine-out safety. F.R.L. described. The new device uses an axisymmetric lifting body sensor of 2.4 mm diam coupled directly to a miniature preamplifier unit (6.35 mm diam). The output voltage varies linearly with the v or w component of turbulence. The device has uniform sensitivity and A71-28032 # Development of high-response data analysis good signal-to-noise ratio over a nominal frequency range of 10 to aids for inletengine testing. Malcolm Row and Mark B. Sussman 10,000 Hz. A discussion of calibration procedures and application (Boeing Co., Seattle, Wash.). Journal ofAircraft, vol. 8, May 1971, p. considerations is included. (Author) 307-311. Contract No. AF 33(657)-69-C-0552. The paper describes two data anaiysis aids recently developed to provide easy interpretation of high-response inlet flowfield informa- ton. A light bulb display is utilized as an analog simulation of the A71-28164 Society of the Plastics Industry, Annual engine compressor face. Bulbs, on a one-to-one basis with high- Western Conference, 28th, Coronado, Calif., May 5-7, 1971, Pro- response pressure transducers, provide flow visualization of high- ceedings. Los Angeles, Society of the Plastics Industry, Inc., 1971.
403 A71 -28168
171 p. $7.00. A7128249 # Measurement of geomagnetic components Recent advances in composite materials and filamentary- from moving platforms. A. la. Rotshtein and I. G. Zhurii (Akademiia composite reinforcement of metal structures are reviewed, with Nauk SSSR, lnstitut Zemnogo Magnetizma, lonosfery i Raspro- special attention to their use in spacecraft and missiles. Polyimides, straneniia Radiovoln, Leningrad, USSR). (Geomagnetizm i Aero- in particular, are considered for use in high temperature service, and nomiia, vol. 10, no. 5, 1970, p. 883-887.) Geomagnetism and potential structural applications to the space shuttle are discussed in Aeronomy, vol. 10, no. 5, 1970, p. 696-699. 10 refs. Translation. the light of ongoing studies. Discussion of direct and indirect methods of measuring geo- M.V.E. magnetic components from ships or aircraft in a system of coordinates which is fixed in space. Direct and indirect methods of stabilizing the system of coordinates are also studied. It is shown that A71-28168 * Filamentary composite reinforcement of metal direct stabilization methods have the advantage of permitting direct structures. P. T. Sumida, L. J. Hart-Smith (Douglas Aircraft CO., measurement of any geomagnetic component in such a way that the Long Beach, Calif.), R. A. Pride, and W. lllg (NASA, Langley results can be averaged without errors over an arbitrary period of Research Center, Hampton, Va.). In: Society of the Plastics Industry, time. V.P Annual Western Conference, 28th. Coronado. Calif., May 5-7, 1971, Proceedings. Los Angeles, Society of the Plastics Industry, Inc., 1971, p. 74-90. 18 refs. A71-28250 # Aircraft refractometer. V. N. Bormotov, I. D. A brief history of filamentary composite reinforced metal Gontar', and V. F. Shul'ga (Akademiia Nauk Ukrainskoi SSR, aircraft structural components is discussed. Trends in structural lnstitut Radiofiziki i Elektroniki, Kharkov, Ukrainian SSR). (Geo- reinforcement 'concepts are enumerated for several different shapes magnetizm i Aeronomiia, vol. 10, no. 5, 1970, p. 888-892.) and configurations. Test data are presented for boron/epoxy in Geomagnetism and Aeronomy, vol. 10, no. 5, 1970, p. 700-703. combination wlth aluminum plus additional data on graphite/epoxy Translation. materials and hybrids with steel, titanium, and magnesium. The Discussion of the design and principles of operation of an effect of thermally induced locked-in stresses arising from the onboard refractometer operating at the 3.2 cm wavelength. Particular differences in thermal coefficients of expansion of the various attention is given to the design of the resonator, on which the constituent materials is presented. Estimates of weight savings and effectiveness of the instrument depends, and to a circuit by means of projected costs of filamentary composite materials are included. which the frequency of two klystron oscillators is phase locked to Some basic problems which need further investigation and analyses the resonator resonant frequencies. The block diagram for measuring are outlined. (Author) the frequency difference of the two klystrons is examined. Mounted on an IL-18 aircraft, the device proved to be highly effective under adverse flight conditions at a height of 11 km. V.P.
A71-28176 Aircraft vortex wake. S. R. Cann (British Air Line Pilots Association, Hayes, Middx., England). Shell Aviation A7128282 # A flow about a low-aspect-ratiodelta wing at News, no. p. 394, 197 1, 8, 9. large angles of attack (Obtikannia del'ta-krila malogo vidovzheniia pri Consideration of the trailing vortices shed by the lifting surfaces velikikh ltutakh ataki). R. 0. Soroka (Akademiia Nauk Ukrains'koi of an aircraft. Vortex strength varies directly with the lift being RSR, lnstitut Gidromekhaniki, Kiev, Ukrainian SSR). Akademiia produced by the wing and inversely as the speed and the span. Thus Nauk Ukrains'koi RSR, Dopovidi, Seriia A - Fiziko-Tekhnichni i it is that at low speeds - i.e., in control zones - that wake effects Matematichni Nauki, vol. 32, Feb. 1971, p. 174-178. 5 refs. In become important. Encounters of aircraft with wakes produced by Ukrainian. other aircraft can result in uncontrollability. Current UK separation A flow model proposed by Brown and Michel (1954) for a standards are summarized. F.R.L. low-aspect-ratiodelta wing is used to derive an expression for the lift coefficient as a function of the vortex-line-to-wing-planeslope. The expression is used in a delta wing design with an aspect ratio of 0.7. A71 -28177 Engine condition monitoring. John Towers Good agreement is obtained between the lift coefficient of this (Aer Lingus Teo, Dublin, Ireland). Shell Aviation News, no. 394, design found from this expression and lift coefficients given for 1971, P. 16-24. comparable wings by Brown and Michel, Mangler and Smith (19591, Description of the methods by which engine condition moni- Johnes (1946),and other authors. V.Z. toring (ECM) can be applied to airline operation. The engine parameters used For trend analysis are exhaust gas temperature (EGT); fuel flow (F); low- and high-pressure rotor speeds; and turbine (T) and diffuser (D) case vibration levels. Performance data A71-28304 The role of military aviation greases in sub- are recorded by flight crews under steady-state cruise conditions, and sonic commercial airplane design. Douglas C. Sullivan (Boeing Co.. the data are then tcsnsferred to punch cards at base. The program Commercial Airplane Group, Renton, Wash.). Society of Automotive compares the perforpance of the gas path parameters for the engine Engineers, National Air Transportation Meeting, Atlanta, Ga., May being monitored to a standard engine of the same type at the same 10-13, 1971, Paper 710417. 6 p. Members, $1.00; nonmembers, thrust setting. It 'is shown that trends appearing on the ECM $1.50. printouts were effactive in detecting defects and preventing secon- The Boeing Co. subsonic commercial airplane design practice is dary damage. F.R.L. to use military specification greases as preferred lubricants. This standardization practice originated with the 707 prototype, and has been continued throughout design and construction stages of all commercial jet models. Based on service experience and supplemen- A7128211 # Load estimation methods for preliminary tary testing, this approach has proven economical and technically design weight prediction. R. S. St. John (LTV Aerospace Corp., beneficial to the airlines. Preferred military specifications and brief Dallas, Tex.). SAWEJournal, vol. 30, Mar.-Apr. 1971, p. 10-17. 12 details of supplementary tests are discussed. (Author) refs. Description of some preliminary load estimation methods used in performance and design concept trade studies required for arriving A71-28305 Airport certification. Clyde W. Pace, Jr. (FAA, at candidate systems for detail analysis. These weight estimation Washington, D.C.). Society of Automotive Engineers, National Air techniques are shown to be accountable and at the same time Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper adaptable enough to be useful in all phases of the advanced design 710413. 5 p. Members, $1.00; nonmembers, $1.50. environment. M.V.E. Discussion of data pertaining to the Airport Certification
404 A71-28313
Program, including the certification and safety inspection proce- has been adopted. All engine standards have been checked out by dures, and a list of minimum safety standards that will be contained extensive bench endurance testing. Performance requirements have in the Federal Aviation Regulations (FAR). Airports served solely by been confirmed by testing in altitude cells and by subsonic flight. air taxis will not be included in the program unless the air taxis (Author) provide contract service for regularly scheduled air carrier aircraft. The program is designed to help put the airport4acilities in uniform, A71-28310 The economics of subsonic transport airplane safe, and proper order for the present and future airport-oriented design, evaluation and operation. Donald D. Hufford, James A. Ross, activities. M.M. and Kenneth W. Hoefs (Boeing Co., Seattle, Wash.). Society of Automo rive Engineers, National Air Transportation Meeting, Atlanta, Ga., May 10-73, 1971, Paper 710423. 12 p. 6 refs. Members, A71-28306 The National Airport System Plan - Its history $1 .OO; nonmembers, $1.50. and its potential. Robert F. Bacon and Elliott B. Perrett, Jr. (FAA, The interactive and cyclical design, evaluation, and operational Washington, D.C.). Society of Automotive Engineers, National Air system that conceives transport airplanes is described. Some Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper economic consequences of preliminary design variable choices are 710414. 11 p. Members, $1.00; nonmembers, $1.50. displayed, followed by an inspection of the 1967 ATA Method and Discussion of the changes undergone by the National Airport actual direct operating costs. Uses and misuses of the formula costs, Plan (NAP) since its inception. Since 1946, a document called NAP as compared to actual cost levels, are considered. Finally, the impact has been prepared annually to 'specify in terms of general location of airplane choice on airline profitability is examined. It is seen that and type of development the projects considered by the Adminis- the profit consequences are great enough to require careful attention trator to be necessary to provide a system of public airports adequate to economic trades in every step of the design, evaluation, and to anticipate and meet the needs of civil aeronauti,cs,' throughout the operational process. ' (Author) US., including Puerto Rico and the Virgin Islands. The process of developing the NAP is conceived as a continuous planning process both from the standpoint of evolving and refining the criteria by A71-28311 The MAC MADAR System - An AIDS model which it comes into being and in the application of the criteria by for commercial airlines. George C. Curtis and Charles F. Elgin the field elements of FAA's Airports Service to provide continuous a (Lockheed-Georgia Co., Marietta, Ga.). Society of Automotive flow of data into Washington for evaluation and processing. A very Engineers, National Air Transportation Meeting, Atlanta, Ga., May essential part of this process is an increasing 'involvement of airport 10-13, 1971, Paper 710425. 9 p. 9 refs. Members, $1.00; non- managements, various elements of FAA, and others having a direct members, $1.50. interest in providing input to a plan which it is hoped, will reflect the Review of the application of the MADAR (Malfunction Detec- best effort possible in defining a national system of aiiports. M.M. tion, Analysis, and Recording) System in the MAC (Military Airlift Command) environment. Some of the implications of applying a computerized system of this type to alleviate problems in the A7 1-28307 Expansibility and economy of terminal struc- commercial aviation environment are examined. The MADAR tures. Jack D. Downey. Society of Automotive Engineers, National System, an on-board monitor and processor, employs an 8192-word Air Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper general purpose computer which affords an automatic monitoring 710418. 5 p. Members, $1.00; nonmembers, $1.50. capacity of 1024 data points. The system as currently configured Discussion of criteria and problems connected with the future monitors 800 signals, providing fault-isolation capability for 1894 design of airport terminals. It is pointed out that, in planning LRUs (Line Replaceable Units). Go-no-go decisions relative to proper terminal structures, it must be recognized that economy and operation of black boxes, as well as assessment of engine condition expansibility are corequirements and must be mutually involved. by means of the mechanized gas-generator technique, are performed Four dimensions of terminal planning and construction should be on board the aircraft, and the results are available in real time. This considered. In addition to the usual dimensions of length, height, and essentially reduces the response time to zero, eliminates dependence width, time is an equally important component. The linearhnit on ground computers, and allows the system outputs to be applied to terminal concept tends to wed these dimensions into a superior short-term maintenance problems. M.M. facility. The extensive use of dimensional planning can make a facility long-lived. M.M. A71-28312 Development of the Lockheed L-1011's flying stabilizer. C. A. Whitmore w lockheed-California Co.. Burbank, Calif.). Society of Automotive Engineers, National Air Transporta- A71 -28308 Development progress on CF6 engines. B. H. tion Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710426. 13 p. Rowe (General Electric Co., Aircraft Engineering Group, West Lynn, Members, $1 .OO; nonmembers, $1.50. Mass.). Society of Automotive Engineers, National Air Transporta- Longitudinal control on the Lockheed L-1011 is provided by a tion Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710421. 14 p. flying stabilizer. This is the first time such an approach has been used Members, $1 .OO;nonmembers, $1.50. on a United States commercial jet transport. This paper presents the The development of commercial engines requires adequate reasons for the choice of longitudinal control systems, and describes testing to assure reliable low cost operation in service. Problems the mechanization of the control system with particular emphasis on experienced as a result of severe endurance testing, and the design how it meets Lockheed's safety standards and the Federal Air- changes which solved these problems, are described in detail. worthiness Requirements. The status of the ground and flight Adequate performance margin is essential to alluw concentrated development tests is discussed. (Author) efforts in the area of reliability and long life. (Author)
A71-2831 3 Beryllium brake experience on the C-5A air- A7 1-28309 Olympus 593 for Concorde updating of plane. Robert D. Gilson (Lockheed-Georgia Co., Marietta, Ga.). development position. M. H. Beanland (Rolls-Royce, Ltd., Bristol Society of Automotive Engineers, National Air Transportation Engine Div., Bristol, England). Sociery of Automotive Engineers, Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710427. 10 p. National Air Transportation Meeting, Atlanta, Ga., May 10-73, 1971, Members, $1 .OO; nonmembers, $1.50. Paper 710422. 11 p. Members, $1.00; nonmembers, $1.50. The critical design weight environment necessary to optimize The development program on the Olympus 593 pure jet twin load-carryingefficiency of the C-5A was such that breakthroughs in shaft engine has been in existence about 51/2 years. Throughout the technology were needed. One such breakthrough was beryllium program a policy of matching engine rating to aircraft requirements brakes. From the discovery of beryllium in 1798 its advantages - as
405 A71-28314
well as its disadvantages - were well known. These are discussed to $1.50. indicate why beryllium was chosen as the brake heat sink material This paper details PT6 reduction gearbox reliability problems as for the design configuration evolved. A review of current C-5A data revealed by development testing and regular service. Initial bench is presented, including flight test experience, as well as expected life tests showed that despite attempts to design within the state-of-the- projection from limited normal operational experience. The re-use of art, the application was such as to require an extension of beryllium elements, and cost effectiveness are also discussed. A contemporary knowledge of gear design. CaviJation erosion of the consideration of the future use of beryllium is indicated, with the planet gear bushings gave rise to some anxiety and excessive wear of conclusion that it will become commonplace in the next decade. coupling splines necessitated a redesign. These and other minor (Author) problems were largely resolved before certification and delivery of the first production units. Except for an incident with units operating in Arctic conditions, no significant reliability problems A71-28314 Study of visible exhaust smoke from aircraft have occurred in regular service. Some wear problems have been jet engines. John Stockham and Howard Betz (IIT Research corrected with subsequent benefit to overhaul costs but most Institute, Chicago, 111.). Society of Automotive Engineers, National complaints have been generated by weepage from the propeller shaft Air Transportation Meeting, Atlania, Ga., May 10-13, 1971, Paper oil seal. This was not an operational hazard. Models in current 710428. 19 p. 13 refs. Members, $1.00; nonmembers, $1.50. production are little different from the initial production standard, Contract No. FA-69-2208. although some have been certified for maximum powers nearly 50% Study of the relation between the visibility of in-flight jet greater than the first units and the minimum approved time between exhaust and the AIA smoke number. A method based on photo- overhauls, for operation in the US., is now 3000 hr. (Author) graphic photometry was developed for measuring the optical density of smoke plumes. This method was related to visibility and to the smoke number through transmissometer measurements and visibility A71-28320 Microbiological contamination of aircraft fuel theory. A portable transmissometer, capable of operating over a wide tanks . Airframe considerations. J. A. Scott (British Aircraft Corp., range of optical pathlengths and under varying ambient light Ltd., Weybridge, Surrey, England). Society of Automotive Engineers, conditions, was fabricated for use in this study. A mathematical National Air TransportationMeeting, Atlanta, Ga., May 10- 13, 1971, expression relating the transmission measurements to the smoke Paper 710438. 8 p. 17 refs. Members, $1 .OO;nonmembers, $1.50. numbers was derived. Liminal visibility requirements of smoke trails, Discussion of microbiological contamination, which became a developed from light scattering theory, were correlated with actual major problem when jet aircraft using integral fuel tanks began visual observations and the transmissometer and photometry mea- operations in tropical areas. Aircraft operating in such areas should surements. Test results, with the engines investigated, indicate that be regularly inspected in order to detect contamination before it AIA smoke numbers below 23 were associated with invisible exhaust reaches .serious proportions, and maintenance personnel should be plumes. Samples of the exhaust smoke showed the particles to be trained to recognize and interpret warning signs. Maintenance composed of lacy agglomerates. At the nozzle, the geometric median practices should be adjusted where possible to minimize the amount particle diam was 0.052 micron. At a distance of 10 nozzle diam the of water collecting in fuel tanks. Biocides may be needed under geometric median particle diam was 0.13 micron at cruise condition. certain conditions. Good fuel-quality control is extremely important, (Author) and particular attention is required at the smaller airports. Good results are being obtained with epoxy primer protective coats heavily A71-28316 FAA appraisal of aircraft design for maintain- pigmented with strontium chromate. F.R.L. ability. James E. Dougherty (FAA, Washington, D.C.). Society of Automotive Engineers, National Air Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710431. 10 p. 23 refs. A71-28321 Electrical and physical nature of microbial Members, $1 .OO;nonmembers, $1.50. membranes implicated in aircre 't fuel quantity probe malfunction. This paper outlines an appraisal of aircraft design for maintain- W. 8. Engel and R. M. Owen (Douglas Aircraft Co., Long Beach, ability as viewed by the Federal Aviation Administration. The basis Calif.). Society of Automotive Engineers, National Air Transporta- for FAA's authority in the Act is set forth. The extent of the tion Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710439. 10 p. 28 applicable requirements now in the Federal Air Regulations is traced. refs. Members, $1 .OO;nonmembers, $1 30. Maintenance concepts and examples of adverse airworthiness situa- Demonstration that microbial membranes have a low resistance tions are described. Controls and procedures employed by FAA to and could easily short out a fuel quantity probe. To determine how account for maintainability of new designs, including MSG-2, are microbial contamination can cause probe malfunction an artificial explained. Maintainability guidelines applicable to new designs are environment conducive to the rapid growth of microbial membranes advanced. (Author) was developed. Studies were conducted on membranes grpwn in this environment to determine their electrical conductive properties, and it was found that the membranes are sufficiently conductive to cause A71-28317 One operator's look at maintainability. the malfunction. Prolonged association of microbial contamination William A. Keeler (Eastern Air Lines, Inc., New York, N.Y.). Society on the probe surface will result in eventual coating penetration and of Automotive Engineers, National Air Transportation Meeting, pitting-type corrosion. F.R.L. Atlanta, Ga., May 10-13, 1971, Paper 710432. 6 p. Members, $1.00; nonmembers, $1.50. Spiraling commercial airplane equipment costs will not tolerate A71-28322 Salt driers assure really dry fuel to aircraft. H. operational inefficiency. The airline operator must keep his depar- R. Porter, G. R. Deits (Standard Oil Company of California, San ture gates well-stocked with mechanically sound equipment if he is Francisco. Calif.). J. A. Bert, and B. C. Anderson (Chevron Research to realize a reasonable return on his investment. The role of Co., Richmond, Calif.). Society of Automotive Engineers, National maintainability in assuring equipment readiness is reviewed from the Air Transportation Meeting, Atlanta, Ga., May 10-13. 1971, Paper viewpoint of one airline operator, and six basic keys to good airplane 710440. 8 p. Members, $1 .OO;nonmembers, $1.50. equipment maintainability are discussed. (Author) Salt driers installed in an airport jet fuel delivery system reduced the fuel water content below saturation, lengthened filter life, and improved the performance of the downstream system components. A71 -2831 8 Development and service experience of the Systems must be designed and operated to control salt carry-over. PTGA reduction gearbox. A. W. Stewart and D. Hollingworth (United The high initial cost of salt driers compared with conventional Aircraft of Canada, Ltd., Montreal, Canada). Society of Automotive filter-coalescers may be justified by low operating cost, improved Engineers, National Air Transportatbn Meeting, Atlanta, Ga., May microbial control, and customer satisfaction. Salt driers have a place 10-13, 1971, Paper 710433. 7 p. Members, $1.00; nonmembers, in airport fuel treating. (Author)
406 A71 -28330
A71-28323 From automatic landing to Category Ill. power unit (APU) that will provide an alternate source of power, in William Russell (Air Transport Association of America, Washington, flight and on the ground, for aircraft hydraulics, pneumatic drives, D .C.). Society of Automotive Engineers, National Air Transportation APU starting, environmental control, main engine starting, electrical Meeting, Atlanta, Ga., May 10.13, 1971, Paper 710441. 7 p. 5 refs. power generation, power transfer to accessory gearbox for shaft- Members, $1 .OO; nonmembers, $1.50. driven accessories, plus the power distribution system to inter- Progress toward full all weather landing operation of transport connect these components. This paper discusses the application of aircraft is evaluated. Experience with Category II instrument this integrated concept and the associated analyses of operating approach operations in actual weather is reviewed. The disparity characteristics of major components. Appropriate interface and between the lagging implementation of ground facilities in the compatibility with the total air vehicle is illustrated. Significant United States, and the extensive implementation of costly Category parameters such as power, weight, efficiencies, product assurance II airborne equipment is discussed. Actions needed to provide viable characteristics. etc., are compared. (Author) Category IIla operations are examined, including discussion of procedures to aid in insuring integrity, and the need for implement- ing Category Illa facilities in the United States. Implications of the A7 1-20327 Contemporary approach to commercial power- proposed new landing guidance system and of possible independent plant development. G. W. Kleinert (General Electric Co., New York, landing monitors are also examined. Limitations of availaue weather N.Y .I. Society of Automotive Engineers, National Air Transportation surveys and a number of econcmic considerations are pointed out. Meeting, Atlanta, Ga., May 10.13, 1971, Paper 710449. 8 p. Aggressive implementation of ground facilities is recommended. Members, $1 .OO;nonmembers, $1.50. (Author) Vital to the success of the turbine powered airplane is the degree to which the engine manufacturer can develop the entire powerplant to its fullest maturity early in the life of the airplane system. With A71-28324 Development testing of the L-1011 Indepen- increasing demands for shorter powerplant development cycles, to dent Landing Monitor. Gerald Holliday and John A. Gorham meet the needs of the shorter airframe development cycle, new (Lockheed-CaliforniaCo., Burbank, Calif.). Society of Automotive techniques and methods are being employed to accelerate the Engineers, National Air Transportation Meeting, Atlanta, Ga., May development of contemporary powerplants. Equally important to 10-73, 1971, Paper 710443. 15 P. Members, $1.00; nonmembers, the improved development techniques and methods is the ability to $1.50. establish and monitor the technical progress early in the powerplant A new, completely independent monitor (capable of operation development program. This paper will describe, the approach taken in through Category I IIc weather condition) for use with automatic the development of the CF6 family of engines, including techniques landing systems is undergoing development by Lockheed for possible established to monitor technical progress. (Author) use in L-1011 aircraft. Following intensive analysis, a K sub a band airborne radar was selected to provide pilot confidence through independent monitoring of the L-1011 (1) dual-dual, fail operative, A71-28328 Propulsion testing from the aircraft manufac- automatic landing system’s performance. Lockheed’s airborne flying turers’ point of view. A. Reinhart (Boeing Co., Seattle, Wash.). test bed (CV-240) program has so far provided evidence that the W. Independent Landing Monitor concept has a definite futur in Society of Automotive Engineers, National Air Transportation commercial automatic landing applications under reduced visibilities. Meeting, Atlanta, Ga., May 10-?3,1971, Paper 770450. 22 p. Visual enhancement would improve the acceptability of near Member;, $1 .OO;nonmembers, $1.50. zero-zero operation and consequently reduce the number of un- Consideration of aircraft propulsion systems in terms of the necessary go-arounds. (Author) total aircraft system. The design requirements tend to become more demanding and the development and proof testing more exacting to assure that the test simulation of the critical operating envirdnment is correct and that the instrumentation systems are adequate for A71 -28325 * Design criteria for selection of aircraft electric power generation and distribution systems. C. H. Lee (AiResearch accurately and quickly obtaining the required information. Careful judgment and ingenuity are required to obtain the data in a timely Manufacturing Co., Los Angeles, Calif.). Society of Automotive and cost-effective manner. Major areas which are becoming more Engineers, National Air Transportation Meeting, Atlanta, Ga., May critical with each generation of aircraft are noise reduction and 10-13, 1971, Paper 710444. 12 p. Members, $1.00; nonmembers, inlet-engine-exhaust system compatibility. Examples of problems $1.50. Contract No. NAS 12-659. which have been faced in recent subsonic aircraft and some of Conventional aircraft use constant-speed drive to generate particular interest in such aircraft as the SST are discussed. F.R.L. constant frequency 400-Hz power of relatively good quality and distribute it at 115/200 V. A detailed study revealed that this power type is not the optimal choice for present and future aircraft A71-28329 Powerplant testing from an operator‘s perspeo- applications. This paper presents the advantages and disadvantages of tive. R. E. Totman (United Air Lines, Inc., Chicago, 111.). Society of various generation and distribution systems and the factors to be Automotive Engineen, National Air Transportation Meeting, considered in selecting an electric power system. For medium and Atlanta, Ga., May 10-13, 1971, Paper 710451. 8 p. Membek, $1.00; large size STOL aircraft, it appears that variable-frequency generation nonmembers, $1.50. and high-voltage d-c distribution with secondary square wave a-c Summary of airline engine performance testing by three distribution may be superior to the conventional system. (Author) precepts: (1) avoid release of engines which will be maintenance problems; (2) prevent rejection of engines which will operate satisfactorily until the next scheduled removal; and (3) reduce testing A7 1-28326 Optimization of military VTOL secondary costs. The methods used most profitably to assign relative weights to power systems. Dennis Stein (Boeing Co., Vertol Div., Philadelphia, the three guidelines are presented, and progress with an automated Pa.) and Jules Vichness (US. Army, Air Mobility R & D Labora- test cell data acquisition system is outlined. F.R.L. tories, Fort Eustis, Va.). Society of Automotive Engineers, National Air Transportation Meeting. Atlanta, Ga., May 10-13, 1971, Paper 710445. 18 p. Members, $1.00; nonmembers, $1.50. A71-28330 The cornheliability relationships of develop Military VTOLlVSTOL aircraft are required to operate in areas ment testing and demonstration. Kirk G. Rummel and Robert B. where it is impractical to provide ground support equipment to Aronson (Boeing CO., Vertol Div., Philadelphia, Pa.). Society of supply types of power needed for system checkout, emergency and Automotive Engineers, National Air Transpdrtation Meeting, standby power, and main engine starting. To provide this capability. Atlanta, Ga., May 10-13, 1971, Paper 710452. 10 p. Members. the Secondary Power System must be considered on an integrated $1 .OO; nonmembers, $1 30. basis as a major aircraft subsystem which incorporates-an auxiliary This paper explores the relationships between the costs of
407 A71-28331 developmental testing and the derived benefits in reliability. The A71-28334 Coated columbium for gas turbine engine analysis quantifies this relationship for the components of the application. J. F. Holloway, H. A. Hauser, and E. F. Bradley (United dynamic system of a specific future helicopter. Distinctions are Aircraft Corp., Pratt and Whitney Aircraft Div., East Hartford, drawn between test costs related to reliability requirements and Conn.). Society of Automotive Engineers, National Air Transporta- those that are not related. Emphasis is placed on the decisionmaking tion Meeting, Atlanta, Ga., May 10.13, 1971, Paper 710460. 9 p. 9 process that is required when formal reliability and maintainability refs. Members, $1 .OO; nonmembers, $1.50. (R & M) demonstration tests are imposed. The statistical aspects of Application of coated columbium alloys to gas-turbine engine demonstration tests are examined and related to the program components operating at metal temperatures above 2000 F. This is a manager's informational requirements. (Author) potentially viable alternative to more complex cooling schemes for present nickel-base and cobalt-base superalloys. The major deterrent to the use of this material centers around the performance and A71-28331 Analysis of transmission failure modes. C. W. reliability of protective coatings such as slurry silicides. Turbine Bowen (Bell Helicopter Co., Fort Worth, Tex.). Society of Auto- vanes so protected have successfully run in a turbine development motive Engineers, National Air Transportation Meeting, Atlanta, Ga., engine for 100 hr of steady state and cyclic operation. A film-cooled May 10-13, 1971, Paper 710454. 7 p. 8 refs. Members, $1.00; burner liner of FS-85 columbium alloy sheet material coated with nonmembers, $1.50. the Sylvania SiCrFe slurry coating has been fabricated and will be rig- This paper presents a synopsis of an extensive failure mode and engine-tested. F.R.L. investigation and analysis of Bell UH-1- and Vertol CH-47 trans- missions. Correlation of these observed field experiences with convenrional design stress analysis techniques and preliminary bench A71-28335 High temperature turbine design considera- test data is presented. Lubrication states as defined by elasto- tions. S. N. Suciu (General Electric Co.. New York, N.Y.). Society of hydrodynamic film thickness calculations are shown to offer Automo tive Engineers, National Air Transportation Meeting, explanation for the existence of many failure modes which are not Atlanta, Ga., May 10-13, 1971, Paper 710462. 13 p. 14 refs. predicted by conventional analyses. Simple statistical methods for Members, $1 .OO; nonmembers, 51.50. failure data analysis are employed as an aid to assessing relative gain The major technological developments which have made in reliability afforded through correction of dominant failure modes. possible the trend towards higher temperatures in modern aircraft gas The premise is advanced that the key to successful design of turbine engines are discussed. The relative importance of manufac- advanced helicopter power transmissions featuring significant turing processes, material developments, cooling techniques, analyti- increases in operational reliability may be found in the application of cal design procedures, rupture and cyclic life considerations, and these lessons. (Author) aerodynamic and mechanical design improvements are discussed along with illustrative examples and technical data. The need for a balanced design approach is stressed, and examples are given where A71-28332 Area navigation in the ATC environment. E. E. trade-offs can be made. It is noted that the advances in aircraft Glanz (Eastern Air Lines, Inc., New York, N.Y.). Society of engines during the last 10 years have been based on the evolution of Automotive Engineers, National Air Transportation Meeting, sound engineering principles, extensive component and engine Atlanta, Ga., May 10-13, 1971, Paper 710455. 5 p. Members, $1.00; development, and careful consideration of the operational require- nonmembers, $1.50. ments rather than a tremendous breakthrough or revolutionary Aircraft equipped with computerized Area Navigation Systems concept in any one area. (Author) have created the need for an entirely new air traffic control environment. This paper will highlight problems encountered as the ATC system begins its evolution toward area navigation, and will A71-28336 Military/commercial STOL transport com- suggest operational techniques favorable to a total area navigation monality. Harold F. Kleckner (Douglas Aircraft Co., Long Beach, ATC environment. Conventional interfaces are no longer useful. Calif.). Society of Automotive Engineers, National Air Transporta- Independent systems (computer, controller, pilot, route structure, tion Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710468. l l p. and aircraft) meet in the cockpit, but satisfactory communications Members, $1 .OO; nonmembers, $1.50. have not been established. Pilot reaction indicates that the informa- Military and commercial turbofan STOL transport work at the tion is not now properly presented in the cockpit. Attempts to solve Douglas Aircraft Company during the past four years has led to the these interface problems have indicated that the solution lies in consideration of commonality between the USAF medium STOL comprehensive software programs and clear situation displays for the transport and a short-range, medium-sized commercial STOL trans- pilot. (Author) port. General requirements for the two airplanes appear to be similar and include a cruise speed of Mach 0.75-0.80 for a 500-nauticalmile range after takeoff from a 2000-foot airstrip. Both require a wide body; and the payload, furnishings, and equipment yield comparable A71-28333 Requirements, performance and integration of STOL takeoff ,weights. Both can be designed with a high wing, a modern navigation aids. A. 8. Winick and D. M. Brandewie (FAA, moderate wing loading, and the same STOL lifting concept. A Washington, D.C.). Society Automotive Engineers, National Air of common engine size appears feasible, and basic engine characteristics Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper such as bypass ratio need not be differeht. Results of a preliminary 710456. 6 p. 9refs. Members, $1.00; nonmembers, $1.50. commonality study are presented in which several cases with varying The need to improve the efficiency and capacity of the Air degrees of commonality are evaluated in terms of costs. The cost Traffic Control and Navigation System has placed greater emphasis benefits of shared development and production were found to on the functional integration of subsystems which have been treated outweigh the penalties related to design compromises, resulting in independently in the past. This paper presents results of limited test programs designed to explore the relationship of terminal area lower costs for both military and commercial operators. (Author) navigation and the air traffic control system, and to show the benefits of an optimum combination of both functions. The need for further analysis is indicated with respect to carrying out the third A71-28337 STOL engine systems and sensitivity factors. generation system design postulated by the DOT Air Traffic Control Joel Godston (United Aircraft Corp., Pratt and Whitney Aircraft Advisory Committee. It is concluded that functional integration of Div., East Hartford, Conn.). Society of Automotive Engineers, ATC and navigation in the terminal area presents the greatest National Air TransportationMeeting, Atlanta, Ga., May 10- 13, 1971, challenge. In other areas, such as enroute, the availability of new, Paper 770469. 11 p. 22 refs. Members, $1.00; nonmembers, $1.50, integrated avionics systems provides an expanded operational capa- The purpose of this paper is to list the possible competitive bility. (Author) engine systems for the STOL aircraft likely to be operational in the
408 A71 -285.84 late 1970s or early 1980s. The importance of integrating the engine circulation. A method is proposed by which the eftect of axial and airframe during the early design phase of the STOL aircraft velocity variation on a known two-dimensional flow or alternatively system is outlined. A description of typical augmented wing and the two-dimensionalequivalent of a flow with axial velocity variation blown flap engine concepts under investigationand the system trade can be calculated. The method is very easy to apply. The deviation factors affecting aircraft gross weight and potential return on may increase or decrease depending on the change in blade investment are presented. System trade factors including noise, circulation and the stagger. An increase in apparent deflection weight, performance, and cost are evaluated to provide an overall through the cascade can be accompanied by a reduction in the blade view of the compromises that are, or must be made in order that the force. The method would be particularly useful for the interpretation STOL aircraft engine system be a viable commercial product. The of cascade wind tunnel data and in the design of impeller stages available and required engine technologies are reviewed. (Author) where three-dimensional flows occur. (Author)
A71-28338 Prop-Fan - A high thrust, low noise propulsor. A71-28489 # Helicopters as cranes, and carrying external George Rosen (United Aircraft Corp., Hamilton Standard Div., loads. It - The planning and the constructive design of 'crane Windsor Locks, Conn.). Society of Automotive Engineers, National helicopters' (Kran- und Aussenlastflug mit Hubschraubern. I1 - Die Air Transportation Meeting, Atlanta, Ga., May 10- 13, 1971, Paper Auslegung und die konstruktive Gestaltung von Kranhubschraubern). 710470. 12 p. 12 refs. Members, $1 .OO; nonmembers, $1.50. Michael Caspari. Technisch-okonomische lnformationen der zivilen The Prop-Fan is introduced as a new propulsor type, inter- Luftfjhrt, vol. 7, no. 3, 1971, p. 133-142. In German. mediate between ducted propellers and low bypass fans. Compared The disadvantages of a use of multipurpose helicopters for to today's fan engines, it offers approximately twice the takeoff flights with external loads are analyzed. The demand for helicopters thrust/hp at half the tip speed and consequently much reduced noise designed exclusively for applications as a crane was found to be very level. Furthermore, its controllable pitch feature provides more limited in a market analysis. However, there appear to be good effective reverse thrust at about one-fourth the weight of current employment possibilitiesfor a helicopter which in addition to serving flow reversers. Prop-Fan characteristics are particularly well matched as a crane can also, transport external loads. A number of designs to the propulsion requirements of advanced STOL transport aircraft. proposed for such a helicopter are described. The landing gear is Highlighted is the uniquely low noise signature of the Prop-Fan. This designed in such a way as to make it possible for the helicopter to now permits the design of medium-to-longrange STOL transports of land in many cases above the load and pick it up. G.R. high-productivity which will meet the stringent noise level limits for STOL-ports. The paper describes the development status of the Prop-Fan, examines potential aircraft installation arrangements, and presents some representative STOL transport effectiveness com- A71-28582 # Assessment of measurement errors in the parisons. (Author) testing of axial-flow compressors and turbines (K voprosu otsenki pogreshnostei izmerenii pri ispytaniiakh osevykh kompressorov i turbin). A. P. Tunakov, Iu. A. Rzhavin, and S. G. Ibragimov. Kazanskii Aviatsionnyi Institut, Trudy, Seriia Aviatsionnye Dvigateli, A71 -28339 Boeing 747 training developments and imple- no. 114,1970, p. 3-17.5 refs. In Russian. mentation. B. M. Tate (TransWorld Phlines, Inc., Kansas City, Mu,,. Experiments performed with single-stage air-driven compressors Society of Automotive Engineers, International Simulation and and turbines with the aim of improving the methods of assessing the Training Conference, 4th, Atlanta, Ga., May 13, 1971, Paper 710473. 5 p. Members, $1 .OO;nonmembers, $1.50. accuracy of the parameters measured are described. An analysis of the formulas conventionally used for calculating the rms error of A training program for crew members of the TWA 747 is indirect measurements (when the error of the direct measurements is described. The paper begins with the formulation of general policies known) shows most of the error involved in the determination of and their translation into a ground training program, and continues torque and temperature is due to the error contained in the with descriptions of the classroom, inertial navigation system, and approximating coefficients. The largest error in the determination of cockpit trainers. The details of the training program afe presented, as the flow rate may be attributed to the errors involved in the flow are a description of the TWA 747 simulator and discussion of coefficient and in the coefficient of flow convergence in the anticipated problems. (Author) measuring orifice. Improved formulas for calculating the principal parameters of turbomachines are proposed. V.P.
A7 1-28340 The use of simulation to promote safety and economy in flying training. W. P. Moran (American Airlines, Inc., A71-28583 # Investigation of the ideal cycle of a New York, N.Y.). Society of Automotive Engineers, International continuouscombustion gas turbine with stepwise heat release Simulation and Training Conference, 4th, Atlanta, Ga., May 13, (overexpansion cycle) (Issledovanie ideal'nogo tsikla gazoturbinnoi 1971, Paper 770475. 6 p. Members, $1 .OO;nonmembers, $1.50. ustanovki nepreryvnogo goreniia so stupenchatym otvodom tepla The combination of simulation and improved training tech- /tsikl s pererasshirenieml). A. P. Tunakov and B. Kh. Perel'shtein. niques ensures a safe and economical flying training program. In a Kazanskii Aviatsionnyi Institut, Trudy, Seriia Aviatsionnye Dvigateli, 5-year period, American Airlines has reduced airplane training and no. 114, 1970, p. 18-30, In Russian. flight check hours by more than 75%. There are strong indications The thermal efficiency of a cycle in which the gas is cooled after that, for qualified airline crewmen, a goal of total simulation for all overexpansion and is then compressed in a low-density compressor to training and flight checks will become a reality. (Author) the ambient pressure is analyzed. The efficiency of an ideal cycle of this type is compared to that of the Brayton and Carnot cycles, and the parameters of the ideal cycle are evaluated on the basis of several numerical examples. V.P. A71-28467 Effect of axial velocity variation in aerofoil cascades. S. Soundranayagam (Indian Institute of Science, Bangalore, India). Journal of Mechanical Engineering Science, vol. 13, Apr. A71-28584 # Gasdynamic verification calculations of multi- 1971, p. 92-99. 12 refs. Research supported by the North of stage axial-flow compressors on a digital computer (Proverochnyi Scotland Hydro-Electric Board. gazodinamicheskii raschet osevykh mnogostupenchatykh kompres- The effect of the variation of axial velocity in the in- sorov na ETsVM). A. P. Tunakov and S. G. Ibragimov. Kazanskii compressible flow through a cascade of aerofoils is discussed and it is Aviatsionnyi lnstitut, Trudy, Seriia Aviatsionnye Dvigateli, no. 114, shown that changes take place in the flow angles and in the blade 1970, p. 31-47. 6 refs. In Russian.
409 A71 -28586
An algorithm for testing the gasdynamic design of axial-flow criticality, and altitude relight considerations of the combustion compressors, particularly in the final adjustment phase, is proposed. system of the Concorde SST throughout the Olympus engine series. Particularly well suited for calculating the parameters of blade rings, The problem of flame tube wall temperatures is discussed, together. the procedure is suitable for use in the design phase if data on the with the smoke problem, the introduction of a lightweight fuel loss coefficients in empirical formulas have been established. V.P. system, flame tube design, the use of fully machined cooling rings, and design modifications to improve the mechanical life of the combustion system. Combustion efficiency and pressure loss, and the A71728586 # Influence of bypass of air behind the com- low-pressurefuel sprayer are also treated. M.M. pressor into a variable-area exhaust nozzle on gas turbine jet engine indices (Vliianie perepuska vozdukha posle kompressora v reaktivnoe soplo na pokazateli gazoturbinnykh reaktivnykh dvigatelei). V. A. A71-28742 The evolution of the RB 162 combustion Kosterin, V. T. Dudkin, and L. V. Fadeev. Kazanskii Aviatsionnyi system for V.T.O.L. applications. J. R. Poyser and H. B. Moxon Institut, Trudy, Seriia Aviatsionnye Dvigateli, no. 114, 1970, p. (Rolls-Royce, Ltd., Derby, England). In: Combustion and heat 58-76.In Russian. transfer in gas turbine systems; Proceedings of an International Formulas are derived which define the dependence of a turbojet Propulsion Symposium, College of Aeronautics, Cranfield, Beds., engine on the energy losses in the afterburner in the case where small England, April 15-17, 1969. Edited by E. R. amounts ot air behind the compressor are applied to the exnaust Norster. Oxford, Pergamon Press, Ltd. (Cranfield International nozzle. By taking into account the coefficients defining the changes Symposium Series. Volume II), 1971,p. 33-61;Discussion, p. 62. in the gas pressure and temperature behind the turbine owing to the Description of. the design and development of the RB 162 added air, the formulas make it possible to obtain solutions for any combustor. The RB 162 combustor incorporated many of the energy losses associated with the expansion and the mixing of the features of the single-reversal chamber but differed in one or two added air with gas behind the turbine. V.P. interesting respects. The RB 162 was designed to achieve ignition with the aid of two pressure jet atomizers operative only during the starting cycle. Weight estimates of the complete starter system favored the latter arrangements. In conjunction with combustor rig A71-28589 # Heat and mass transfer in the turbulent flow of a chemically active gas in the manifolds of a hydro-jet engine tests, extensive use has been made of sectored, full-size perspex (Teplomassoobmen pri turbulentnom techenii khimicheski aktivnogo models to examine the aerodynamic behavior of the RB 162 gaza v kanalakh GRD). A. V. Fafurin and Iu. D. Krechetnikov. combustion engine. Of the substantial volume of testing carried out Kazanskii A viatsionnyi lnstitut, Trudy, Seriia Aviatsionnye Dvigateli, on the perspex models, typical instances illustrating this approach are given. no. 114,1970,p. 101-104.5 refs. In Russian. A method for calculating the ablation of a heat shield under the effects of a high-enthalpy chemically active gas flow is developed on the basis of boundary layer theory and the corresponding friction A71-28743 Some combustion aspects of plenum chamber and heat transfer laws. The method is based on the assumptions that burning. A. Sotheran (Rolls-Royce, Ltd., Bristol, England). In: the components of the main gas flow which react with the wall Combustion and heat transfer in gas turbine systems; Proceedings of material form a binary mixture with the reaction prodhts; that all an International Propulsion Symposium, College of Aeronautics. components of the mixture in the boundary layer obey the ideal gas Cranfield, Beds., England, April 15-17,1969. laws; and that the chemical reaction rate is limited by the supply of Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. (Cranfield the oxidizer to the surface rather than by the chemical reaction rate. International Symposium Series. Volume 1 I), 1971, p. 63-86; A closed system of equations describing the flow in an axisymmetric Discussion, p. 87, 88. channel in the presence of chemical reactions at the surface is A brief explanation is given of the manner in which aircraft derived. V.P. performance improvements can be obtained by providing PCB on the high by-pass ratio turbofan engines of subsonic VTOL aircraft of the Harrier type. The necessity of PCB to supersonic developments is A71-28739 Combustion and heat transfer in gas turbine noted. An account is then given to the design considerations behind systems; Proceedings of an International Propulsion Symposium, the choice of the 'staggered gutter colander' combustion system for College of Aeronautics, Cranfield, Beds., England, April 15-17, 1969. PCB, and of the experimental development program which led, Edited by E. R. Norster (Cranfield Institute of Technology, eventually, to the successful demonstration of PCB on an adapted Cranfield, Beds., England). Oxford, Pergamon Press, Ltd. (Cranfield Pegasus engine. (Author) International Symposium Series. Volume 11). 1971. 397 p. $27. The topics include the combustion system for the Olympus 593 A71-28745 Ignition theory and its application to the engine, combustion chamber temperature profiles, the RB 162 altitude relighting performance of gas turbine combustors. A. H. combustion system for VTOL applications, annular vaporizing Lefebvre (Cranfield Institute of Technology, Cranfield, Beds., combustion chambers, ignition theory and its application to the England). In: Combustion and heat transfer in gas turbine systems; altitude relighting, the air recirculation ratio in can-type gas turbine Proceedings of an International Propulsion Symposium, College of combustion chambers, assessment of flame tube temperatures in a Aeronailtics, Cranfield, Beds., England, April 15-17, 1969. combustor operating under SST conditions, radiation heat transfer, Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. and corrosion testing of high-temperature gas turbine alloys. (Cranfield International Symposium Series. Volume 11). 1971, p. M.M. 105-116; Discussion, p. 117-119. 28 refs. The various ignition theories fall into two groups: those in which diffusion is considered to be the dominant process in flame initiation; and those in which thermal mechanisms are considered A71-28740 The combustion system for the Olympus 593 more important. Two equations which show broad agreement with Concorde engine. D. W. Harvey (Rolls-Royce, Ltd., Bristol, England). practical experience in regard to the effects of pressure, temperature In: Combustion and heat transfer in gas turbine systems; Proceedings and velocity, provide quantitative relationships between the main of an International Propulsion Symposium, Colleye of Aeronautics, variables influencing the ignition process. The most significant factor Cranfield, Beds., England, April 15-17, 1969 influencing ignition performance, however, is velocity. It is suggesred Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. (Cranfield that these two equations could prove useful in assessing the relative International Symposium Series. Volume 11). 1971,' p. 3-17; importance of the various factors influencing ignition performance in Discussion, p. 18, 19. practical combustion chambers and in the correlation of ignition data Discussion of the operating conditions, combustion performance obtained from such systems. M.M.
41 0 A71-28758
Cranfield, Beds., England, April A71 -2874% Cooled gas turbine blades. J. F. Barnes and J. 15-17, 1969. P. Edwards (National Gas Turbine Establishment, Farnborough, Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. (Cranfield Hants., England). In: Combustion and heat transfer in gas turbine International Symposium Series. Volume 11). 1971, p. 309-323; systems; Proceedings of an International Propulsion Symposium, Discussion, p. 324,325. 11 refs. College of Aeronautics, Cranfield, Beds., England, April 15-17,1969. Consideration of kerosene-type fuels meeting either the British Edited by E. R. Norster. Oxford, Pergamon D.Eng.R.D.2494 specifications or the ASTM Jet A or A-1 specifica- Press, Ltd. (Cranfield International Symposium Series. Volume 11 ), tions. These fuels are produced mainly by straightforward distillation 1971,p. 167-181;Discussion,p. 182. 14refs. processes, with subsequent treatments to remove sulfur and trace This paper is concerned with the prediction of metal tempera- components. Combustion problems with either type of fuel have tures in rotating blades and with the aerodynamics of coolant flow been largely eliminated by the progressive development of the into and out of the blades. The section on blade temperatures engines although there is a growing preoccupation with the forma- includes a description of two complementary methods currently used tion and emission of smoke during takeoff and landing. The trend of fuel injection systems is towards greater use of air assistance in at the National Gas Turbine Establishment. (Author) atomization and the possible use of fuel vaporization. The possibility of fuel additives for reducing smoke emission is discussed. The problems of bacterial or fungal contamination of aircraft fuel Theoretical assessment of flame tube tempera- A71 -28749 systems still exist. F.R.L. tures in a combustor operating at typical S.S.T. conditions. M. Whittaker (Rolls-Royce, Ltd., Bristol, England). In: Combustion and heat transfer in gas turbine systems; Proceedings of an International Propulsion Symposium, College of Aeronautics, Cranfield, Beds., A71-28756 Some observations of the atomizing charac- England, April 15-17,1969. Edited by E. R. teristics of air-blast atomizers. R. Bryan, P. S. Godbole, and E. R. Norster. Oxford, Pergamon Press, Ltd. (Cranfield International Norster (Cranfield Institute of Technology, Cranfield, Beds., Symposium Series. Volume ll), 1971,p. 183-204.6 refs. England). In: Combustion and heat transfer in gas turbine systems; A typical annular vaporizing combustion chamber project with Proceedings of an International Propulsion Symposium, College of conventional film cooling has been analyzed around a datum Aeronautics, Cranfield, Beds., England, April 15-17, 1969. supersonic cruise condition. The need for accurate prediction of Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. metal temperatures and a better understanding of the processes (Cranfield International Symposium Series. Volume 1 I), 1971, p. involved has been demonstrated by reference to the rapid increase in 343-355;Discussion, p. 356-359.21 refs. compressor delivery temperature over the years. It has been shown An optical method of measuring mean droplet size of sprays due that the dominant primary zone heat transfer process is flame to Dobbins is described and has been used to assess the effect of radiation and every effort should be made to reduce the effective operating variables on the characteristics of an air-blast atomizer. flame radiation temperature and flame emissivity subject to per- Simple variations in the design of the atomizer indicate ways in formance considerations. The gain in wall cooling is approximately which its performance may be improved. Measurements of mean 25-30C for 100 C reduction in mean flame temperature and 30 C for droplet size with ambient pressures ranging from atmospheric up to 0.1 reduction in flame emissivity. M.M. 200 Ib/sq in abs and air-to-fuel ratios covering a wide range show some of the potential advantages of air-blast atomizers for high- pressure gas-turbine engine application. (Author) A71-28751 Correlation of data and prediction of effective- ness from film cooling injection geometries of a practical nature. G. J. Sturgess (General Electric Co., West Lynn, Mass.). In: Combustion A71 -28757 Some considerations of the measurement of and heat transfer in gas turbine systems; Proceedings of an temperatures within aircraft combustion chambers, using a calori- International Propulsion Symposium, College of Aeronautics, metric probe. A. F. Schlader, P. Rouiller, and J. Odgers (UniversitB Cranfield, Beds., England, April 15-17,1969. Laval, Quebec, Canada). In: Combustion and heat transfer in gas Edited by E. R. Norster. Oxford, Pergamon Press, Ltd. (Cranfield turbine systems; Proceedings of an International Propulsion Sympo- International Symposium Series. Volume 1 I), 1971, p. 229-250.24 sium. College of Aeronautics, Cranfield, Beds., England, April 15-17, refs. 1969. Edited by E. R. Norster. Oxford, The simple boundary layer theory of Stollery and El-Ehwany, Pergamon Press, Ltd. (Cranfield International Symposium Series. which has been applied with some success to idealized injection slots, Volume 11). 1971, p. 363-379;Discussion, p. 380,381.5 refs. is extended to account for the velocity defect introduced into the Use of a calorimetric probe to measure gas temperatures in iniected film by the finitely thick slot lip and the boundary layers excess of 1200 C, previously accomplished by gas analysis tech- which exist on it. The resulting equations are used to provide a niques. The device consists of three concentric tubes, the outer two correlation group which is tested against the collected experimental comprising a water jacket around the center one, through which the data from nine practical injection geometries of greatly differing gas is drawn. Sheathed thermocouples are situated at the entry and construction, over wide ranges of velocity and temperature ratios, exit of the coolant qnd a further thermocouple is located in the gas and slot Reynolds number. For individual geometries effectiveness stream immediately opposite to the one at the coolant outlet. Both correlation to plus or minus 5% of unity is achieved; for geometries gas and water flows are metered and the original gas temperature is of the same general class a 'universal' correlation of plus or minus computed by enthalpy balance. The probe design has been modified 10% is obtained. Equations are obtained which describe the data so as to be applicable to turbine gas combustors. In its present form within these limits. These equations are shown to be valid for the equipment should be satisfactory for combustion chamber differing mainstream approach boundary layers and differing tur- applications under laboratory conditions. Consideration is also given bulence levels in both main and injected streams. In view of the to an improved design of probe obviating the need for mass flow present general uncertainties associated with adequately specifying determination and gas analysis measurements. F.R.L. the mainstream conditions for application to the gas-turbine combus- t.ion chamber, the present simple equations are both suitable and convenient for predicting film effectiveness for preliminary design A71-28758 The measurement of temperatures and radical work and thermal analysis. (Author) concentrations in high-temperature, flowinggas streams. D. H. Cotton and C. G. Haupt (Shell Research, Ltd., Thornton Research A71-28754 Fuels for aircraft gas turbine engines. A. Lewis Centre, Chester, England). In: Combustion and heat transfer in gas (Shell Research, Ltd., Thornton Research Centre, Chester, England). turbine systems; Proceedings of an International Propulsion Sym- In: Combustion and heat transfer in gas turbine systems; Proceedings posium, College of Aeronautics, Cranfield, Beds., England, April of an International Propulsion Symposium. College of Aeronautics, 15-17,1969. Edited by E. R. Norster. Oxford,
41 1 A71 -28767
Pergamon Press, Ltd. (Cranfield International Symposium Series. unspecified coefficients which are determined by means of Newton's Volume ll),1971, p. 383-406. 18 refs. method. Typically 8 to 10 iterations are required for convergence This paper describes methods of measuring temperature and when using the epsilon technique. Comparisons are made of solutions radical concentrations in a rig simulating conditions in a ramjet obtained by using this technique and the energy method. (Author) combustion chamber and nozzle. The line-reversal technique for measuring temperatures was not successful, and the errors are explained in terms of interference by chemiluminescence. Radical concentrations were measured by the lithium-lithium hydroxide A71-28841 Plug in relay - Panacea or Pandora's Box. I. method which is described in detail. The results of these measure- Carol (US. Army, Electronics Command, Fort IMonmouth, N.J.), J. ments show that radical concentrations are frozen at or before the Lerner (U.S. Naval Air Systems Command, Washington, D.C.), I. J. throat of the nozzle. The point of freezing correlates with that Soper (USAF, Logistics Command, Wright-Patterson AFB, Ohio), predicted by the Bray criterion of sudden freezing, and although the and E:U. Thomas (Grumman Aerospace Corp., Bethpage, N.Y.). In: freezing is not instantaneous, these results provide experimental National Asscciation of Relay Manufacturers, Annual National Relay confirmation of the hypothesis and an indication of the limits of i'ts Conference, 19th, Oklahoma State University, Stillwater, Okla., validity . (Author) April 27, 28, 1971, Proceedings. Conference co-sponsored by the Oklahoma State University. Scottsdale, Ariz., National Association of Relay Manufacturers, 1971, p. 11-1 to 11-10, refs. A71-28767 High-speed flash photography of jets and 8 study of noises of aerodynamic origin. Marie Merle and J. P. Fragassi Areas where plug-in relays may be used advantageously are (CNRS, Centre de Recherches Physiques, Marseille, France). SMPTE, suggested, and some hazards due to use of plug-in relays are Journal, vol. 80,Apr. 1971, p. 282-285. 9 refs. Translation. examined. Once it has been decided that plug-in relays will be used In the study of noises coming from gaseous supercriticaljets the consideration should be given to minimizing replacement problems in waves were investigated by four separate methods in order to cross the field. A table listing approaches for minimizing plug-in hazards is check the results. With the use of an electronic camera a film was provided. Attention is to be giver1 to the fact that equipment which made showing the evolution of acoustic waves. A sound analysis was is acceptable for ground support equipment may not be acceptable made using a narrow passband analyzer and a microphone sensitive for safety of flight applications in aircraft. G.R. to high frequency. Schlieren photographs show that the waves on one side are out of phase relatively to those on the other side. Convergent-divergent nozzles were used giving Mach numbers from 1 A71-28873 Interference criteria between space-borne and to 4 comparable to sonic nozzles. The jet has a cellular structure at earthbound aeronautical services. B. A. Pontano (COMSAT Systems the exit as shown on shadowgraph pictures. 'Screeches' occur when Integration Laboratory, Clarksburg. Md.). In: Institute of Electrical the jet is overexpanded, A specific ratio of pressure exists for each and Electronics Engineers, Regional Electromagnetic Compatibilitv nozzle which brings about maximum screech. Frequency of oscilla- Symposium, San Antonio, Tex., October 6-8, 1970, Record. tion was determined from 16 views filmed by the schlieren and New York, Institute of Electrical and Electronics shadowgraph methods. Two schlieren photographs demonstrate that Engineers, Inc., 1970, p. V-D-1 to V-D-15. 6 refs. a reflector at the origination of the jet diminishes jet screech by 20 The feasibility of a VHF aeronautical satellite system which dB. (Author) frequency shares the band presently used by the air traffic control (ATC) service is under investigation with the aim of securing efficient utilization of the spectrum. The proposed system will employ a A71-28778 How VAST troubleshoots a doppler radar. combination of spacial separation, antenna directivity, and frequency Joseph J. Stanco (PRD Electronics, Inc., Syotset, N.Y.!. Microwaves, offset (channel interleaving) for providing the required intersystem vol. IO, May 1971, p. 34, 35. isolation. The geometrical aspects of spacial separation and antenna The application of the VAST (Versatile Avionics Shop Test) directivity have been reported elsewhere. The purpose of the present computer-controlled system, developed for performing automatic study was to investigate the protection ratios required for compatible diagnoses and analyses of complete avionic units, to testing failures intersystem operation. Protection ratios measured in the laboratory occurred in an airborne doppler radar receiver transmitter unit for the various operating parameters of detected signal to inter- aboard a carrier is described. Features of the computer program ference, channel separation, and receiver bandwidth correspond with written for this system are briefly characterized. A block diagram world-wide usage. The objective measurements are converted to the illustrating the system is presented. O.H. subjective criteria of intelligibility through a calculation of the articulation index. Protection ratios are provided in tabular form for given intelligibility criteria and operating parameters. (Author) A71-28831 * A comparison of minimum time profiles for the F-104 using Balakhrishnan's epsilon technique and the energy method. Lawrence W. Taylor, Jr., Harriet J. Smith, and Kenneth W. lliff (NASA, Flight Research Center, Edwards, Calif.). In: Inter- A71-28880 # Game theory and the use of game planning national Federation for Information Processing, Symposium on techniques for aircraft evaluation (Spieltheorie und Planspieltechnik Optimization, Nice, France, June 29-July 5, 1969, Proceedings. bei der Flugzeug-Evaluation). Andreas Paul Anton Pechota. Eidge- Edited by A. V. Balakrishnan, M. Contensou, B. nossische Technische Hochschule, Doktor der Naturwissenschaften F. de Veubeke, P. Kree, J. L. Lions, and N. N. Moiseev. Berlin and Dissertation, 1970. 77 p. 16 refs. In German. New York, Springer-Verlag (Lecture Notes in Mathematics. Volume Evaluation of new tactical aircraft for the Swiss Air Force by 132). 1970, p. 327-335. 11 refs. means of extensive operations research studies. Following preevalua- Balakrishnan's epsilon technique is used to compute minimum tion the problem was to choose between a small fleet of high time profiles for the F-104 airplane. This technique differs from the performance aircraft or a larger one of less efficient aircraft. A simple classical gradient method in that a quadratic penalty on the error in air war game was constructed and theoretically treated. The fleets satisfying the equations of motion is included in the cost function to were evaluated in terms'of survival probability and hits obtained, A be minimized as a means of eliminating the requirement of satisfying handplayed noncomputer game was developed which permits alloca- the equations of motion. Although the number of unknown tion of aircraft and other arms of two hostile forces under conditions independent functions is increased to include the state variables, the similar to a hypothetical war. The results are evaluated by a modified evaluation of the gradient of the modified cost is simplified, resulting Wilcoxon text. In order 10 use the game in conjunction with a in considerable computational savings. The unknown control and computer, a model is described which can carry out the task of the state variables are approximated by a functional expansion with umpires during a game. F.R.L.
41 2 A71-28883 # Potential flow interaction between blade rows Discussion of the adjustment of cams of the resilient aneroid in axial-flow compressors. Ching-Yee Ma. Swansea, University sensors of altimeters to make the altimeter readings more accurate. A College, Doctor of Philosophy Dissertation, 1969. 212 p. 50 refs. procedure is described for obtaining cam sets facilitating a more This Ph. D. thesis investigates the potential flow interaction efficient and less laborious cam adjustment process without the effects between blade rows in an axial flow compressor, and a necessity of adjusting individual cams. This procedure can be used as method of analysis for flow through such multiple cascades of blades a basis for producing precision-profile cams by a programmed having finite thickness with relative motion is presented. The flow is process. V.Z. assumed to be incompressible, two-dimensional, and irrotational. The flow equation is formulated in terms of a velocity potential function and is solved by an iterative process based on finite difference A71-28940 # Problem of position determination of the approximations. Calculations for several inlet guide vane-rotor (IGV) neutral layer and critical curvature radius in waffle panels under combinations were carried out, and from these the velocity and purely elastoplastic bending (K voprosu opredeleniia polozheriiia pressure fluctuations at any point in the flow can be obtained. neitral'nogo sloia i kriticheskogo radiusa krivizny pri chistom Experimental studies indicate that the magnitude of the fluctuation uprugo-plasticheskom izgibe vafel'nykh panelei). A. G. Lukashov and depends critically on the IGV-rotor spacing. At a small interspace the M. I. Lysov. Kazanskii Aviatsionnyi Institut, Seriia Aviatsionnaia effect of interference between the pressure fields of the IGV and Tekhnologiia iOrganizatsiia Proizvodstva, no. 120, 1970, p. 10-24. rotor is th'e major cause of discrete frequency pressure fluctuation In Russian. and hence of discrete noise. The thesis includes the FORTRAN IV Refinement of the method proposed by Lukashov and Lysov computer program that was written for the analysis and requiies only (1969) for solving problems of locating the critical curvature radius the basic geometry of the blades plus upstream and downstream flow in waffle panels while the latter are shaped into aircraft components. velocities as input. F.R.L. The improved method provides more accurate approximations and includes the following assumptions: (1) the panel material is isotropic in both the elastic and plastic regions, behaves uniformly under tension and compression, and is incompressible beyond the A71-28884 En route speed control techniques. A. J. hit of elasticity; (2) cross-sections during bending remain flat; Kulikowski. Journal of Air Traffic Control, vol. 14, May 1971, p. (3) the directions of the adopted coordinate axes coincide with the 5-8. directions of the main stress and strain axes; (4) the linear Analysis of the speed range used in a typical flight profile of a dimensions of the component right up to buckling remain invariant; turbojet in an effort to assess its impact on ATC procedures. It is and (5) strain concentrations in the vicinity of stiffener intersections suggested that a uniform range of airspeeds be used by all turbojets are neglected. M.V.E. transitioning to and from en route altitude< via published directives. These indicated airspeeds should be mandatory unless otherwise authorized by the controller. F.R.L. A71-28941 # Research study of optimal treatment routines applicable to an automated orifice-making process (Issledovanie A71-28885 A world wide synopsis of turbulence related izyskaniia optimal'nykh rezhimov obrabotki primenitel'no k avto- accidents. David D. Thomas (Flight Safety Foundation, Inc.. matizirovannomuprotsessu obrazovaniia otverstii). A. P. Nazarychev. Arlington, Va.). (Federal Aviation Administration, Turbulwce Kazanskii Aviatsionnyi lnstitut, Seriia Aviatsionnaia Tekhnologiia i Symposium, Washington, D.C., Mar. 22, 1971.) Journal of Air Organizatsiia Proizvodstva, no. 120, 1970, p. 25-29. In Russian. Traffic Control, vol. 14, May 1971, p. 16-21. Investigations were performed of the parameters decisive in the Review of turbulence-related accidents during the past few years optimization of orifice-drilling techniques aimed at obtaining the in order to provide perspective on the frequency and severity of such highest qualitative and quantitative machining performance in the accidents. It appears that turbulence accidents are rarely fatal in air use of drilling equipment operated with the aid of programmed carrier operations, but 50% of those occurring in general aviation is numerical control systems and engaged in the production of fatal. F.R.L. long-shaped aircraft components out of elongate profiles and panels. Proper timing of cutting tool resting periods, during which effective heat rejection out of the drilling bit and processed component into A71-28886 3-D radar is here. Albert R. Fellin. Journal of Air Traffic Control, vol. 14, May 1971, p. 24, 25. the surrounding medium can take place, and adequate allqwance for the total drilling depth are found to be the major optimization Discussion of 'beacon numerics,' presently employed in the Atlanta and Indianapolis centers on a common-usage radar site, as a prerequisites. M.V.E. means of using a radarscope net not only for target azimuth and distance but also for direct altitude readout. This equipment gives a # Problem of gear link design for grindingbelt numerical readout from any aircraft with the proper equipment. A71-28943 machines (K voprosu proektirovaniia kulisnykh mekhanizmov Simplicity of operation is its greatest asset. F.R.L. lentochno~hlifoval'nykh stankov). V. G. Borisovich, F. S. Iunusov, A. U. Gubaidullin. and K. G. laushev. Kazanskii Aviatsionnyi A71-28910 Interface circuits drive high-level switches lnstitut, Seriia A viatsionnaia Tekhnologiia i Organizatsiia from low-level inputs. J. 0. M. Jenkins (Siliconix, Ltd., Swansea, Proizvodstva, no. 120, 1970, p. 52-59. In Russian. Wales). Electronic Engineering, vol. 43, May 1971, p. 45-49. Surface finish requirements of helicopter components are briefly A universal need exists at present for switching-systems which reviewed, and some design aspects of thereto applied grinding can provide the interfacing required to drive 'high' voltage level equipment are discussed. These components have external surfaces,of transistor switches from 'low' level (0.5V) logic inputs. Furthermore, complex three-dimensional curvature, are heavily loaded, and per- the degree of compactness and reliability needed in these systems can form critical key functions. Their service circumstances put forth only be achieved with the use of i.cs. This is particularly so in stringent demands upon the machining characteristics of their avionics systems where switching is required at a 28 V d.c. level. surfaces in terms of fine-finished smoothness and of the sign and (Author) magnitude of residual stresses. At present, these demands are met mostly through use of grinding-belt machines. The required uni- A71-28938 # Selection of a cam profile for the computing formity and continuity in abrasive belt contact pressure during resolving unit of an altimeter (Vybor profilia kulachka schetno- grinding are ensured by link gear mechanisms whose belt-applying reshaiushchego uzla vysotomera). L. I. Simakov and A. F. Akhmerov. elastic contact rollers are actuated by special hydraulic follow-up Kazanskii Aviatsionnyi Insritut, Trudy, Seriia Aviatsionnye Pribory i systems. The operation of these gear link mechanisms is described Avtomaty, no. 121, 1970, P. 9299. In Russian. and some of their design parameters are analyzed. M.V.E.
41 3 A71 -28944
A71-28944 # Evafuation of the mechanical properties of A71-28968 # Comparative estimation of start-up and break- alloys and components in aircraft engine production (K otsenke down characteristics of gas-turbine engine combustion chambers with mekhanicheskikh svoistv splavov i detalei v proizvodstve mechanical and air-stream mechanical propellant atomization aviadvigatelei). E. N. Darchinov. Kazanskii Aviatsionnyi Institut, (Sravnitel'naia otsenka puskovykh i sryvnykh kharakteristik kamery Seriia Aviatsionnaia Tekhnologiia i Organizatsiia Proizvodstva, no. sgoraniia GTD pri mekhanicheskom i vozdushno-mekhanicheskom 120, 1970, p. 60-65.6 refs. In Russian. raspylivanii topliva). I. N. Diatlov. In: Combustion in a flow (Gorenie Discussion of approaches intended to raise the reliability of v potoke). Edited by A. V. Talantov. Kazan. design and production decisions based on evaluations of mechanical Kazanskii Aviationnyi lnstitut (KAI, Trudy, Seriia Aviatsionnye characteristics in products of mass processes. It is shown that this Dvigateli, no. 124), 1970, p. 160.169. In Russian. reliability can be improved through application of quantitative Theoretical and experimental study of the effectiveness of variables expressing the statistical differences among observed distri- propellant atomization with and without air injection in the butions and norms. M.V.E. combustion chamber nozzle of a gas-turbine engine. Tests show that the start-up and burning performance of these combustion chambers can be improved by using air injection during the mechanical propellant atomization process. It is shown that the operational A71-28945 # Determination problem of sound limit ex- range of combustion chambers can be extended to poorer propellant penditures per parameter unit in civil transport aircraft design (K mixtures by combined air-injection mechanical atomization of the voprosu opredeleniia predel'nykh tselesoobraznykh zatrat na edinitsu propellant. V.Z. parametra pri proektirovanii grazhdanskikh transportnykh samoletov). M. K. Nasyrov. Kazanskii Aviatsionnyi Institut, Seriia Aviatsionnaia Tekhnologiia i Organizatsiia Proizvodstva, no. 1 20. A71-28969 # Investigation of a gas turbine engine start-up 1970,p. 70-74.In Russian. igniter (Issledovanie puskovogo voplamenitelia GTD). I. N. Diatlov. Formulas for calculating cost-efficient limit expenditures in new In: Combustion in a flow (Gorcnie v potoke). commercial aircraft designs are derived and discussed. The attempt is Edited by A. V. Talantov. Kazan, Kazanskii Aviatsionnyi lnstitut made to include, among other things, the effects of the functional (KAI, Trudy, Seriia Aviatsionnye Dvigateli, no. 124). 1970, p. interdependence of amortization amounts and those of additional 170-177.In Russian. capital investments. It is felt that the actual operation of the An experimental gas turbine engine igniter with a modified commercial-exploitation process is thereby more accurately reflected propellant atomizer was designed in an attempt to improve the in the derived formulas. M.V.E. standard prototype with a mechanical propellant atomizer. The modified atomizer differed from the standard atomizer in that propellant atomization in it was enhanced by air injection. Tests showed that the combined propellant atomization technique A71-28954 Combustion in a flow (Gorenie v potoke). improved substantially the igniter performance, expanding con- Edited by A. V. Talantov. Kazan, Kazanskii Aviatsionnyi lnstitut siderably the range of steady operation in terms of propellant flow (KAI, Trudy, Seriia Aviatsionnye Dvigateli, no. 124). i970. 204 p. In rates and Dressure. V.Z. Russian. Experimental and theoretical research on combustiun processes A71-28970 # Effect of airstream-mechanical propellant in turbulent and laminar flows of kerosene and gasoline mixtures, atomization on the carbon deposition rates in a gas-turbine engine with emphasis on problems encountered in gas turbine engines. combustion chamber (Vliianie vozdushno-mekhanicheskogo Topics treated include measurement of flame propagation rates, raspylivaniia topliva na intensivnost' nagaroobrazovaniia v kamere effects of flow turbulence on flameout phenomena, effects of flame sgoraniia GTD). 1. N. Diatlov and V. G. Semenov. In: Combustion in holder and stabilizer arrangements on combustion parameters, a flow (Gorenie v potoke). Edited by A. V. influence of initial combustion parameters on afterburning charac- Talantov. Kazan. Kazanskii Aviatsionnyi lnstitut (KAI, Trudy, Seriia teristics, formation of temperature fields in the exhaust ducts of gas Aviatsionnye Dvigateli, no. 124). 1970, p. 178-185. 6 refs. In turbine engines, gasdynamic stabilization of flames, use of boundary Russian. slipstreams for ignition of combustion products in afterburners, and Experiments are described in which carbon deposition rates in a minimization of combustion deposits by appropriate design of fuel combustion chamber with airstream propellant atomization were injection systems. Numerous design procedures for gas-turbine compared with those in a combustion chamber with mechanical comhustion chambers are described. propellant atomization. Conditions are found to minimize carbon T.M. deposition by improving the air-propellant mixing process. Air- propellant flows are indicated which produce almost no carbon deposits when airstream-mechanical propellant atomization is used. A71-28962 # Role of turbulence intensity during the mixing V.Z. of plane isothermal slipstreams in an enclosed flow (Rol' inten- sivnosti turbulentnosti v protsesse smesheniia sputnykh ploskikh A71-28971 # Effect of the penetrating ability of jets on the izotermicheskikh strui v zakrytom potoke). lu. V. Vinogradov, V. N. peripheral nonuniformity of a gas temperature field at the outlet of a Gruzdev, and A. V. Talantov. In: Combustion in a flow (Gorenie v gas turbine engine chamber (Vliianie probivnoi spasobnosti strui na potoke) . Edited by A. V. Talantov. Kazan, okruzhnuiu neravnomernost' temperaturnogo polia gaza na vykhode Kazanskii Aviatsionnyi lnstitut (KAI, Trudy, Seriia Aviatsionnye iz kamery sgoraniia GTD). lu. A. Spiridonov, K. V. Kakhovskii, and Dvigateli, no, 124). 1970, p. 86-97.5 refs. In Russian. A. V. Talantov. In: Combustion in a flow (Govenie v potoke). Experimental study of turbulence effects on the mixing of three Edited by A. V. Talantov. Kazan, Kazanskii plane parallel streams with equal velocities (30 to 70 m/sec) and Aviatsionnyi lnstitut (KAI, Trudy, Seriia Aviatsionnye Dvigateli, no. temperature (313 to 323 K). The level of turbulence was varied by 124). 1970. p. 186-192.In Russian. udng different grids in the channels prior to entry into a transparent Experimental study of the behavior of a gas flow temperature mixing chamber. The central flow contained smoke for photographic field at the outlet of a combustion chamber with flame tubes having visualization of the mixing process in the transparent chamber. The circular cross sections. It is shown that there is an optimum in the results show that a simultaneous increase of turbulence in all three dependence of the peripheral nonuniformity of the temperature field channels intensifies the mixing process in accordance with turbulent on the penetrating ability of air jets when air is injected into the gas diffusion theory. The effects of increasing turbulence only in the flow through orifices in the flame tube walls. The Point of optimum central channel depend on the turbulence ratio between this channel is shown to be a singular point at which the gas flow field undergoes and the outer channels. T.M . a major structural change. V.Z.
41 4 A71 -29169
A71-28972 # Generalized characteristic of peripheral non- Association, 1970, p. 63-70; Discussion, p. 71-81. uniformity in the temperature field of a gas at the outlet of a Interpretation of results obtained in testing the Do 31 jet gas-turbine engine combustion chamber (Obobshchennaia kharak- transport built to land and take off vertically. When full throttle is teristika okruzhnoi neravnomernosti temperaturnogo polia gaza na applied the aircraft lifts from the ground with zero roll and vykhode iz kamery sgoraniia GTD). Iu. A. Spiridonov and A. V. accelerates quickly. The takeoff profile is optional with the pilot or Talantov. In: Combustion in a flow (Gorenie v potoke). is as directed by traffic procedures. The landing approach is the same Edited by A. V. Talantov. Kazan, Kazanskii Aviatsion- as that for any conventional jet aircraft with the exception of the lift nyi lnstitut (KAI, Trudy, Seriia Aviatsionnye Dv@ate/i, no. 124). engine start procedure. It is considered that there can be increased 1970, p. 193-200. In Russian. automation of air traffic control and the actual control of the A procedure is given for obtaining this characteristic on the aircraft by electronic systems during takeoff and landing. F.R.L. assumption that the airstream penetrating ability at the singular point does not depend on the jet momenta, that the air distribution in the ring channel is uniform, and that the orifice diameters in A7129132 # Flight systems, flight deck display and individual sections of the mixing zone are equal. Limiting conditions automatic flight control. R. W. Howard (Elliott Flight Automation, for the delivery of air jets into the mixing zone, for the hydraulic Ltd., Rochester, Kent, England). In: V/STOL in civil aviation; British resistance factor and for the gas motion from the flame tube into the Air Line Pilots Association, Annual Technical Symposium, 11th, ring channel are discussed. It is shown that for each total orifice area London, England, November 24-26, 1970, Proceedings. Hayes, there is an optimal air distribution in the mixing zone with a Middx., England, British Air Line Pilots Association, 1970, p. minimum peripheral nonuniformity of the flow temperature field. 123-137;Discussion, p. 138-141. V.Z. Discussion of the application of existing controls, instruments, and displays to the takeoff and landing operation of a V/STOL. The flying control system is considered to be essentially a problem of A71-28985 # The effect of flow direction on combined convective heat transfer from cylinders to air. P. H. Oosthuizen and applications engineering rather than one requiring some new S. Madan (Queen's University, Kingston, Ontario, Canada). ASME, breakthrough in systems or hardware technology. Electronic displays Transactions, Series C - Journal of Heat Transfer, vol . 93, May 197 1, have the ability to presevt data in any form or combination on any p. 240-242. National Research Council of Canada Grant No. A-5573. suitable display surface. F.R.L. In combined forced and free convective heat transfer from cylinders, the Nusselt number is shown to depend on the Reynolds number, the Grashof number, the Prandtl number, and the angle A71-29144 # Helicopters as cranes, and ,carrying external alpha between the directions of the forced flow and the buoyancy loads. Ill (Kran- und Aussedastflug mit Hubschraubern. Ill).Michael force. Previous measurements of convective heat transfer for alpha = Csspari. Technisch-okonomische Informationen der zivilen Luftfahrt, 0 deg were extended to investigate the effect of varying alpha, vol. 7, no. 4, 1971, p. 192-196. In German. Operational costs of helicopters and the economic value of their assuming alpha = 0, 90, 135, and 180 deg. O.H. use are analyzed. The operational costs consist of direct and indirect operating expenses and overhead expenses. It is found that the A71-29043 # Principal characteristics of aircraft flight me- employment of helicopters becomes more economical with in- creasing time of operation. Examples are presented of cases in which chanics (Osnovnye osobennosti dinamiki poleta samoleta). \' S. the employment of helicopters has great advantages when compared Pyshnov. Aviatsiia i Kosmonavtika, Apr. 1971, p. 13-15. In Russian. with the use of conventional equipment for load-lifting and The changes in the flight parameter as a function of the angle of transportation. Approaches for increasing the application possibilities roll and the angle pitch are discussed, and the dependence of the 07 of helicopters by decreasing operation costs are examined. G.R. angle of attack on the path inclination at a constant angle of pitch is illustrated. Indirect criteria from which a pilot can detect the banking of the aircraft in the absence of a visual or artificial horizon A71-29155 # Measurement of light pressure forces and of are outlined. V.P. aerodynamic forces acting on a body of complex shape in a free-molecule flow (Izmerenie si1 svetovogo davleniia i aerodinami- cheskikh sil, deistvuiushchikh na telo slozhnoi formy v svobodno- A71 -29106 Low stratus at Embakasi Airport Nairobi. molekuliarnom potoke). L. A. Vasil'ev, T. A. Kuramshin, L. P. Dietrich Stranz. Pure and Applied Geophysics, vol. 86, no. 3, 1971, Nazarova, and L. I. Travnikova. Aerodinamika Raarezhennykh p. 1 18-139. 26 refs. Gazov, no. 5, 1970, p. 113-118. In Russian. The relatively frequent occurrence of low clouds over the Description of an assembly designed to produce a distribution of Embakasi Airport near Nairobi (Kenya) is a great hazard particularly light reflected from a body which is similar to the distribution of to aircraft without an automatic landing device. Hence, the necessity molecules reflected from this body in a free-molecule flow. The for the flight direction and control staff to receive early and reliable assembly consists of a frame rotating about its vertical axis and of a information regarding low clouds from the meteorologist. The great ring fixed to the frame and rotating about its horizontal axis, both difficulty is evident from the fact that low stratus can form and also axes intersecting at the center of the ring. A body of complex disappear very suddenly. Considerable and sudden local and temporal geometry is suspended at the intersection of the axes on thin steel variations prevent the meteorologist from exactly forecasting the filaments. A light beam is emitted onto the body from a collimator phenomenon. The statistical results obtained from more than five fixed to the ring, so that the relative positions of the body and the years of observations should provide a means of tackling the beam remain unchanged during the rotation of the frame and the problem, but they appear to be inadequate unless the actual state of ring. Radiation reflected from the body in any direction can be the atmosphere in its lowest meters near the airfield is taken into 200 measured by photoelectric, bolometric, and photographic recording account as an additional aid for the forecast. It is pointed out that on this assembly. The theory of this technique is discussed. V.Z. radiosounding from a site to the northeast and below the level of the airfield would be of more use than that from Dagoretti which lies A71-29169 Similarity laws for three-dimensional steady downstream and at a greater altitude. M.M. # separated liquid and gas flows past bodies (Zakony podobiia dlia trekhmernogo statsionarnogo otryvnogo obtekaniia tel zhidkost'iu i A71-29131 # Commercial VSTQL and the jet VTOL trans- gazom). A. A. Nikol'skii. TsAGI, Uchenye Zapiski, vol. 1, no. 1, port. Drury Wood (Dornier AG, Friedrichshafen, West Germany). In: 1970, p. 1-7. 6 refs. In Russian. V/STOL in civil aviation; British Air Line Pilots Association, Annual Theoretical study of the behavior of ideal fluid flows past Technical Symposium, 1 lth, London, England, November 24-26, low-aspect-ratiobodies with flow separation. Conditions are obtained 1970, Proceedings. Hayes, Middx., England, British Air Line Pilots under which the plane cross section law is asymptotically applicable
41 5 A71-29172 to these flows. The conditions are used to reduce the three- is constructed from the lines of flow at the isolated minimum-diag dimensional problem to a two-dimensional problem of such flows wing. The third approximation takes an additional deformation of past two-dimensional bodies. General and specific similarity laws are the fuselage surface into account. V.P. derived for the reduction process. A low-aspect-ratiowing in a flow consistent with the plane cross-section law is discussed specifically. V.Z. A71-29183 # Investigation of means of increasing the lift/ drag ratio of conical bodies (Issledovanie vozmozhnostei uvelicheniia A71-29172 # Similarity and variation of the aerodynamical aerodinamicheskogo kachestva konicheskikh tel). 8. L. Zhirnikov characteristics in the transition region at hypersonic flow velocities and K. P. Petrov. TsAGI, Uchenye Zapiski, vol. 1, no. 1, 1970, p. (0 podobii i izmenenii aerodinamicheskikh kharakteristik v pere- 140-144. In Russian. khodnoi oblasti pri giperzvukhovykh skorostiakh potoka). V. N. The aerodynamic characteristics of cones with a wedge-shaped Gusev, M. N. Kogan, and V. A. Perepukhov. TsAGI, Uchenye nose are studied experimentally and theorerically as a function of Zapiski, vol. 1, no. 1, 1970, p. 24-33. 37 refs. In Russian. their geometrical parameters. The experiments were performed fol Analysis of the aerodynamic characteristic? of simple bodies in angles of attack ranging from 0 to 18 deg at a Mach number of 1.6 hypersonic flows with structural characteristics ranging from those of and a Reynolds number of 0.88 x 10 to the sixth power. The a free-molecule flow to those of a solid medium. The Boltzmann theoretical results were obtained within the framework of Newtonian equation is used as a basis for deriving a similarity criterion for such theory. It is shown that for certain geometrical parameters, the media. The basic gas dynamical similarity parameter is shown to be a configurations studied have a much greater lift and lift!drag ratio Reynolds number whose viscosity factor is a function of the drag than circular cones. The configurations studied may be well suited temperature. This parameter is used .in a comparison of the for space vehicles reentering the atmosphere at speed above 7 theoretical and experimental results. V.Z. miles/sec. V.P.
A71-29175 # Flow in the inlet section of a supersonic A71-29185 # Approximate calculation of a certain class of diffuser channel when the boundary layer is separated by a shock gliding trajectories (0 priblizhennom raschete odnogo klassa wave (Techenie YO vkhodnom lichastke kanala sverkhzvukovogo traektorii planirovaniia). V. G. Koniaev. TsAGI, Uchenye Zapiski, diffuzora pri otryve pogranichnogo sloia golovnoi volnoi). A. V. vol. 1, no. 1, 1970, p. 149-157. In Russian. Nikolaev. TsAGI, Uchenye Zapiski, vol. 1, no. 1, 1970, p. 60-70. In Analysis of quasi-stationary gliding trajectories of an aircraft in a Russian. planetary atmosphere during constant control of attack and bank Theoretical study of a plane flow in an experimental air inlet angles. Values of parameters are determined at which these trajec- with extended rectilinear generatrices. The air inlet design is used for tories are possible. Approximate formulas are obtained for calculat- simulation of a shock-wave-separated flow in supersonic diffusers. A ing the longitudinal and lateral ranges of the gliding aircraft as a jet with a free boundary behind the flow separation point is used as a function of its characteristics. Z.W. flow prototype in the simulation experiments. Expressions are obtained for determining the pressure variation profile along the free boundary from data for a critical pressure gradienl t the flow A71-29188 # Theory for the unsteady curvilinear motion of separation point. V.Z. a lifting surface in a gas (K teorii nestatsionarnogo krivolineinogo dvizheniia nesushchei poverkhnosti v gaze). V. E. Baskin. TsAGI, UchenyeZapiski, vol. 1, no. 2, 1970, p. 18-28. 5 refs. In Russian. A71-29176 # Experimental study of heat transfer on spheres The velocities of gas flows induced by the unsteady curvilinear and sharp cone> in a rarefied hypersonic gas flow (Eksperimental'noe motion of a lifting surface are expressed in terms of vortex densities. issledovanie teploperedachi na sferakh i tonkikh konusakh v giper- These expressions generalize the Biot-Savart law in such a manner zvukovom potoke razrezhennogo gaza). Iu. V. Nikol'skii. G. E. that it becomes valid (in the linear approximation) for arbitrary Pervushin, and L. G. Chernikova. TsAGI, Uchenye Zapiski, vol. 1, nonstationary vortices in a gas. The generalization involves an no. 1. 1970, p. 71-77. 7 refs. In Russian. allowance for the delay (lasting on the order of the time required for Wind tunnel vacuum experiments with heat transfer measure- the passage of the sound signal) in velocity formation when applying ments on spheres and sharp cones in rarefied gas flows at zero angles the usual Biot-Savart formula to the vortex elements. This yields of attack at hypersonic speeds are described. Heat transfer is studied certain supplementary wavelike components of the induced veloc- on spheres at Mach numbers from 4.9 to 9.5 and Reynolds numbers ities. T.M. from 35 down to 1, and on cones at Reynolds numbers from 100 down to 4, realizing the conditions of transition from a free- molecular flow to a continuous medium flow. Good agreement is A71-29189 # Hypersonic flow around a delta wing (Obteka- obtained between the experimental results and theoretical results nie treugol'nogo kryla giperzvukovym potokom). V. P. Kolgan. obtained by Nikolaev (1962) for viscous hypersonic flows and by TsAGI, Uchenyezapiski, vol. 1, no. 2, 1970, p. 29-35. In Russian. V.Z. Perepukhov (1967) for nearly free-molecular flows. Hypersonic flow around a delta wing at small angles of attack is examined by using the method of pressure sources. The problem is reduced to a singular integral equation which is regularized to yield a A71-29182 # Minimum-drag wing-fuselage combination for Fredholm integral equation of the second kind with a continuous kernel. The results are illustrated by .example calculations of the supersonic speeds (Kombinatsiia kryla z fiuzeliazhem, obla- daiushchaia minimal'nym soprotivleniem pri sverkhzvukovykh pressure field for a disturbed flow region. T.M. skorostiakh). Iu. L. Zhilin. TsAGI, Uchenye Zapiski, vol. 1, no. 1, 1970, p. 134-139. 5 refs. In Russian. The variational problem of determining a minimum-drag wing- A71-29190 # Investigation of the aerodynamic character- fuselage combination for prescribed lifting force, longitudinal istics of elevons on low-aspect wings (Issledovanie aerodinami- moment, and volume is examined. It is assumed that the wing cheskikh kharakteristik elevonov na kryl'iakh malogo udlineniia). V. thickness is zero at the supersonic leading and trailing edges. For a G. Mikeladze. TsAGI, UchenyeZapiski, vol. 1, no. 2, 1970, p. 36-45. slender fuselage, the variational problem is solved by the method of In Russian. successive approximations.' In the first two approximations, the Calculations of the subsonic and supersonic aerodynamic charac- problem is reduced to certain variational pi-oblems for an isolated teristics of elevons used as longitudinal and lateral control elements wing. The surface of the fuselage in the contact region with the wing on low-aspect wings. The method used for the subsonic velocities is
41 6 A71-29224 based on a rf.ciprocitv theorem that establishes the relation between obteKanie konusa, dvizhushchegosia PO stepennomu zakonu). S. K. the wing's azrodynamic characteristics in forward flow and in reverse Betiaev. TsAGI, Uchenye Zapiski, vol. 1. no. 3, 1970, p. 15-29. 8 flow (whet2 the direction of the oncoming flow's velocity is refs. In Russian. reversed). Calculations for supersonic velocities are based on the The unsteady hypersonic asymmetric gas flow past a circular linear theory of supersonic flows. The effects of individual elevon cone and wedge moving at a variable velocity is analyzed for the case parameters are explained systematically, and flow patterns are where the piston analogy of Heus is not applicable. An elliptical zone described fot wings with highly deflected elevons at subsonic, with an isotropic expansion of weak disturbances and an entropy transonic, and supersonic velocities. T.M. singularity is contained between the hypersonic regions of the flow. A solution to the problem is obtained with the aid of external and internal asymptotic expansions. Numerical results are obtained by the method of characteristics within the framework of small A71-29191 # Influence of the real properties of air on flow perturbation hypersonic theory. The theory of self-similar motion parameters around an elliptical cone - Aerodynamic characteristics of proposed can be used for calculating the wave drag coefficient as a elliptical cones at large angles of attack (Vliianie real'nykh svoistv function of time for a cone of finite dimensions. It is shown that for vozdukha na parametry techeniia okolo ellipticheskogo konusa . a cone accelerated according to a power law, the drag coefficient Aerodinamicheskie kharakteristiki ellipticheskikh konusov pri cannot increase more than twice. V.P. bol'shikh uglakh ataki). A. P. Bazzhin, 0. N. Trusova, and I. F. Chelysheva. TsAGI, Uchenye Zapiski, vol. 1, no. 2, 1970, p. 46-52, In Russian. A71-29207 # Interference between a wing and a jet in cross Calculations of flow around an elliptical cone having a cross- wind (Interferentsiia kryla i strui v snosiashchem potoke). V. N. sectional major-to-minor axis ratio of 2 and a vertex angle of 30 deg Arnol'dov, M. G. Gordon, and A. A. Savinov. TsAGI, Uchenye in the horizontal plane. The cone was oriented at a 30-deg angle of Zapiski, vol. 1, no. 3, 1970, p. 36-44. 7 refs. In Russian. attack in air flows with speeds of 2350, 3356, and 6713 mlsec. The The influence of a jet expelled at an angle of 90 deg toward the air was treated as a three-component (nitrogen, oxygen, and lower wing surface on the aerodynamic characteristics of isolated nitrogen) gas, and its thermodynamic functions were calculated by a wings close to and far from a wall is studied experimentally. The standard program. The results are graphically compared with those factors responsible for the changes in the effective thrust of the jet for a perfect gas, showing relatively small changes in shock-wave with an increase of the oncoming flow rate and a decrease of the positions, pressure ratios, and density ratios when the real gas distance from the wall is analyzed on the basis of experimental and properties are taken into account. The second part of the study theoretical data on the interaction between jets with initial cross shows the calculated behavior of lift, .drag, and pitch-moment sections of various shape and wings of various relative dimensions coefficients in perfect gas as functions of vertex angles (20, 30, and and planforms. It is shown that at large distances from the wall 40 deg) and angles of attack (30 to 50 deg) at Mach 7. T.M. (ground), the external flow past the jet plays an important role in the changes of the aerodynamic characteristics of the wing when the oncoming flow rate is increased, while near the ground, the vortices A71-29201 # Ballistic wind tunnel for drag measurements created at the upper wing surface have a favorable influence of the on models during free flight at supersonic speeds (Aeroballisti- interference between the wing and jet. V.P. cheskaia truba dlia izrnereniia soprotivleniia modelei v svobodnom poke pri giperzvukovykh skorostiakh). L. P. Gur'iashkin, k. P. A71-29217 # Phenomenon of vortex formation associated Krasil'shchikov. and V. Podobin. TsAGI, Uchenye Zapiski, vol. 1, P. with the oblique flow past a rotor (0iavlenii vikhreobrazovanii pri no. 2, 1970, p. 111-114. 6 refs. In Russian. obtekanii nesushchego vinta kosym potokom). A. V. Larin. TsAGI, A brief description is presented of a wind tunnel, the underlying UchenyeZapiski, vol. 1, no. 3, 1970, p. 115.122. 9 refs. In Russian. principle of operation of which is firing modei bodies into an The structure and shape of the vortex wake behind a multiblade oncoming supersonic flow. The wind tunnel was designed for hinged rotor in oblique flow is studied by the cavitation method for measurements of the drag coefficient and for studies of the various flight loads and various flow conditions at the rotor. The characteristics of flow past axisymmetric bodies in the range of results are analyzed and are illustrated by photographs and sketches. supersonic and hypersonic flight velocities. O.H. A new effect is observed which consists in the transformation of the outer cycloidal segments of trailing vortices into vortex filaments consisting of several helical loops. V.P. A71-29204 # Limiting flows of a viscous fluid with station- ary separation zones at Reynolds numbers tending to infinity (0 predel'nykh techeniiakh viazkai zhidkosti so statsionarnymi A71-29222 # Optimal distribution of wing thickness in sryvnymi zonami pri Re tending to infinity). G. I. Taganov. TsAGI, supersonic flow (Optimal'noe raspredelenie tolshchiny kryla v UchenyeZapiski, vol. 1, no. 3, 1970, p. 1-14. 14 refs. In Russian. sverkhzvukovom potoke). I. I. Burakov and Iu. L. Zhilin. TsAGI, Quantitative asymptotic results for nondegenerate flow within a Uchenyezapiski, vol. 1, no. 4, 1970, p. 15-21. 5refs. In Russian. separation region with a circulating core are obtained for Reynolds Determination of the surface shape of a wing having minimum numbers tending to infinity. The global flow pattern at a two- wave drag at zero'angle of attack in supersonic flow. The Mach dimensional body with an indefinitely increasing separation zone is number and the wing's planform are given, and the wing thickness analyzed, and the local flow pattern near the body studied in detail. becomes zero at the leading and trailing edges. For high Mach Analysis of the local flow pattern leads to an asymptotic formula for numbers, the problem has a simple solution since the drag does not the drag coefficient of a two-dimensional body in the presence of depend on the planform, and for a given profile, is governed by the dissipation at Reynolds numbers tending to infinity. A qualitative distribution of the relative thickness and local chord along the span. analysis of the drag coefficient as a function of Re for a plate A parabolic-profile wing whose thickness varies in proportion to the situated normal to a flow with a stationary separation zone leads to a local chord along the span exhibits minimum drag in this case. paradoxical result, according to which the drag of plate normal to Solutions for lower Mach numbers are obtained by using the Ritz the flow becomes at a certain Reynolds number smaller than that of method which reduces the problem to the determination of a plate at zero incidence at the same Reynolds number. The conditional minimum. T.M. configuration of the separation zone which corresponds to the limiting state of a flow at Reynolds numbers tending to infinity past a symmetrical two-dimensionalbody is determined. V.P. A71-29224 # Wind-tunnel simulations of viscous hypersonic flows (0 modelirovanii viazkikh giperzvukovykh techenii v aero- A71-29205 # Hypersonic self-similar flow past a cone dinamicheskikh trubakh). V. S. Galkin and V. S. Nikolaev. TsAGI, moving according to a power law (Giperzvukovoe avtomodel'noe UchenyeZapiski, vol. 1, no. 4, 1970, p. 26-33. 8 refs. In Russian.
41 7 All-29228
Analysis of problems involved in direct wind-tunnel simulation similar to that at an angle of 5 deg. The tip vortex closer to the lower of natural interactions between a hypersonic viscous flow and a surface of the wing intensifies in the transition from zero angle of laminar boundary layer on a plate positioned at zero angle of attack. attack to an angle of attack of 5 deg, while the tip vortex located Direct simulation implies the possibility of relating the experimental closer to the upper wing surface hardly changes. It is shown that the data directly to the natural conditions. This can be done when all the flow at zero angle of attack has an influence of lift formation. V.P. wind-tunnel similarity criteria coincide with the natural criteria or when differences between them cause only slight discrepancies in the aerodynamic characteristics. Calculated data are given for the effects A7129235 # Investigation of the vortex system of a heli- of individual similarity parameters on the lift and drag coefficients, copter rotor (Issledovanie vikhrevoi ~istemy nesushchego vinta and practical recommendations are included for relating the results vertoleta). V. G. Kolkov. TsAGI, Uchenye Zapiski, vol. 1, no. 4, of wind-tunnel experiments to natural situations in cases where 1970, p. 113-117. In Russian. several similarity parameters diverge simultaneously. T.M. A smoke visualization technique is applied to a study of the vortex system of a rotor and the induced velocity field over a wide range of positive and negative angles of attack, flight conditions, and A7129228 # Longitudinal stability criteria for a ground- unit loads. Expressions describing the dependence of the configura- effect airplane (Kriterii prodol'noi ustoichivosti ekranoplana). R. D. tion of the vortex system on the velocity of the oncoming flow and Irodov. TsAGI, Uchenye Zapiski, vol. 1, no. 4, 1970, p. 63-72. In on the unit load at the rotor are proposed. Vortex system Russian. configurations are determined for various modes of rotor operation. Analysis of factors affecting the longitudinal stability of an The range of applicability of existing vortex models is established. airplane which relies on the ground effect for substantial enhance- V.P. ment of its lift properties and of the wing's aerodynamic quality. The advantageous influence of the ground effect increases with decreasing A7 1-29256 Elevator-inducedmanoeuvring loads from the height of the wing's trailing edge over the surface, as measured in standpoint of airworthiness requirements for sailplanes. Piero Morelli fractions of the chord. For a given wing surface area and a given (Torino, Universiti, Turin, Italy). (Organisation Scientifique et height of the trailing edge (governed by the roughness of the Technique Internationale du Vol 2 Voile, Congress, 12th, Alpine, surface), the influence of the ground effect increases with decreasing Tex., June 27-July 4, 1970.1 Aero-Revue, May 1971, p. 247, 248. wing aspect ratio. Some new longitudinal stability criteria associated Modifications of International Airworthiness Requirements for with these aerodynamic characteristics are defined and developed Sailplanes are proposed on the basis of criteria previously defined into supplementary aerodynamic design requirements. T.M. and discussed. The proposed modifications pertain to loads on horizontal tail surfaces and to maneuvering loads. Resclts of sample calculations of loads for typical sailplanes (a single- and a two-seater) A71-29229 # Irregular optimal trajectories of a spacecraft are presented in two tables. M.V.E. during flight in the atmosphere (Nereguliarnye optimal'nye traektorii apparata pri polete v atmodere). V. V. Dikusar and A. A. Shilov. TsAGI, Uchenye Zapiski, vol. 1, no. 4, 1970, p. 73-83. In Russian. A71-29257 Airfoils for the variable geometry concept. F. The control of a spacecraft's angle of attack during atmospheric X. Wortmann (Stuttgart, Universitat, Stuttgart, West Germany). reentry for minimum flight distances is examined with allowance for (Organisation Scientifique et Technique Internationale du Vol a load constraints in the case of local inefficiencies of control. This Voile, Congress, 12th. Alpine, Tex., June 27-July 4, 1970.1 Aero- case involves a situation where the local influence of the lifting force Revue, May 1971, p. 249-251. on the loads becomes exhausted. The necessary optimality con- Wind tunnel tests were run on a pair of geometrically com- ditions are analyzed, and Pontriagin's maximum principle is used for patible airfoils designed to, implement a veriable chord concept numerical determination of the spacecraft's maneuvering capabilities. applicable to sailplanes. The experimental results obtained confirm Attention is given to the methodological aspects of solving boundary the expectation based on theoretical calculations and suggest value problems when calculating irregular optimal trajectories. T.M. excellent performance probabilities for a variable-chord sailplane. M.V.E.
A71-29231 # Allowance for the operational experience in A7129261 # The operational proving of automatic flight the determination of the lifetime of a structure (Ob uchete opyta control systems in the approach and landing phase. R. H. Ashforth. ekspluatatsii pri opredelenii sroka sluzhby konstruktsii). V. D. Aviation Review, May 1971, p. 14-16. Il'ichev. TsAGI, Uchenye Zapiski, vol. 1, no. 4, 1970, p. 92-98. In For the Hawker Siddeley Trident aircraft the autopilot was Russian. conceived on the basis that automatic landings in blind conditions Calculation of the safe service life of currently used structures could be achieved with a safety margin one order improved from that and its prolongation without increasing the failure probability in of the human pilot when making landings. Clearance for fully blind storage, taking into consideration the linear accumulation of fatigue automatic landings is to be achieved in a series of gradual stages. The damages. To this purpose, the utilization of current load measure- Category 1 standard of certification is considered. For Category 2 it ments and laboratory fatigue testing is recommended, as well as the was necessary to design and develop a radio deviation and com- use of mileage statistics of aircraft in current operation, including the parator system. Lessons learned in developing the Category 38 leader aircraft. Z.W. system could result in an easier operation if they were implemented on future aircraft. G.R. A71-29234 # Influence of the vortex system of a wing in the absence of lift on the flow past the wing at small angles of attack (Vliianie vikhrevoi sistemy kryla pri otsutstvii pod'emnoi sily na ego A71-29262 # Accessories for gas turbine APU's. V. L. obtekanie pri malykh uglakh ataki). K. I<. Fediaevskii and N. N. Benson.Aviafion Review, May 1971, p. 18, 19. Fomina. TsAGI, UchenyeZapiski,vol. 1,no. 4, 1970, p. 109-112. In The growing importance of the gas turbine Auxiliary Power Unit Russian. (APU) for aircraft and their electronic systems is considered. The flow characteristics at zero angle of attack and an angle of Accessories of the APUs consist of high energy igniters, cables and attack of 5 deg were studied for a small-aspect-ratio thick-section connectors, thermocouples, and equipment for speed and tempera wing (NACA-0018) of rectangular planform with flat tips. A ture monitoring. The accuracy and reliability of speed and tempera- comparison of the transverse velocity fields at these angles of attack ture monitoring equipment is an important factor in the control of shcws that the nature of the flow at zero angle of attack is very an APU. G.R.
41 8 A71 -29312
A71-29265 # Aerodynamic behaviour of bodies in the wakes method called Noise Exposure Forecast (NEF) for the delineation of of other bodies. W. A. Mair and D. J. Maul1 (Cambridge University, noise affected areas is described in detail. Finally, the 'cost' of noise Cambridge, England). Royal Society (London), Philosophical Trans- is discussed. O.H. actions,SeriesA, vol. 269, May 13, 1971, p. 425-437. 21 refs. Wakes of two-dimensional bluff bodies are described, with emphasis on the properties of the wake which influence the loads on A71-29308 # Propulsion guidance and stability of the other bodies placed in the wake. The unsteady irrotational flow ground effect vehicle with perimetric Coanda fluid boundary (Asupra outside the true wake is included in the discussion. Some limited propulsiei, dirijirii si stabilititii vehiculului cu efect de sol GU information on the wakes of three-dimensional bluff bodies is also frontieri fluidi Coandi perimetrali). Clement Alecsandriescu. Trans- given. The interaction- between two bodies is subdivided into two porturiAuto, Navale SiAeriene, vol. 1 (18), Feb. 1971, p. 66-70. 6 categories: (1) when the bodies are close together and the upstream refs. ,In Rumanian. body is influenced by the downstream one and (2) when the bodies Two variants of the propulsion system are presented: (1) the are so far apart that only the downstream body is affected. shutter system which is only briefly described and (2) the system Experiments are described in which the load on an aerofoil in the using the Coanda effect to obtain a directlonal change of the flow. wake of a two-dimensional bluff body was measured. The results are Theoretical computations are given for the latter together with presented in the form of an aerodynamic admittance, and these details on the braking and stability of the vehicle during turns and at experiments are used to illustrate the type of problem associated upgrades. N.D. with the determination of the loads on a bluff body in a wake. Experiments are also described which show the large variation of time-averaged load which can be developed on a body which is part A71-29309 Roissy-en-France - New major airport for of a closely packed complex of bodies, as the orientation of the Paris. Gerhard Scheuch (Verein Deutscher Ingenieure, Darmstadt, complex to the wind is varied. (Author) West Germany).Airportforum, no. 1, 1971, p. 25-31, 33, 34, 36. In English and German. The new airport is under construction since 1967. It is situated A71-29276 The 'Mercure' - The first aircraft of a new approximately 20 km to the north-east of the Notre Dame cathedral. generation (Le 'Mercure' - Premier,avion d'une nouvelle gheration). In its final stage, the airport will be capable of handling 30 million Jean de Galard and Jacques Morisset. Air et Cosmos, vol. 9, May 15, passengers a year. Five separate terminals for six million passengers 1971, p. 21-36. In French. each will be built at a rate of one per year. The airport will have four Review of the development of the Dassault Mercure short-range runways: two to the north and two to the south. The maximum aircraft. An extensive study of world air traffic showed that the traffic volume which could be handled by this runway system would average distance traveled per passenger was less than 1000 km. be 500,000 aircraft movements a year. The present state of Studies by Dassault indicated that aircraft currently in use were construction is briefly described. Z.W. poorly suited to their purpose. Thus a twin-jet aircraft was conceived which is larger than the Caravelle, the BAC-111, and the Boeing 8-737 now actually in line use. It is considered to be well adapted to A71-29310 The new Melbourne/Tullamarine airport. short stages and capable of further development by use of new and James M. Eames (Department of Civil Aviation, Melbourne, more powerful engines. F.R.L. Australia). Airport forum, no. 1, 1971, p. 39, 40, 42 (5 ff.). In English and German. General description of the new airport, its facilities, and capacity. A three-story international and domestic passenger terminal A71-29281 Fuel-optimal landings of jet-supported VTOL with radiating passenger concourses was placed on a 200-acre site on aircraft (Treibstoffoptimale Landetransitionen strahlgestiitzter the eastern side of the airport, with its road system connected to an VTOL-Flugzeuge). G. Schmidt and A. Weimann (Dornier AG, Friedrichshafen, West Germany). lngenieur-Archiv, vol. 40, no. 2, express highway to the city. Five hundred acres to the south were 1971, p. 96-106. In German. reserved for airline maintenance bases and a future cargo handling area. The airport has two runways: a primary 8500 ft north-south The present paper considers an optimal control problem, namely fueCoptimal landings of a VTOL aircraft. The aircraft is approxi- runway to be extended to 12,000 ft, and a secondary east-west mated as a mass point. However, separate main and lift engines, main runway of 7500 ft, which is also capable of extension. The aerodynamic forces and jet inlet impulse are taken into account. The imternational departure lounge and its associated areas will be capable of handling up to about 4000 passengers over a peak hour. The equations of motion are given for the case of static air mass and a domestic terminals are planned to accommodate about 12,000 two dimensional translational motion in a vertical plane with pitch people an hour in the busiest period. Z.W. attitude constant. Utilizing this mathematical model and Pontriagin's Maximum Principle the analytical equations for computing combined fuel-timeoptimal landing transitions are derived. These equations were solved in an analog computer study assuming data of the VTOL A71-2931 1 Design principles for airport pavements. Carl jet transport DO 31. A survey and discussion of the results are given. E. Gerlach (Stuttgart, Universiet, Stuttgart, West Germany). Airport (Author) forum, no. 1, 1971, p. 53-60. In English and German. Analysis of the criteria for estimating the stresses exerted by different types of loads imposed during operation on an airport pavement. Load classification numbers are introduced which make it A71-29304 An over-view of the airport noise problem. possible to represent the stress imposed on the pavement by a lnder K. Sud (Stanford University, Stanford, Calif.). Logistics multiple-wheel landing gear in the form of an isolated single-wheel Review, vol. 6, no. 29, 1970, p. 12-31. 15 refs. load of equivalent value. Factors affecting the stresses arising in the The main sources of aircraft noise on and near airports and the pavement on flight operation areas, runways, taxiways, apron and factors affecting its intensity are specified. Legal aspects of airport waiting positions, overrun areas, shoulders and strips, and airport noise are examined. A detailed discussion is presented of some roads are discussed, and the suitable type of pavement is recom- approaches to alleviate noise and thus improve the relationship mended for each case. Z.W. between airport and its environs. These approaches include design changes of aircraft engines, nacelle, or airplanes themselves; opera- tion procedures such as special takeoff and landing approaches for noise abatement and use of preferential runways; and compatible A71 -29312 Baggage conveyor system in the New land use development around airports. The features of a method to Frankfurt terminal. Karlhans Muller (Flughafen Frankfurt am Main obtain noise characteristics of an aircraft are outlined, and the AG, Frankfurt am Main, West Germany). Airport Forum, no. 1,
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1971, p. 79-84. In English and German. seat is provided with a design which permits the airman to go The new terminal building at Frankfurt's Rhein-Main airport is through an opening much smaller thari possible with the conven- designed for a capacity of up to 30 million passengers a year, and the tional system. G.R. percentage of the transfer passengers is about 50%. An automatic luggage conveyor system to the aircraft positions is described. This system uses entirely new methods of luggage handling. Tray pallets which travel on a special wheel and belt track were used for each A71-29384 Special problems in helicopter handling quali- individual suitcase. The conveyor tracks have a total length of over ties as influenced by ASW requirements. J. R. Williford. Society of 18 miles with differences in level of up to 16 ft. Z.W. Experimental Test Pilots, Technical Review, vol. 10. no. 3, 197 1, p. 31-34, 39. Th. pilot is flying as much as 4 hours, sometimes more, on an antisubmarine warfare mission. On this mission he has to come to a A71 -29313 A new concept: UCAT - Ultra Compact hover at 40 feet, perhaps on complete instruments, as often as every Airport Terminal. Wendell E. Rossman. Airport Forum, no. 1, 1971, 10 minutes. In anything other than a sea state of 2 or 3 the approach p. 91-102. In English and German. to, stability therein, and recovery from a hover at 40 feet on The terminal described consists of a closed concourse ring as the complete instruments is a challenge which is not yet adequately met. link between externally parked aircraft and the internal ground Substantial gains in a number of areas are needed if the use of the approach. It constitutes an endless chain of segments, each consisting dipping sonar as prime sensor is to be continued. Needed improve- of the three elements: landside, link (terminal), and airside. Each ments related to the control and use of the helicopter are discussed. segment is autonomous and as such is a model of the whole. The G.R. circular form of the passenger terminal constitutes an optimum solution. Compared to traditional systems, its economics are much more favorable due to the lesser expense of facilities and smaller land requirements. Z.W. A71729385 Ejection seat system performance, versus air- craft performance. Ulf Frieberg (Saab-Scania AB, Linkoping, Sweden). Society of Experimental Test Pilots, Technical Review, vol. 10. no. 3, 1971, p. 35-39. Low Reynolds number turbulent flow in large A71-29378 # The trajectories of open ejection seats under various conditions aspect ratio rectangular ducts. G. S. Beavers, E. M. Sparrow, and J. from the lowest flying speed up to maximum speed are examined R. Lloyd (Minnesota, University, Minneapolis, Minn.). American and desired trajectories are shown in a graph. It is pointed out that it Society of Mechanical Engineers, Paper no. 71-FE-A, p. 1971. 4 9 must be possible to reach ejection seat handles without any delay. refs. Members, $1.00; nonmembers, 52.00. NSF Grant No. Handles mounted at the seat side are recommended. A harness for GK-13303. normal flying should allow the pilot to move freely forward and Experiments are reported on fully developed turbulent flows at laterally with the go-forward released while sitting on the survival low Reynolds numbers in rectangular ducts of large aspect ratio. Six pack. Leg fixation, head fixation and protection, parachute descent ducts, with aspect ratios between 15.5:l and 35.0:1, were employed and landings are discussed. G.R. for the investigation, covering a Reynolds number range from 5000 to 27,000. A friction factor, Reynolds number relation =xpressed as 0.507 R to the -0.30 power was found to be an excellent representation of the experimental data when the equivalent diam- A71-29387 The SST. A. W. Blackburn. Society of Ex- eter was used as the characteristic length dimension. The Blasius and perimental Test Pilots, Technical Review, vol. 10, no. 3, 1971, p. Prandtl circular tube friction factor relations, generalized by use of 70-75. the equivalent diameter, gave results within 5% or better of the Aspects of the worldwide leadership of the US. in providing air aforementioned correlation over the Reynolds number range of this transport are examined. Threats to US. dominance in the air investigation. (Author) transport field are seen to arise because of the absence of a U.S. SST in the face of the Anglo-FrenchConcord and the Soviet TU-144. The need for Federal funds in order to ensure that the necessary SST technology is in hand to maintain U.S. leadership in the world air A71-29382 'Third Chance' flight control system. Michael transport market is discussed. G.R. J. Burke (Grumman Aerospace Corp., Bethpage, N.Y.). Society of Experimental Test Pilots, Technical Review, vol. 10, no. 3, 1971, p. 3-9. The A-6 aircraft was equipped with a backup hydraulic system. The purpose of the system was to provide a means of egress from the A7129433 # On separation control of flow along curved combat zone following loss of both hydraulic systems due to battle wall by various forms of jets or suctions (Controlling characteristics damage. The system was to supply as a minimum, a control and comparison of effects). Masayosi Sat0 and Kenji Matsuoka capability to allow ejection in a safe zone with the possibility of a (Osaka Prefecture, University, Sakai, Japan). In: Japan National field landing capability. Flight tests were conducted utilizing the Committee for Theoretical and Applied Mechanics, National Con- Third Chance' system' only. Aspects of basic navigation are gress for Applied Mechanics, 18th. Tokyo Metropolitan University, discussed, and the results of an investigation of the landing capability Tokyo, Japan, November 8, 9, 1968, Proceedings. are reported. G.R. Tokyo, Chuo Kagaku-Sha, 1970, p. 155-163. Experimental investigation of the controlling characteristics of the separation position of the two-dimensional incompressible air A71-29383 Yankee escape system. Ralph Richardson. flow from the turbuleot boundary layer along a circular-cylindrical Society of Experimental Test Pilots, Technical Review, vol. 10, no. wall by various forms of jets or suctions. The results may be used to 3, 1971, p. 10'13. increase wing lift. It was found that there are stable, unstable, The new system uses a tractor rocKet which pulls rather than fluctuating, and uncontrollable zones, depending on the control pushes, and, thus, solves the problem of crew escape for the low condition. The optimum slit (or porous surface) position in which the control will be carried out most economically will not always speed, low altitude conditions in which conventional ejection seats encounter formidable stability problems. Escape at higher subsonic coincide with the original separation position of the external flow. speed is comparable to that afforded by the conventional but vastly For the large attachment angle of the external flow, control by a heavier ejection seat. It is possible to lift the airman out of any seat. tangential jet should be adopted; for the small attachment angle the To maximize ease of his escape through small apertures, however, a distributed normal suctions should be adopted. F.R.L.
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A71-29434 # Fatigue of aircraft structures. Fumio Shima A71-29467 # Skin friction drag and velocity profile mea- (Nihon Aeroplane Manufacturing Co., Ltd., Tokyo, Japan). In: Japan surement techniques in two-phase flow. M. P. Boyce (Texas A & M National Committee for Theoretical and Applied Mechanics, University, College Station, Tex.) and E. F. Blick (Oklahoma, National Congress for Applied Mechanics, 18th, Tokyo Metropolitan University, Norman, Okla.). American Society of Mechanical En- University, Tokyo, Japan, November 8, 9, 1968, Proceedings. gineers, Fluids Engineering Conference, Pittsburgh, Pa,, May 9-12, Tokyo, Chuo Kagaku-Sha, 1970, p. 167-176. 1977, Paper 71-FE-3.2. 11 p. Members, $1.00; nonmembers, $2.00. Investigation of several fatigue problems involved in aircraft Contract No. DA-31-124-ARO(D)-349. design. Safe-life and fail-safe concepts are explained with reference to Two-phase flow in a circular pipe and in a subsonic wind tunnel an example of a twin-engine transport fatigue test conducted in the is considered. The measurement of velocity profiles of particles phase of initial design. The procedures and results of determining the suspended in a gaseous media is a very significant factor in weak point are shown, as well as the outline of a fail-safe test calculating the drag and boundary layers encountered in such a flow. conducted to acquire data concerning fail-safe of the airframe, crack A detailed account of the flow visualization techniques is provided. propagation rate, and residual strength, etc. Some problems for The technique utilized was specially developed for gas-solid media. It future investigation are suggested. F.R.L. consists of two strobe lights with color filters connected to each other through a time delay relay system. Measurement techniques of skin friction drag on a flat plate in a wind tunnel, in a gas-solid A71-29448 * # On flow past a supercavitating cascade of environment are explained in detail. The photographic and measure- cambered blades. C. C. Hsu (Hydronautics, Inc., Laurel, Md.). ment techniques used in the investigation were perfected after a long American Society of Mechanical Engineers, Fluids Engineering trial-and-error period. G.R. Conference, Pittsburgh, Pa., May 9-12, 1971, Paper 71-FE-6. 6 p. 14 refs. Members, $1.00; nonmembers, $2.00. Contract No. NAS 8-20625. A71-29468 # Circumferential traversing technique for intra- A linearized theory of supercavitating flow past a straight stage analysis of axial flow compressors. M. Christianson (United cascade with arbitrary blade shapes is developed. From the analysis, Aircraft Research Laboratories, East Hartford, Conn.) and J. it is possible to determine the lift and drag coefficients, cavitation Yustinich (United Aircraft Corp.. Pratt and Whitney Aircraft Div., number, cavity shape, and exit flow conditions for any given specific East Hartford, Conn.). American Society of Mechanical Engineers, cascade geometry, blade shape, cavity. length, and initial inflow Fluids Engineering Conference, Pittsburgh, Pa., May 9- 12, 1971, conditions. The cavitating performance of the cascade is, in general, Paper 71-FE-33. 11 p. Members, $1.00; nonmembers, $2.00. found to depend strongly on stagger angle, solidity; blade shape, and The capability and application of the probe traversing instru- cavity length. G.R. mentation currently in use at the research laboratory of a U.S. aerospace company are considered, and the data reduction tech- niques which incorporate methods of mass-flow-averaging are pre- A71-29450 # Some results on the heat transfer within sented. Compressor facilities and the automatic data acquisition resonant cavities at subsonic and supersonic Mach numbers. R. A. system are discussed. Typical rotor and stator blade element White (Illinois, University, Urbana, Ill.). American Society of performance parameters calculated by the data reduction program Mechanical Engineers, Fluids Engineering Conference, Pittsburgh, are provided. Typical overall compressor performance, at constant Pa., May 9-12, 1971, Paper 71-FE-9. 6 p. 15 refs. Members, $1.00; speed, based on fixed instrumentation data and circumferential nonmembers, $2.00. Research supported by the Aeronautical Re- traverse data is presented in a graph. It is concluded that the search Institute of Sweden; NSF Grant No. GK-2053. technique reported allows the flow field to be analyzed in greater An experimental investigation of the heat transfer within two detail while reducing the data acquisition time. G.R. cavities (L/D equal to 1.25 and 2.0) exhibiting self-induced pressure oscillations (comnlonly referred to as resonance) is discussed. The tests were conducted with free stream Mach numbers between 0.35 A71-29469 * # High entrainment ejector design. K. E. and 1.5. The approaching boundary layer and shear layer over the Hickman, G. B. Gilbert (Dynatech Co., Cambridge, Mass.], and J. H. cavities were turbulent at all times. The pattern for the heat transfer Carey (American Standard Research Laboratories, Brunswick, N.J.). coefficient distribution over the cavity walls is in good agreement American Society of Mechanical Engineers, Fluids Engineering with that found by other investigators. The effect of the self-induced Conference, Pittsburgh, Pa., May 9-12, 1971. Paper 71-FE-34, 13 p. pressure oscillations, however, is to cause large changes in the level of 9 refs. Members, $1.00; nonmembers, $2.00. Contract No. NAS the heat transfer, with low values occurring at the distinctive peaks 2-4824. of the pressure oscillations. The ratio of the integrated heat transfer The use of ejectors is of increasing interest for bounaary layer within the cavity to the heat transfer from a flat plate with area control or control force augmentation in V/STOL aircraft. This equal to the area of ths cavity opening was found to vary from 1.10 paper presents a simplified analytical model which can be used to to 0.40, depending on Mach number and cavity resonance condi- estimate the performance of high-entrainment constant-areaejectors tions. (Author) for such applications. Analytical results are given for ejectors with primary flow pressure ratios above 5 and entrainment ratios from 10 to 40. An experimental program, employing primary flows up to 350 psia and 1200 F, was performed to confirm the analytical model. A7129453 # An experimental study of rectilinear jet-flap Test results are reported for a multiple-nozzle ejector with two cascades. T. J. Landsberg and E. Krasnoff (Ingersoll-RandResearch, mixing tube lengths. (Author) Inc., Princeton, N.J.). American Society of Mechanical Engineers, Fluids Engineering Conference, Pittsburgh, Pa., May 9- 12, 1971, Paper 71-FE-14. 8 p. 7 refs. Members, $1.00; nonmembers, $2.00. A71-29483 # Visual flight simulation with high information The performance of two-dimensional jet-flap cascades is deter- density image storage media (Flugsichtsimulation mit Bildspeichern mined experimentally. Stream deflection angles are presented as a hoher Inforrnationsdichte). Joachim Wernicke. Berlin, Technische function of the ratio of jet to mainstream momentum flux at chord Universitat, Fakultat fur Maschinenwesen, Dr.-lng. Dissertation, spacing ratios of 0.375 and 0.75. Results obtained with conventional 1969. 117 p. 72 refs. In German. jet-flap airfoils (normal blowing near trailing edge) are in good The functional principles and performance criteria of visual agreement with published theoretical results. Tangential blowing flight simulation devices are analyzed. The representation of terrain jet-flap airfoils (tangential blowing over a rounded trailing edge) are optical textures is considered to be a very important factor for shown to approximately double the turning effectiveness of the obtaining a realistic image; it creates, however, a major problem of cascade. (Author) storaging very considerable quantities of optical information. From
42 1 A71 -29524 the point of view of information storage capacity, only two storage Structural details, circuit diagrams, and operational specifica- principles for general use in the terrain flight simulation are found to tions of various aircraft electrical devices are given in a form intended be worth considering - Le., high-resolution photographic plates, and for use in maintenance and overhaul operations. Direct current digital memories. A method is described that uses current technology generators, alternators, starter generators, turbine-powered genera- to generate perspective views of a hilly terrain. The method is based tors, starter motors, and battery systems are examined, and proper on improvements of the television raster shape visual simulation maintenance intervals, diagnostic clues, lubrication materials, and principle. For information storage, a pair of photographic plates electrolyte requirements are described. Various types of cables, (brightness, elevation) is used. A study of digital methods for visual wires, insulations, electrical harness configurations, terminals, simulation of textured flight scenes reveals the negative result in that couplings, and connectors are outlined, and special attention is given both the storage capacity and computing cycles of electronic digital to mechanical and electrical countermeasures against electromagnetic computers will not be sufficient for this purpose in the near future. interference. T.M. O.H.
A71-29524 # Experimental aeromechanics (Eksperimen- A71-29548 # The role of aircraft in the intraurban trans- tal'naia aeromekhanika). S. M. Gorlin. Moscow, Izdatel'stvo Vysshaia portation system for the Detroit metropolitan area. L. A. Riedinger Shkola, 1970. 424 p. 19 refs. In Russian. and E. G. Stout (Lockheed-California Co., Burbank, Calif.). Explanation of the physical fundamentals, experimental American Institute of Aeronautics and Astronautics, International methods, and significance of the results of aerodynamic research. City Management Association, National League of Cities, and U.S. Various types of wind tunnels and shock tubes are described for tests Conference of Mayors, Urban Technology Conference, New York, of subsonic, supersonic, and hypersonic velocities. The physical N.Y., May 24-26, 1971, AlAA Paper 71-504.9 p. Members, $1.50; properties of liquids and gases are defined, together with laws nonmembers, $2.00. governing the behavior of gas flows and the use of similarity criteria. Study of aircraft capabilities in intraurban transportation system Procedures and equipment for measuring flow parameters arb in terms of selection and evaluation of aircraft concepts, using the outlined, including methods of introducing necessary corrections Detroit metropolitan area as a specific example and computer models into the experimental data. Emphasis is on test methods for adaptable to any intraurban or interurban area. Vehicle design, fleet determining the aerodynamic characteristics of aircraft, rockets, size, cost, terminal location, fares, and frequency are thoroughly various types of bluff bodies, surface transport vehicles, and considered and optimized on the basis of a realistic market scenario. ground-based structures. Flow in tubes, nozzles, and diffusers is also The propeller-powered deflected-slipstream STOL is the preferred studied. T.M. concept, the ;learest competitors being the compound helicopter VTOL and the autogyro STOL. All vehicle concepts considered are believed to involve low technical risk in their respective time periods. Current technology is sufficient for the development of the A71-29525 # Electrical power supply systems of airplanes intraurban transport system for the 1975 time period. M.V.E. and helicopters (Sistemy elektrosnabzheniia samoletov i vertoletov). I. 1. Lukin and V. V. Liubimov. Moscow, Izdatel'stvo Transport, 1970. 360 p. 12 refs. In Russian. The theory and practice of electrical power supply systems on A71-29549 # VTOL in the urban context. M. W. Hellyar aircraft are given in a systematic text intended for use in technical (United Aircraft Corp., Sikorsky Aircraft Div., Stratford, Conn.). educational courses. Equipment considered includes storage American Institute of Aeronautics and Astronautics, International batteries, dc generators, alternators, voltage regulators, current and City Management Association, National League of Cities, and U.S. frequency control systems, overload protection systems, converters, Conference of Mayors, Urban Technology Conference, New York, and power transmission and distribution systems. Principles of N. Y., May 24-26,1971, AlAA Paper 71-507. 7 p. Members, $1.50; operation, structural features, circuit diagrams, design procedures, nonmembers, $2.00. and operational specifications are included. The design procedures Discussion of the merits of helicopter systems operation in, are illustrated by examples of electrical and thermal constraints; around, and between major metropolitan areas. The performance of typical failure modes are demonstrated and various protective devices New York Airways' metropolitan helicopter service in 1970 without are explained. T.M. subsidy of any kind indicates that mature management and reliable equipment make profitable operation possible. Larger and more economical helicopters are now emerging from experience with big, A71-29529 f Aircraft materials science and treatment of high-speed military transport aircraft. These helicopter technology materials (Aviatsionnoe materialovedenie i obrabotka materialov). D. advances make VTOL transportation economically competitive with A. Ryzhinskii and V. N. Romanchuk. Moscow, Izdatel'stvo Mashino- alternative modes in terms of both cost and time. The helicopter's stroenie, 1970. 328 p. 17 refs. In Russian. environmental advantages are also briefly reviewed. M.V.E. The fundamentals of steel and cast iron processing are pre- sented, together with the principles of metallography, heat treat- ment, and thermochemical treatments. The properties of the most A71-29550 # STOL - An asset for Manhattan. R. K. important materials used in aircraft structures are examined. Ransone (American Airlines, Inc., New York, N.Y.). American Methods used for surface protection of metals and alloys against Institute of Aeronautics and Astronautics, international City corrosion are described. The foundry technology and working of Management Association, National League of Cities, ,and U.S. metals by extrusion, machining, and welding are described. The Conference of Mayors, Urban Technology Conference, New 'fork, requirements concerning the tolerances, fitting, and measurements of N.Y., May 1971, AIAA Paper 71-508. 7 p. Members, $1.50; machine elements in the aircraft industry are presented. The 24-26, Ilonmembers. $2.00. properties and testing of nonmetallic materials are examined, The merits of an integrated short-haul transportation system are including paints, resins, plastics, glues, and sound- and electric- considered between centers of industry and commerce 100 to 300 insulators. Z.W. miles apart in a makeup consisting of conventional jet aircraft, STOL aircraft, and high-speed ground transportation. It is felt that the STOL portion of this system can be designed from the outset to A71-29530 # Aircraft technician's handbook of electrical operate conveniently, reliably, and economically in congested urban equipment (Spravochnik aviatsionnogo tekhnika PO elektrooboru- and suburban areas without degrading neighborhoods in terms of dovaniiu). V. F. Bliuger and V. G. Breslavets. Moscow, Izdatel'stvo noise, air pollution, safety, or ground congestion. M.V.E. Transport, 1970. 308 p. In Russian.
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A7129551 # Operations research analysis of aircraft noise A71-29635 Evaluation of coated alloys for turbine com- abatement. Edward B. Ahlers (IIT Research Institute, Chicago, 111.). ponents of advanced gas turbine engines. Norman M. Geyer (USAF, American Institute of Aeronautics and Astronautics, International Materials Laboratory, Wright-Patterson AFB, Ohio) and Kenneth H. City Management Association, National League of Cities, and U.S. Ryan (General Motors Corp., .Allison Div., Indianapolis. Ind.). In: Conference of Mayors, Urban Technology Conference, New York, Materials '71 ; Society of Aerospace Material and Process Engineers, N.Y., May 24-26, 1971, AIAA Paper 71-525.8 p. Members, $1.50; National Symposium and Exhibit, 16th. Anaheim, Calif., April nonmembers, $2.00. Research sponsored by the Air Transport 21-23, 1971, Proceedings. Anaheim, Calif., Association of America and the Aerospace Industries of America. Society of Aerospace Material and Process Engineers (Science of Methods are developed for computing relative costs of various Advanced Materials and Process Engineering Series. Volume 16). combinations of countermeasures for reducing community noise 1971'. p. 11-29. exposures to various levels in a national. system of airport com- A program to evaluate the effects of newly developed coatings munities by extrapolation from a statistically significant sample of on modern superalloys is being conducted by Detroit Diesel Allison airports. The procedures can be used to seek the minimum-cost of Division for the Air Force Materials Laboratories. Hollow thin wall alternate near-minimum cost combinations of countermeasures. test specimens are employed so results can be related to air cooled Measures for estimating the probable error of problem solutions are turbine components. Phase I testing established correlation of incorporated in the formulation. Printed output includes: total costs laboratory testing with turbine engine and flight service test results. for reducing noise exposures to various levels and costs associated In Phase II a baseline of performance is established on current with engine modifications, airframe modification, operation changes, commercial coatings for comparison with advanced development increments in direct operating costs, and land-use changes. M.V.E. coating systems being tested in Phase I I I. Evaluation includes room and elevated temperature tensile, stress rupture, hot corrosion, oxidation-erosion, ballistic impact, thermal fatigue and high cycle fatigue tests. Test results demonstrate the importance of using thin A7129578 # Supersonic combustion research techniques in wall specimens to avaluate the effects of coating systems and thermal a hypersonic shock tunnel. Raymond John Parsons. Sheffield, environments on alloy properties. (Author) University, Doctor of Philosophy Dissertation, 1969. 267 p. 91 refs. Research supported by the Ministry of Technology; Grant No. AF EOAR 67-5. A71-29642 Aerospace materials klection and verification The use of a hypersonic shock tunnel in the simulation of of structural designs developed by means of high velocity impact combustor conditions at flight Mach numbers in excess of 10 is testing. John W. Noonan (National Aeronautical Establishment, examined, with special reference to instrumentation techniques. The Ottawa, Canada). In: Materials '71 ; Society of Aerospace Material technique of using combustion heated helium as driver gas was and Process Engineers, National Symposium and Exhibit, 16th. shown to correctly simulate combustor conditions from Mach 10 tc Anaheim, Calif., April 21-23, 1971, Proceedings. Mach 16. The starting transients in supersonic ducts were examined Anaheim, Calif., Society of Aerospace Material and Process Engineers to establish criteria for minimizing the starting time and over- (Science of Advanced Materials and Process Engineering Series. pressure. These were achieved by evacuating the duct to between Volume 161, 1971, p. 97-108.8 refs. l/lOth and 1/30th torr of the running static pressure. The Latest generation of large transport aircraft and high subsonic electromagnetic induction method for measuring gas velocity wed speed, low-level mission, military aircraft have high susceptibility to to be a novel and acceptable instrumentation technique. Z.W. catastrophic bird impact damage. New materials and processes under development to cow with this hazard require extensive impact testing for verification of design. Current analysis techniques and A71-29610 # Plane iet of a conducting fluid in a slipstream standardized test equipment are inadequate for predicting impact (Ploskaia struia provodiashchei zhidkosti v sputnom potoke). M. 2. strength of windshields and tail surface structures. A pneumatically Zhivov and Iu. A. Sokovishin. Magnitnaia Gidrodinamika, vol. 7, powered bird gun has been developed at the National Aeronautical Jan.-Mar. 1971, p. 49-52. 5 refs, In Russian. Establishment, Ottawa, Canada capable of simulating bird strikes at Partial differential equations are derived to describe the expan- velocities up to 600 to 700 MPH using birds of 4 and 8 pounds body sion of a plane jet of incompressible conducting fluid in a weight. Velocity prediction and aiming accuracy are considered to be homogeneous slipstream of this fluid. An implicit difference scheme of an unusually high order; unique packaging maintains bird intact is used for solving these equations in a nonconduction approxima- up to the target. The gun, types of birds used and instrumentation tion. The results are compared with an approximate asymptotic are described and operational experience is related. (Author) solution, showing that there is only an insignificant relation between the initial jet profile and the asymptotic drag which acts on the jet A71-29645 Rain erosion resistant radomes for supersonic during expansion in the same fluid. V.Z. aircraft. Glenn Wintermute (Goodyear Aerospace Corp., Litchfield Park, Ariz.). In: Materials '71; Society of Aerospace Material and A71-29633 Materials '71 ; Society of Aerospace Material Process Engineers, National Symposium and Exhibit, 16th, Anaheim, and Process Engineers, National Symposium and Exhibit, 16th. Calif., April 21-23, 1971, Proceedings. Anaheim, Anaheim, Calif., April 21-23, 1971, Proceedings. Anaheim, Calif., Calif., Society of Aerospace Material and Process Engineers (Science Society of Aerospace Material and Process Engineers (Science of of Advanced Materials and Process Engineering Series. Volume 16). Advanced Materials and Process Engineering Series. Volume 16). 1971, p. 138-161. Contract No. AF 33(615)-57-C-1349. 1971. 435 p. $28.50. Materials and processing methods for forming rain erosion Experimental and theoretical studies of the high-temperature resistant ceramic coated plastic structures were studied and 'eval- oxidation and ablation of superalloys and composites, and advanced uated. Manufacturing techniques were developed and optimized for processing, testing, and cost evaluation of nonmetallic materials and producing fiberglass reinforced polyimide radomes with a thin composites. The development of silane coupling agents for urethane alumina protective coating. Several prototype radomes were fabri- adhesives is described, together with fabrication of hybrid boron- cated and were tested by means of a rocket sled at Mach 3 through a graphite filament composites, three-dimensionally reinforced felt simulated rainfield. The radomes successfully passed the test. composites, and advanced plastic composites. A description is (Author) presented of rain erosion resistant radomes for supersonic aircraft, protective coatings for supersonic flight which are resistant up to 3000 F. and corrosion protection for solid rocket propulsion A71-29646 Protective coatings for a hypersonic flight systems. load-bearing refractory alloy control surface. Robert H. Witt Z.W. (Grumman Aerospace Corp., Bethpage, N.Y.). In: Materials '71 ;
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Sociery of Aerospace Material and Process Engineers, National considered. Approaches involving the avoidance of turbulence are Symposium and Exhibit, 16th. Anaheim, Calif., April 21-23, 1971, discussed giving attention to the detection system and to forecasting Proceedings. Anaheim, Calif., Society of Aero- services required. The importance of pilot training, equipment, and space Material and Process Engineers (Science of Advanced Materials pilot stress in mastering difficult situations is emphasized, and ways and Process Engineering Series. Volume 161, 1971, p. 162-175K. to reduce or alleviate deficiencies in these areas are investigated. The A materials effort was made in support of the design, fabrica- advisability of increasing structural design criteria for either static tion, and testing of a full-scale control surface (elevon) test article. strength or fatigue is discussed. G.R This paper concerns itself with two primary areas of the total effort, namely oxidation screening tests for coating selection at ambient and reduced pressures and hardware evaluations. It was found that A71-29751 # An assessment of atmospheric turbulence data R512C slurry silicide coating on Ta-1OW substrate provides a system for aeronautical applications. Jan N. Garrison (USAF, Flight Dy- that has excellent protective and self-healing qualities up to 3000 F. namics Laboratory, Wright-Patterson AFB, Ohio). In: Royal Aero- This coating retains usefulness even after short overshoot exposures to temperatures near 3200 F. Final proof of the usefulness of the nautical Society, International Conference on Atmospheric Tur- approach was demonstrated by cycling a full-scale elevon under bulence, London, England, May 18-21, 1971, Proceedings. extreme conditions with severe thermal shock prevailing in each run. Conference co-sponsored by the American Institute ot Recommendationsare included for future work along these lines. Aeronautics and Astronautics and the Canadian Aeronautics and (Author) Space Institute. London, Royal Aeronautical Society, 1971. 18 p. 35 refs. Turbulence models currently used for aircraft design attempt to answer questions regarding the probability for the aircraft to A71-29656 Advanced composite cost comparison. D. D. Dial and M. S. Howeth (General Dynamics Corp., Convair Aerospace encounter a gust input of any given magnitude, and the power Div., Fort Worth, Tex.). In: Materials '71; Society of Aerospace spectral density of the gust input. The Low-Low Altitude Critical Material and Process Engineers, National Symposium and Exhibit, Atmospheric Turbulence Project is discussed. The data obtained in 16th. Anaheim, Calif., April 21-23, 1971, Proceedings. this project confirmed that lateral gusts are somewhat more severe Anaheim, Calif., Society of Aerospace Material and than vertical gusts at very low altitudes. Turbulence in the free Process Engineers (Science of Advanced Materials and Process atmosphere is considered, and general conclusions regarding CAT Engineering Series. Volume 16). 1971, p. 302-314. activity are drawn. Aspects of turbulence in and around thunder- storms are examined. G.R. Relative cost comparisons of advanced composite applications with conventional material components are presented. Specific detailed comparison studies are described for several components selected from a supersonic fighter-bomber. These comparisons A71-29752 # Comparison of thunderstorms over Oklahoma include material and labor required to fabricate the wing trailing edge and Malaysia based on aircraft measurements. J. T. Lee (NOAA, panel, wing pivot fitting doubler, and wing pivot fairings. The wing National Severe Storms Laboratory, Boulder, Colo.) and A. trailing edge components were manufactured on a research and McPherson (Royal Aircraft Establishment, Bedford, England). In: development basis and did not prove to be cost-competitive. The Royal Aeronautical Society, International Conference on Atmo- other two compilnents were produced with either boron-epoxy or spheric Turbulence, London, England, May 18-21, 1971, Proceed- graphite epoxy materials and are currently in production. Both of ings. Conference co-sponsored by the American these applications are shown to be cost-competitive with other Institute of Aeronautics and Astronautics and the Canadian Aero- approaches using conventional materials. Z.W. nautics and Space Institute. London, Royal Aeronautical Society, 1971. 12p. A Canberra WH793 and the RB57F. a USAF weather recon- A71-29749 Royal Aeronautical Society, International naissance aircraft, were used in the thunderstorm investigations. The Conference on Atmospheric Turbulence, London, England, May results obtained for Oklahoma and for Malaysia were similar except 18-21, 1971, Proceedings. Conference co-sponsored by the American for the longer duration of turbulence patches over Oklahoma. This Institute of Aeronautics and Astronautics and the Canadian Aeronau- difference corresponds to the differing echo patterns in the two tics and Space Institute. London, Royal Aeronautical Society, 1971. areas. It appears that the energy of larger Malaysian thunderstorms is 453 p. less than that of the larger Oklahoma thunderstorms, since the The topics deal with knowledge of the atmosphere based on former evidences less overall vertical development, smaller top scientific observation, stressing thunderstorms and clear air turbu- diameter, and, from analysis of soundings, less energy appears to be lence, considering then the nature and physics of the environmental available for it. G.R. wind field (incluaing turbulence) from the theoretical point of view. Attention is given to operational aspects and experience, aircraft control and load alleviation, human factors, and structural loads and A71-29753 # Flight studies of clear air turbulence - The design. current position and further research needs. K. Mather (National F.R.L. G. Aeronautical Establishment, Ottawa, Canada). In: Royal Aero- nautical Society, International Conference on Atmospheric Tur- bulence, London, England, May 18-21, 1971, Proceedings. . A71-29750 * # Atmospheric turbulence and the air trans- Conference co-sponsored by the American Institute of portation system. Philip Donely (NASA, Langley Research Center, Aeronautics and Astronautics and the Canadian Aeronautics and Hampton, Va.). In: Royal Aeronautical Society, International Space Institute. London, Royal Aeronautical Society, 1971. 12 p. 7 Conference on Atmospheric Turbulence, London, England, May refs. 18-21, 1971, Proceedings. Conference co- A highly instrumented T-33 was used in the studies. Aircraft sponsored by the American Institute of Aeronautics and Astro- instrumentation was designed 'to measure the three orthogonal nautics and the Canadian Aeronautics and Space Institute. London, components of turbulence along the major aircraft axes and the Royal Aeronautical Society, 1971. 14 p. fluctuating static temperatures. The mean horizontal wind and In regard to extreme rough air, the aim must be to increase the temperature fields could also be determined. The turbulence energy chances of survival of the aircraft. In the case of moderate budget is discussed and the flight data are analyzed. It is pointed out turbulence, the aim is to provide the pilot with control and structural that two aspects of the results reported may be applicable to the capability for safe operation on a day-to-day routine basis. Opera- problem areas of CAT forecasting and airline operations. G.R. tional data on gust accelerations for turbine-powered aircraft are
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A71-29755 # Measurements of stratospheric airflow and or more. The records cited are considered to be invaluable in clear air turbulence, up to 63000 ft, over and downwind of obtaining a better understanding of the mesoscale structure of mountainous terrain. J. M. Nicholls (MeteorologicalOffice, London, turbulence and its effect on airspeed, altitude and, indirectly, pilot England). In: Royal Aeronautical Society. International Conference reaction. Attention is given to thunderstorm turbulence. CAT and on Atmospheric Turbulence, London, England, May 18-21, 1971, weather-induced turbulence, the forecasting of mountain waves, low Proceedings. Conference co-sponsored by the level wind shears, and detection equipment. F.R.L. American Institute of Aeronautics and Astronautics and the Canadian Aeronautics and Space Institute. London, Royal Aero- nautical Society, 1971. 12 p. 15 refs. 871-29765 # Development of airborne remote clear air Two series of flights have been made over the Western USA. turbulence (CAT) detection equipment. Andrew S. Carten, Jr. and Important features of the flow patterns obtained on 4 days during Wilbur H. Paulsen (USAF, Cambridge Research Laboratories, the project are described. The results obtained indicate that clear air Bedford, Mass.). In: Royal Aeronautical Society, International turbulence is associated with two distinct features of vertical cross Conference on Atmospheric Turbulence, London, England, May sections of air flow over and downwind of mountains, namely large 18-21, 1971, Proceedings. Conference co- isentropic oscillations in the flow, and negative wind shear zones sponsored by the American Institute of Aeronautics and Astro- which were disturbed by orographically induced waves. The largest nautics and the Canadian Aeronautics and Space Institute. London, stratospheric oscillations in the flow patterns, in which turbulence Royal 4eronautical Society, 1971. lop. 16 refs. was frequently found, were usually located almost over the Investigation of methods for detect-ing CAT ahead of an aircraft mountain. G.R. with the intent to achieve an operationally useful system. Major attention is given to laser and infrared techniques. It is pointed out that the pulsed Doppler laser is expensive and cumbersome, while the A71-29756 # Measurement of extreme mechanical tur- relatively inexpensive infrared systems are on the verge of practical bulence during low level flights by Mirage A3-76. C. K. Rider, M. R. use. F.R.L. Thomson, and F. E. Verinder (Department of Supply. Aeronautical Research Laboratories, Melbourne, Australia). In: Royal Aero- nautical Society, International Conference dn Atmospheric Tur- A71-29767 # Stratospheric turbulence and temperature bulence, London, England, May 18-21. 1971, Proceedings. change measurements from the Coldscan program. J. I. MacPherson Conference co-sponsored by the American Institute of (National Aeronautical Establishment, Ottawa, Canada) and E. G. Aeronautics and Astronautics and the Canadian Aeronautics and Morrissey (Department of Mines and Technical Surveys, Meteorologi- Space Institute. London, Royal Aeronautical Society, 1971. 8 p. cal Service, Ottawa, Canada). In: Royal Aeronautical Society, On Sept. 11, 1969, an instrumented Mirage fighter-aircraft International Conference on Atmospheric Turbulence, London, carried out three flights in an area of severe low level turbulence. England. May 18-21, 1971, Proceedings. Con- Acceleration maxima of +3.5 g, -1.5 g were recorded. True gust ference co-sponsored by the American Institute of Aeronautics and velocities have been computed for 5400 sec of recorded data. Results Astronautics and the Canadian Aeronautics and Space Institute. presented apply to conditions experienced for more than five hours London, Royal Aeronautical Society, 1971. 11 p. 8 refs. on the one day. All records were obtained on the same track, about Project Coldscan has been expanded to include the relationship 100 miles long at pressure-height levels between 2900 and 4200 f'. of the nature and severity of the recorded phenomena to meteorolog- G.R. ical conditions and the underlying terrain. Eighty-three Coldscan flights to date have shown that moderate stratospheric turbulence occurred about 0.5% of the time above 40,000 ft and tended to be A71-29763 # Partially trapped waves. F. H. Berkshire and F. concentrated over mountains. More frequent, and perhaps more W. G. Warren (Imperial College of Science and Technology, London, important to the SSTs, are the encounters with temperature waves England). In: Royal Aeronautical Society, International Conference and horizontal temperature gradients exceeding 2.5 C in 3 n mi. on Atmospheric Turbulence, London, England, May 18-21, 1971, These averaged 0.8 encounters per 1000 n mi tended to shoN a peak Proceedings. Conference co-sponsored by the in their distribution at 60,000 ft, and were associated with American Institute of Aeronautics and Astronautics and the turbulence of at least moderate intensity only 1/6 of the time. Canadian Aeronautics and Space Institute. London; Royal Aero- Although the largest temperature changes have been encountered nautical Society, 1971. 8 p. 9.refs. only over mountains to date, a considerable number of temperature Consideration of atmospheric models which contain an upper changes with gradients up to this level have been measured on the layer above the tropopause in which the Scorer parameter (which SST routes off the east coast of North America. M.M. depends on the undisturbed atmospheric parameters) becomes large. Waves which would be trapped in the troposphere by a neutral stratosphere are thus able to pass through the tropopause and A7129768 # Air turbulence - Hidden and revealed. M. N. propagate into the higher regions of the atmosphere. F.R.L. Mom (British Air Line Pilots' Association, Hayes, Middx., England). In: Royal Aeronautical Society, International Conference on Atmo- spheric Turbulence, London, England, May 18-21, 1971, Proceed- A71-29764 # Operational forecasting and analysis of tur- ings. Conference co-sponsored by the American bulence. W. Boynton Beckwith (United Air Lines, Inc., Chicago, Ill.). Institute of Aeronautics and Astronautics and the Canadian Aero- In: Royal Aeronautical Society, International Conference on At- nautics and Space Institute. London, Royal Aeronautical Society, mospheric Turbulence, London, England, May 18-21, 1971, Proceed- 1971.6~. ings. Cunference co-sponsored by the American Discussion of primary and secondary effects of air turbulence Institute of Aeronautics and Astronautics and the Canadian Aero- and of criteria for avoiding it. It is pointed out that air turbulence nautics and Space Institute. London, Royal Aeronautical Society, might be better avoided by action in the following areas: (1) 1971. 13p. 11 refs. observation and forecasting over smaller scale sections of airspace; Consideration of turbulence as it affects transport aircraft, using (2) detection of even moderate or light turbulence; (3) direct the Fairchild or Lockheed accelerometer records as an indication communications and more effective involvement of ATC personnel that is quite consistent with the subjective evaluation assigned to an in the handling of data; and (4) provision of ATC techniques and event by an experienced airline pilot. Moderate turbulence is defined equipment which recognize turbulent and turbulence-prone areas as as that which a transport aircraft registers on its recorder as an nonvalid airspace. It is noted that the effects can also be minimized excursion from the 1.Og reference of plus or minus 0.50 to 0.759. by a reexamination of aircraft design characteristics and automatic Severe turbulence is equivalent to an excursion of plus or minus 1.Og flight control modes. M.M.
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A71-29770 # Lessons to be learned from accidents at- on Atmospheric Turbulence, London, England, May 18-21, 1971, tributed to turbulence. Alan I. Brunstein (National Transportation Proceedings. Conference co-sponsored by the Safety Board, Bureau of Aviation Safety, Washington, D.C.). In: American Institute of Aeronautics and Astronautics and the Royal Aeronautical Society, International Conference on Atmo- Canadian Aeronautics and Space Institute. London, Royal Aero- spheric Turbulence, London, England, May 18-21, 1971, Proceed- nautical Society, 1971.9 p. ings. Conference co-sponsored by the American Some investigation results are discussed about an automatic Institute of Aeronautics and Astronautics and the Canadian Aero- aircraft landing system's inadequate responses to air turbulence nautics and Space Institute. London, Royal Aeronautical Society, effects the system was supposed to neutralize. It was found that the 1971. 12p. largest disturbing input to the aircraft was turbulence. With hind Analysis of air carrier accidents caused by air turbulence from sight it was determined that by modification of the original system it 1964 to 1969 in the total number of 441 accidents, including 97 was possible to improve the response to turbulence. Buildings near involving turbulence. The main lessons learned from turbulence- airfields affecting the airflow in threshold areas probably cause the involved accidents are: (1) turbulence is one of the major in-flight most significant gusts. M.V.E. weather problems; (2) airborne weather radar is an excellent thunderstorm-avoidance tool; (3) airborne weather radar must be A71-29774 * # Analysis of subjective ratings for the XB-70 maintained and operated properly; (4) training should be formalized airplane response to atmospheric turbulence and controlled inputs. in the use and interpretation of airborne weather radar; (5) recurrent Ronald J. Wilson and L. J. Ehernberger (NASA, Flight Research airborne weather radar training is desirable; (6) CAT forecasts need Center, Edwards, Calif.). In: Royal Aeronautical Society, Inter- considerable improvement; (7) CAT detection systems, airborne and national Conference on Atmospheric Turbulence, London, England, ground-based, are needed; and (8) real-time weather data are needed on the ground, and most certainly in the cockpit. M.M. May 18-21, 1971, Proceedings. Conference co- sponsored by the American Institute of Aeronautics and Astro- nautics and the Canadian Aeronautics and Space Institute. London, A71-29771 # Turbulence experience recorded by CAADRP. Royal Aeronautical Society, 1971. 11 p. 14 refs. J. R. Sturgeon (Royal Aircraft Establishment, Farnborough, Hants., Description of the XB-70 crew's subjective evaluation of the England). In: Royal Aeronautical Society, International Conference aircraft's response in comparison with measured accelerations. The on Atmospheric Turbulence, London, England, May 18-21, 1971, turbulence response of the crew station and other fuselage locations Proceedings. Conference co-sponsored by the is evaluateei, and the crew's reaction to controlled sinusoidal American Institute of Aeronautics and Astronautics and the excitations of the airframe during flight is examined. Results show Canadian Aeronautics and Space Institute. London, Royal Aero- that the pilot subjective ratings of turbulence intensity in comparison nautical Society, 1971. 10 p. 8 refs. to the accelerations measured at the pilot's station and the center of Discussion of the characteristics of flight in severe turbulence, gravity caused some overlap of acceleration range. For a given encountered during 23,000 flying hours, from an analysis of analog acceleration range, 0.15 to 0.259. the turbulence could have been trace records of 65,000 hr of operational civil flying including rated from light to severe. The pilot ratings were also more severe for airspeed, normal acceleration, height, air tempqrature, control a given acceleration range than had been recommended by previous surface and flight attitude parameters. Attention .- drawn to reporting criteria. M.M. variations in rate of climb of up to 8000 ftlmin, maneuver accelerations of up to 0.7 g and rapid control surface movements recorded during automatic and manual flight in severe atmospheric A71-29775 # Gust effects on V/STOL aircraft. Grant B. disturbances. The possibilities of reducing structural loads by Skelton (Honeywell, Inc., Minnedpolis, Minn.). In: Royal Aero- improved aircraft system design, maintenance and operational nautical Society, International Conference on Atmospheric Tur- practices, are considered, and an example of variation in the bulence. London, England, May 18-21, 1971, Proceedings. performance of nominally identical aircraft is given. M.M. Conference co-sponsored by the American Institute of Aeronautics and Astronautics and the Canadian Aeronautics and Space Institute. London, Royal Aeronautical Society, 1971. 15 p. A71-29772 * # Control considerations in severe turbulence. A. Description of a mathematical gust model suitable for analyses Gerald Rainey, William D. Grantham, and William P. Gilbert (NASA, of flight in the lowest 100 meters of the atmosphere. The model is Langley Research Center, Hampton, Va.). In: Royal Aeronautical useful for takeoffs and landings of all aircraft and for significant Society, International Conference on Atmospheric Turbulence, portions of typical V/STOL flight profiles. The model consists of London. England, May 1821, 1971, Proceedings. eight gusts generated by eight white noise sources, eight filters, and Conference co-sponsored by the American Institute of lines. It is based upon good mean wind profile data, Aeionautics and Astronautics and the Canadian Aeronautics and three delay Space Institute. London, Royal Aeronautical Society, 1971. 16 p. 20 spotty gust spectral data, and very sparse probability data. The mbdel was grossly simplified in order to be convenient for aircraft refs. gust response analyses without having to pay a severe approximation The intensive studies which seem to have solved the 'jet upset price. Hybrid simulation flights of the Ryan XV-5 V/STOL in crisis' of the early 1960s are briefly reviewed. Some recent turbulence showed that the wing-to-tail transport delay and the information adding to the primarily longitudinal results obtained spanwise shear of head-on and vertical gusts were important and had previously, concerning the possible influence of lateral-directional to be retained in the gust model. The simulation tests also showed characteristics, particularly an unstable spiral mode, is described. The that the XV-5 flew nonlinearly at low airspeeds. M.M. need for a rational, quantitative method of estimating optimum turbulence penetration conditions and the results of initial attempts to provide such information is presented. The basic transonic A71-29776 # Control of V/STOL aircraft in turbulence. aerodynamic characteristics of advanced transport aircraft have been Robert L. Swaim (Purdue University, West Lafayette, Ind.). In: reviewed and, although no immediate controllability problems are Royal Aeronautical Society, International Conference on Atmo- obvious, it is suggested that the characteristics of such transports in spheric Turbulence, London, England, May 18-21, 1971, Proceed- severe turbulence will need to be examined carefully prior to fleet ings. Conference co-sponsored by the American operations. (Author) Institute of Aeronautics and Astronautics and the Canadian Aero- nautics and Space Institute. London, Royal Aeronautical Society, A71-29773 # Development of an approach and landing 1971. 12 p. 18refs. Grant No. NGR-15005069. system with special reference to the effects of turbulence. R. M. P. Description of the nature of flight path control (guidance and McManus (Hawker Siddeley Aviation, Ltd., Hatfield, Herts., maneuvering) problem and the attitude control (stability augmenta- England). In: Royal Aeronautical Society, International Conference tion) problem for V/STOL aircraft. An analytical approach and
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design methodology, based on the state variable methods of modern ceedings. Con'ference co-sponsored by the control theory, and which structures the stability augmentation American Institute of Aeronautics and Astronautics and the system required for satisfactory handling qualities, while simulta- Canadian Aeronautics and Space Institute. London, Royal Aero- neously yielding minimum required values of stabilization control nautical Society, 1971. 16 p. 9 refs. power, is described. The process uses power spectral density An examination is made of the gust loads encountered by descriptions of the homogeneous turbulence environment. aircraft on research flights taking a large number of time intervals of Additional stabilization control power is frequently required to about 1 minute. A simple means of describing the intensity of the counter the effects of heterogeneous or discrete turbulence typified turbulence and the number of gusts per kilometer is devised. The by wind shears and vortex patterns generated by osbtacles such as procedure is used to examine records from a few tens of thousand trees, hills, and buildings. Such turbulence is nonstatistical in nature flying hours and to define the loads to be expected on different and generates nonlinear input disturbances to an aircraft which are aircraft. The method allows an examination to be made of selected best analyzed by a momentum transfer approach. M.M. short traverses of turbulence either in research or operational flying and to appraise their intensity relative to average conditions. A combination of the data from research and operational flying can be A7129777 # Some effects of designing for increased safety made to give information that can be used to define design requirements. (Author) in turbulence. M. W. Salisbury (British Aircraft Corp., Ltd., London, England). In: Royal Aeronautical Society, International Conference on Atmospheric Turbulence, London, England, May 18-21, 1971, Proceedings. Conference co-sponsored by the A7129785 # Some results on gust alleviation. Gabriel American Institute of Aeronautics and Astronautics and the Coupry (ONERA, Chitillon-sous-Bagneux, Hauts-de-Seine, France). Canadian Aeronautics and Space Institute. London, Royal Aero- In: Royal Aeronautical Society, International Conference on At- nautical Society, 1971. 12 p. mospheric Turbulence, London, England, May 18-21, 1971, Proceed- The development of cruise altitude limitations to provide ings. Conference co-sponsored by the American adequate buffet margins in turbulence is reviewed, and the problems Institute of Aeronautics and Astronautics and the Canadian Aero- facing the aircraft designer in establishing and improving the nautics a'nd Space Institute. London, Royal Aeronautical Society, allowable operating altitudes are discussed. The effect of lags in flow 1971. 12 p. 6 refs. separations due to the rapid change of incidence in a gust is A method is described which provides gust alleviation without illustrated by a read-out from a gust encounter. Finally it is shown any change to the flight mechanics of the aircraft. In this method, that an autopilot mode designed for use in turbulence can reduce the the aircraft movement is corrected, assuming that the turbulent field pitch and 'g' excursions as well as improve the structural fatigue life. is known. Turbulence is measured, in real time, aboard the aircraft (Author) with the aid of data supplied by vanes, gyrometers, and accelerome- ters. Orders to the controls are determined as a linear functional law of turbulence. The functional law is determined using Wiener's A71-29779 * # Simulation techniques used in investigating mathematical approach, in the case of a turbulent field characterized aircraft accidents. Richard S. Bray and Seth B. Anderson (NASA, by a rational power spectrum. For actual power spectra which are no Ames Research Center, Moffett Field, Calif.). In: Royal Aerona!.*'cal longer rational, an expansion in Laguerre functions is added to Society, International Conference on Atmospheric Turbulence, Wiener's solution. The validity of the theory was checked on an London, England, May 18-21, 1971, Proceedings. analog computer which was excited by actual records of in-flight Conference co-sponsored by the American Institute of measured turbulence. Some flight tests that have been performed are Aeronautics and Astronautics and the Canadian Aeronautics and discussed. O.H. Space Institute. London, Royal Aeronautical Society, 1971. 10 p. The use of simulation techniques is discussed, first for the general case of a typical turbulence 'upset' to show how simulation A71-29786 # Design for lateral gusts. H. P. Y. Hitch (British techniques can be used to uncover possible reasons for the upset. Aircraft Corp., Ltd.. Weybridge, Surrey, England). In: Royal Next, the techniques are applied to two specific accidents to show Aeronautical Society, International Conference on Atmospheric the degree of simulator sophistication needed to match the accident Turbulence, London, England, May 18-21, 1971, Proceedings. conditions properly. Finally, several important factors are discussed Conference co-sponsored by the American In- that should be considered in using simulation techniques for accident stitute of Aeronautics and Astronautics and the Canadian Aero- investigations. O.H. nautics and Space Institute. London, Royal Aeronautical Society, 1971. B p. The dynamic response of aircraft with a T-tail configuration to lateral gusts is examined. It is shown that the conventional R71-29782 # Commercial aircraft flying in turbulence - antisymmetric analysis is inappropriate and an analysis involving Some considerations. Scott Flower (Pan American World Airways, both antisymmetric and symmetric motion is needed. Values Inc., New York, N.Y.). In: Royal Aeronautical Society, International obtained by the current isolated gust procedure and those obtained Conference on Atmospheric Turbulence, London, England, May 18-21, 1971, Proceedings. Conference co- by the proposed design envelope procedure are presented and sponsored by the American Institute of Aeronautics and Astro- compared. O.H. nautics and the Canadian Aeronautics and Space Institute. London, Royal Aeronautical Society, 1971. 9 p. Factors that affect the pilot's ability to fly in turbulence - Le., A71-29787 # The effects of atmospheric turbulence on aircraft characteristics, instrumentation, procedures, pilot training, handling qualities and structural loads. William H. Austin, Jr. (USAF, and kinesthetic cues - are discussed. They are confronted with the Aeronautical Systems Div., Wright-Patterson AFB, Ohio). In: Royal capabilities of the 8747 aircraft and the efficiency of other tools Aeronautical Society, International Conference on Atmospheric provided by the airline industry to their pilots for successful flight in Turbulence, London, England, May 18-21, 1971, Proceedings. turbulence. O.H. Conference co-sponsored by the American Insti- tute of Aeronautics and Astronautics and the Canadian Aeronautics and Space Institute. London, Royal Aeronautical Society, 1971. 11 A71-29784 # Gust loads for structural design. J. Taylor p. 5 refs. (Royal Aircraft Establishment, Farnborough, Hants., England). In: Trad;tionally, handling qualities and structural loads have been Royal Aeronautical Society, International Conference on Atmo- regarded as independent aeronautical engineering disciplines when, in spheric Turbulence, London, England, May 1&21, 1971, Pro- fact, they are very closely interrelated, particularly when atmospher-
42 7 A71-29788 ic turbulence is considered. It is shown that lack of consideration of England), and R. Shaw (Liverpool, Unlversity, Liverpool, England). the two disciplines together can lead to unfortunate results. Use of a Institution of Mechanical Engineers, Proceedings, vol. 184, pt. 1, no. high authority stability augmentation system can yield results that 61, 1969-1970.p. 11 19-1131; Communications, p. 1132;Author's will improve handling qualities and reduce structural loads, though Reply, p. 1133. 10 refs. similar results could be attained by careful attention to inherent Specifications are given and test performance analysis is made to stability, particularly Dutch roll damping. Recognition of the basic determine the suitability of these turbine designs for turbocharger interaction of handling qualities and structural loads by engineering application. Test results are given in a form allowing the turbine management is of utmos1 importance, and constant vigilance is efficiencies to be plotted vs mean dimensionless blade speed required to insure that adequate consideration is given to the irrespective of the pulsation level. The test data displays can be interactionsduring design of an aircraft. (Author) directly used for design purposes and in matching calculations, permitting the assessment of the efficiency penalty due to pulse flow, of the effect of pulse flow on turbine size selection, and of the preferred degree of reaction under pulse flow. Further tests under A71-29788 # The analysis of normal accelerations ex- modified pulse conditions with a significant windage period are perienced by fleets of transport aircraft. N. I. Bullen (Royal Aircraft suggested. V.Z. Establishment, Farnborough, Hants., England). In: Royal Aero- nautical Society, International Conference on Atmospheric Tur- bulence, London, England, May 18-21, 1971, Proceedings. a71-29826 Testing of fubricants for the Olympus T. Conference co-sponsored by the American Institute of 593. F. Blenkiron (Rolls-Royce, Ltd., Bristol Engine Div., Bristol, Aeronautics and Astronautics and the Canadian Aeronautics and England). (Symposium on Lubricant Test Devices and Their Relation Space Institute. London, Royal Aeronautical Society, p. 1971. I1 6 to Service Conditions, Paisley College of Technology, Paisley, refs. Scotland, Sept. 7-11, 1970.) Wear, vol. 17, May-June 1971, p. An analysis of tatigue load meter records from a fleet of 367-379.Research supported by the Ministry of Technology. transport aircraft is made to examine the variation in the occurrence Discussion of new types of lubricant and new methods of of loads and to determine whether differences between aircraft are evaluating lubricants for the Olympus 593 supersonic engiue. The significant. It is shown how the knowledge so gained can be applied main requirements for a lubricant for the Concorde engines are to determine appropriate factors to allow for times when the fatigue defined in terms of bulk thermal stability, resistance to breakdown in load meter is inoperative. Seasonal variations of counting rates are a hot bearing, oil mist coking, and gear load carrying. The rigs used discussed. (Author) to evaluate these various properties are described, and some of the reasons for the choice of these particular rigs are given. Problems which may arise on mainshaft bearings are split into two gioups, A71-29789 # An analysis of gust velocities for application to fatigue at high load, and wear due to skidding at iow load. The test aircraft design. F. K. Atnip and J. Gault (Boeing Co., Seattle, Wash.). rigs and methods used to explore these phenomena are described. It In: Royal Aeronautical Society, International Conference on At- is noted that fatigue is relatively well understood but skidding at low mospheric Turbulence, London, England, May 18-21,1971, Proceed- loads is a much more complex matter. Minor lubricant problems have ings. Conference co-sponsored by the American arisen on early standards of engine but these have now been Institute of Aeronautics and Astronautics and the Canadian Aero- overcome and performance of the oils is satisfactory. It is concluded nautics and Space Institute. London, Royal Aeronautical Society, that oil evaluation methods are successfs!ly screening out un- 1971. 11 p. 14 refs. satisfactory oils. M.M. Factors necessary to establish appropriate gust criteria for the design and for monitoring the fatigue life of aircraft are examined. They include: frequency distributions of gust velocities in patches of turbulence; frequency distributions of the rms values of gust am-29833 it Measurements of static strains on titanium velocities for the patches; and the form of gust velocity power under rapid heating. T. E. H. Lemon (British Aircraft Corp., Ltd., spectral densities and frequency distributions of associated integral Guided Weapons Div., Bristol, England). Strain, vol. 7, Apr. 1971, p. scale lengths. Effects of aircraft speed on turbulence statistics are refs. Research sponsored by the Ministry of Technology. also examined. O.H. 66-73.7 Resistance changes with temperature were measured for various types of strain gauges on a titanium specimen subjected to different conductive heating rates. The tests were conducted for the purpose A71-29811 Trends in the development of aeronautical of developing a practical strain measuring system for a triangular turbojet engines (Tendenze nello sviluppo dei turbogetti aeronautici). titanium wing heated to 520 deg C at a maximum rate of 40 deg C Salvatore Caggiani. Rivista Aeronautica, vol. 47, Apr. 1971, p. per sec. The results show that the Microdot SG 420 strain gauge was 643-664.11 refs. In Italian. the only sensor suitable for this application. Gauge preparation and Survey of the current state of development of subsonic and connection procedures are outlined. T.M. supersonic turbojet engines. The engines considered are built by Pratt and Whitney, GE, and Rolls-Royce. Engines manufactured by smaller companies are also reviewed. The particular aspects considered are general engine architecture, dependable operation and reliability, A71 -29860 Thrust measurement of great accuracy of specific weight and specific consumption. It is pointed out that all aircraft propulsion systems giving particular attention to a hydraulic the innovations and refinements made to turbojet engines, besides force measurement device. II (Schubmessung grosser Genauigkeit an requiring lengthy tests, necessitate expensive investments and a Flugtriebwerken unter besonderer Berucksichtigung einer hydrau- selection of materials which are ever more difficult to produce and lischen Kraftmesseinrichtung. 11). Joachim Frubose. Archiv fur purchase. M.M. technisches Messen und industrielle Messtechnik, May 197 1, p. 85-88. 7 refs. In German. Relations between the displacement of the piston of the device A71-29819 A comparison of the performance of three on one side and the oil pressure and the pressure to be measured on model axial flow turbines tested under both steady and pulse flow the other side are investigated. Factors connected with diametrical conditions. H. Daneshyar, J. H. Horlock (Cambridge University, clearance and roundness of the edges have an effect on these Cambridge, England), K. J. Edwards (D. Napier and Son, Ltd., relations. The quantity of oil flowing through the device is Liverpool, England), M. S. Janota (Queen Mary College, London, determined, and questions of calibration and measurement accuracy England), R. D. Pearson (Bath University of Technology, Bath, are discussed. A sensitivity of 0.04 per cent was obtained. G.R.
428 A71 -29930
A71-29868 * # An evaluation of theories for predicting tur- vorticity distribution on the airfoil contour and can calculate the bulent skin friction and heat transfer on flat plates at supersonic and potential flow pressure distribution on multielement airfoils with hypersonic Mach numbers. Edward J. Hopkins and Mamoru lnouye deflected leading edge devices and slotted trailing edge flaps. Second, (NASA, Ames Research Center, Moffett Field, Calif.). AIAA Journal, a wall blowing technique was developed which is essential for vol. 9, June 1971, p. 993-1003. 65 refs. obtaining reliable two-dimensional wind tunnel data for airfoils in An evaluation of existing theories is presented, which is the high lift condition, and for testing effectively complex high lift restricted to flat plates, cones, and wind-tunnel walls on which the models. Comparisons of calculated and experimental data obtained flow is essentially isothermal and isobaric. It is suggested that the on some of the complex configurations tested at NAE using the wall Van Driest II theory (1956) be used to predict the turbulent skin blowing technique demonstrate the usefulness of the methods used friction for the design of supersonic and hypersonic vehicles until and the approach to the design of future high lift systems. (Author) additional direct measurements of skin friction are made. This theory with an assumed Reynolds analogy factor of 1.0 should also be used to predict the heat transfer to surfaces exposed to hypersonic Mach A71-29911 # The Yak-40 aircraft flight test procedures. K. numbers. For heat transfer predictions to near adiabatic surfaces B. Bekirbaev, A. D. Miranov, and I. I. Sneshko (lakolev Design exposed to supersonic and lower Mach numbers, the use of a Bureau, Moscow, USSR). (Canadian Aeronautics and Space Institute, Reynolds analogy factor of 1.2 is recommended. For the incom- Flight Test Symposium, Montreal, Canada, Feb. 9, 1971.) Canadian pressible case, also required for compressible transformation theories Aeronautics and Space Journal, vol. 17, May 1971, p. 185-188. such as that of Van Driest, additional direct measurements of skin The flight testing of the Yak-40 jet passenger aircraft for friction are needed at extremely high ana low Reynolds numbers compliance with the Civil Airworthiness Requirements of the USSR before the KBrmin-Schoenherr formula can be accepted without was performed in the three stages of manufacturer's, government, reservation. O.H. and service tests. A series of special ground tests and investigations, such as wind tunnel tests, static structural and vibration tests, preceded the manufakturer's flight tests. The manufacturer's tests A71-29887 * # Effect of angle of attack on boundary-layer were carried out simultaneously on four experimental aircraft, transition at Mach 21. Michael C. Fischer and David H. Rudy together with government flight testing. Service tests were carried (NASA, Langley Research Center, Hypersonic Vehicles Div., out on six production aircraft. The service tests, including some Hampton, Va.). AIAA Journal, vol. 9, June 1971, p. 1203-1205. 8 flights under special route conditions, amounted to 2,482 flights. refs. The Yak-40 is undergoing certification tests by the Italian authorities Boundary-layer transition at angles of attack in the range from 0 to prove compliance with the technical standards of the US. Federal to 3 deg was studied on a slender cone in a nbminal Mach-20 flow Aviation Regulations. Demonstrationflights of the Yak40 have been promoted on the leeward ray and essentially fixed on the windward made in 36 countries in Europe, Asia and America. M.M. ray. The obtained angle-of-attack transition results directly conflict with previously reported results with a cone of identical geometry tested in the same facility. The results obtained are believed to A7129925 * # A review of the mass-flux probe. Lloyd illustrate the correct trends as the results from the previous N. Krause and George E. Glawe (NASA, Lewis Research Center, meisurements were probably adversely influenced by the questic-- Cleveland, Ohio). American Institute of Physics, American Society of able method of detecting transition. M.V.E. Mechanical Engineers. Instrument Society of America, and National Bureau of Standards, Symposium on Flow - Its Measurements and Control in Science and Industry, Pittsburgh, Pa., May 9-14, 1971, A71-29889 Pressures on boat-tailed afterbodies in tran- # Paper. 28 p. 22 refs. sonic flow with a low-thrust jet. D. M. Sykes (City University, The mass-flux probe is used to measure the mass flow rate per London, England). AIAA Journal, vol. 9, June 1971. p. 1206-1208. unit cross-sectional area of supersonic streams. The probe consists of Extension of Sykes' (1970) previous base drag study of an aspirating tube with a supersonic inlet which 'swallows' the shock axisymmetric afterbodies to pressure distributions on a family of and ingests the stream flow tube. The mass flow rate per unit area of afterbodies at stream Mach numbers from 0.8 to 1.2 and to the the stream is determined by measuring the flow rate of ingested gas effect of a low-thrust jet on these pressures. The base pressure through the probe at a convenient downstream station, and then coefficient change with jet flow and the afterbody drag coefficient dividing by the probe's inlet area. The instrument has been applied to variation for various afterbody geometries with jet flow are il- studies of supersonic boundary layers, and of high-enthalpy, high- lustrated in diagrams and briefly discussed. M.V.E. temperature gas flows, such as may occur in hypersonic flight. This review presents a description of the instrument, a historical review of work reported in the literature, and a discussion of the factors A7129890 # Effect of yaw of repose on ballistic match of influencing performance. These factors include probe inlet geometry, similar projectiles. H. R. Vaughn and G. G. Wilson (Sandia angle of attack, and Reynolds and Mach number effects. (Author) Laboratories, Albuquerque, N. Mex.). AlAA Journal, vol. 9, June 1971, p. 1208-1210. 6 refs. AEC-supported research. Using a given aeroballistic axis system, the yaw of repose part of A7129930 * # Airbreathing nuclear propulsion - A new look. the motion of a shell is considered. In the light of yaw of repose Frank E. Rom (NASA, Lewis Research Center, Cleveland, Ohio). theory, it is shown that the ratio of roll moment of inertia to the US. Air Force Office of Scientific Research, Symposium on static margin predominates in controlling the yaw of repose angle Advanced Propulsion Coccepts, 6h, Niagara Falls, N. Y., May 4-6, magnitude in the usual projectile problem. Aside from the drag-to- 7971, Paper. 23 p. 19 refs. weight ratio, which dominates any projectile ballistic match problem, Aircraft with gross weights of at least one million pounds are the yaw of repose is shown to be the single most important projectile necessary to make nuclear aircraft-practical. However, the example parameter. M.V.E. of the Lockheed C-5 and the Boeing 747, which weigh almost one million pounds, has shown the practicality and profitability of very large subsonic aircraft. The major obstacle to the use of an aircraft A7129910 # Aerodynamic research on high lift systems. F nuclear powerplant is the problem of public safety in major aircraft Mavriplis (Canadair, Ltd., Montreal, Canada). Canadian Aeronautics accidents. An experimental investigation of techniques for preven- and Space Journal, vol. 17, May 1971, p. 175-183. 8 refs. tion of reactor containment vessel rupture during impact has shown This paper describes two-dimensional flow research conducted very encouraging first results. The safety problems of reactors for air at Canadair to develop high lift system technology for advanced cushion vehicles are small compared to aircraft because of the lower STOL aircraft. First a theoretical method was developed which uses a speeds of travel and because they would travel on the surface of the
429 A7 1 -29938 earth and mainly over water. Nuclear powered air cushion vehicles A71-30055 # The flight test instrumentation installation for are, therefore, potentially much closer to practical application. A the Concorde SST. B. Roantree (British Aircraft Corp., Ltd., good economic performance potential for nuclear air cushion Fairford, England). In: Dynamic testing; Society of Environmental vehicles is predicted. G.R. Engineers, Symposium, Imperial College ofscience and Technology, London, England, January 5, 6, 1971, Proceedings. Volume 1. London, Society of Environmental Engineers, A71-29938 Aspects of air law and civil air policy in the 1971,p. 81-818. seventies. H. A. Wassenbergh (KLM - Royal Dutch Airlines, Shiphol Description of Concorde SST flight test equipment for measur- Airport, Netherlands). The Hague, Martinus Nijhoff, 1970. 176 p. ing a total of 3000 parameters tape-recorded continuously during a 295 refs. $7.55. complete flight with the aid of the Pulse Code Modulation recording General characteristics of the international civil aviation policy system backed up by FM tape decks, photographic paper records, and regulation, and the concepts of national versus international direct display pen recorders, and 450 visual instruments. The approach to civil aviation are first briefly outlined. Problems involved measured values include pressures, temperatures, stresses, angular and in the national control of the air traffic market, freedom traffic linear positions, and accelerations. The test equipment also includes classification, exchange of routes and traffic rights, route specifica- analog recording systems, an accident recording system, and a digital tions, and equal opportunity for carriers to compete are examined. replay system. Details on the Pulse Code Modulation System are The role of nonscheduled services in relation to scheduled services is given. V.Z. investigated, inclusive tour traffic and noninclusive tour charter traffic are compared, and traffic rights for charter carriers are considered. The growing need of cooperative arrangements between A71730068 * The response of a simply supported plate to air carriers is emphasized, and features of various agreements are 'N' waves at oblique incidence. A. Craggs (Alberta, University, dealt with. A short analysis is also presented of the 1970 U.S. Edmonton, Alberta, Canada). Journal of Sound and Vibration, vol. international civil aviation policy. O.H. 16, May 22. 1971, p. 293-307.5 refs. Grant No. NGR-52-025-003. A numerical method is used to compute the response of a simply supported plate to an 'N' wave arriving at oblique incidence. The factors influencing the response under these conditions are (1) A71-29944 # Helicopter designs (Konstruktsiia vetroletov). the ratio of thspulse duration to the fundamental period of the plate V. N. Dalin. Moscow, Izdatel'stvo Mashinostroenie, 1971. 275 p. 11 and (2) the convection forcing terms which are different for each refs. In Russian. mode..Also, asymmetric modes are excited, which do not make any This book contains a comprehensive coverage of modern contribution when the wave is at normal incidence to the plate. The helicopter technology including aerodynamic properties of these computed results show that both the convection terms and the aircraft, their power plants and engines, rotor, wing and rudder asymmetrical modes make a significant contribution to the form of designs, transmission and control systems, and manufacturing. the response for the displacements, velocities and accelerations, Particular attention is given to component weight, fatigue and cost though their effects are more dominant in the accelerations than for minimization and to strength analysis of the compmsnts working any other parameter. (Author) under variable loads. The book is written to assist students attending courses in helicopter design offered at schools for technicians in this field. V.Z. A71-30070 # Pressure-altitude assembly for high-altitude balloons. Oscar L. Cooper (National Center for Atmospheric Research, Boulder, Colo.). Facilities for Atmospheric Research, Dec. p. A71-30014 Map presentations for future ATC displays. G. 1970, 16-21. A full-range pressure-altitude transducer assembly is described R. Beaumont (Computing Devices of Canada, Ltd., Ottawa, Canada). that has been developed for use in high-altitude balloon flights. The CATCA Journal, vol. Spring p. 3, 1971, 16-19. transducer is of the capacitive type, using a thin taut-diaphragm The major points to be considered in the selection of a mapping sensing element positioned between two stationary capacitor plates. technique for use in future air traffic control (ATC) radar display The space between the diaphragm and one of the stationary plates is systems are outlined. Two techniques for presenting map informa- evacuated and sealed. The space on the other side of the diaphragm is tion on radar displays - i.e., the Vector Drawn Map (VDM) and the exposed to ambient pressure. The capacitances change as the Optically Projected Map (OPM) method - and the possibilities of absolute ambient pressure changes. A diode rectifier circuit detects their updating are considered. It is shown that for either method, a the Capacitor current and develops a dc voltage across a resistor. This similar amount of effort will be required to achieve an update. In the voltage is linear with pressure. The three transducers in the assembly VDM system, the update is essentially a computer program change which will generate a new map data list for storage in computer cover the full ambient range expected in balloon flights. M.V.E. memory. For the OPM system, the map update will be a cartographic change followed by a film generation cycle. The OPM system is A71-301 58 Aviation's place in transport; Royal Aeronauti- shown to offer significant advantages over the VDM system from the cal Society, Two Day Convention, London, England, May 12, 13, human factors viewpoint. The availability of bright colors, coupled 1971, Proceedings. London, Royal Aeronautical Society, 1971. 246 with the correct choice of color selection for various classes of data, P. can greatly enhance operator interpretation of a radar-map com- Among the subjects treated are areas of growth in,air transport, posite image. O.H. long haul air transport, V/STOL prospects for civil aviation, prospects for the development of air traffic in competition with other modes, and aviation within the total transport system. A71 -30053 Dynamic testing; Society of Environmental F.R.L. Engineers, Symposium, Imperial College of Science and Technology, London, England, January 5, 6, 1971, Proceedings. Volumes 1 & 2. A71-30159 # The total transport demand. Gabriel Bou- London, Society of Environmental Engineers, Vol. p.; 1971. 1, 125 ladon. In: Aviation's place in transport; Royal Aeronautical Society, vol. 2, 140 p. Price of two volumes, $19.20. Two Day Convention, London, England, May 12, 13, 1971, Various theoretical, technological and practical aspects, in- Froceedings. London, Royal Aeronautical cluding impedance testing, flight instrumentation for Concorde, and Society, p. vibration data analysis. 1971. 11 Examination of the possibility that transport and travel demand V.Z. will become a future economic constant, such as housing, clothing,
430 A71 -30227 and food. It appears that in the USA transport consumption in miles A71-30164 # Prospects for the development of air traffic in per capita doubles every 24 years. The rate of travel expansion is competition with other modes. J. R. Collingbourne. In: Aviation's even greater in Europe and Japan. The basic motivations for travel place in transport; Royal Aeronautical Society, Two Day Conven- are psychological, sociological, and economic. A progressive price tion, London, England, May 12, 13, 1971, Proceedings. increase in air transport of around 15% over the next 12 years may London, Royal Aeronautical Society, 1971. 19 p. be expected, dqe to the fight against pollution and other problems. Review of evidence concerning the division of travellers among F.R.L. various modes of travel, followed by examination of the way scheduled passenger air transport has progressed in competition with other modes in the U.S. Attention is drawn to certain features A71-30160 # Areas of growth in air transport. M. E. L. considered to be of general application and indicative of tuture Spanyol (Hawker Siddeley Aviation, Ltd., Kingston-on-Thames, trends. Some estimates of the sensitivity of the demand for a VTOL Surrey, England). In: Aviation's place in transport; Royal Aero- service are presented. It is considered that the long term prospects nautical Society, Two Day Convention, Loudon, England, May 12, for the growth of air travel are intrinsically good because an effect of 13, 1971, Proceedings. London, Royal Aero- increasing affluence is that people tend to take more and longer trips. F.R.L. nautical Society, 1971. 19 p. Examination of the circumstances leading to growth in the different sectors of air transport. The mechanisms which generate A71-30165 # Aviation within the total transport system. traffic are outlined. Since scheduled air transport services are geared Keith Legg (Loughborough University of Technology, Lough- primarily to the requirements of the major urban communities, and borough, Leics., England). In: Aviation's place in transport; Royal urban populations travel more frequently than rural populations, it is Aeronautical Society, Two Day Convention, London, England, May considered more realistic to relate air traffic to urban populations 12, 13, 1971, Proceedings. London, Royal than total populations. The cost and value of air transport, the Aeronautical Society, 1971. 22 p. 13 refs. capital requirement of aviation, business and leisure air travel, Consideration of the broad transport issues that follow from corporate aviation, and future developments are discussed. F.R.L. detailed study of transport demand, communications and future air transport prospects, because it is here that the greatest difficulty seems to be encountered in making good decisions. It is suggested A71-30161 # Future prospects for air transport - Long haul that transport policy, organization and decision must be coordinated air transport. C. H. Jackson. In: Aviation's place in transport; Royal and originate from the highest level within 'a framework of Aeronautical Society, Two Day Convention, London, England, May systematic overall studies which define the constraints and resource 12, 13, 1971, Proceedings. London, Royal limitations within which the total transport system must operate. It Aeronautical Society, 1971. 14 p. is emphasized that the purpose of transport is to satisfy social Consideration of long haul air transport, which is essential to demand and it must do this with the minimum of inconvenience to international affairs and commerce. Annual growth rates ranging the nonuser. F.R.L. according to area from 11 to 14% during the next 15 years, and from 7 to 10% thereafter are anticipated. The distribution of growth shows increases of average journey length, with eventually only A71-30200 Sonic-boom analog for investigating indoor about one third of the total traffic being over journeys of 3000 *? acoustical waves. Sui Lin (Toronto, University, Toronto, Canada). 5000 mi. In general, the development prospect seems to be of Acoustical Society of America, Journal, vol. 49, May 1971, pt. 1, p. continuing and painstaking effort to enable long haul operators to do 1386-1392. 7 refs. Research supported by the National Research what they are now doing in air transport, but on a bigger scale, mo-e Council of Canada. efficiently, and more acceptably to the public at large. F.R.L. Acoustical waves induced by sonic Dooms in a room with an open window are investigated by using an electrical analog. The good agreement between the results from the electrical analog and those of A71-30162 # V-STOL - Prospects for civil aviation. J. T. Vaidya shows that the electrical analog is a suitable device for Stamper (Hawker Siddeley Aviation, Ltd., Kingston-on-Thames, investigating the room response to sonic booms. (Author) Surrey, England). In: Aviation's place in transport; Royal Aero- nautical Society, Two Day Convention, London, England, May 12, 13, 1971, Proceedings. London, Royal Aero- A71-30218 # Universal squations of the laminar boundary nautical Society, 1971. 43 p. layer on a rotating wing (Universal'nye uravneniia laminarnogo Reappraisal of what the customer, as exemplified by the pogranichnogo sloia na vrashchaiushchemsia kryle). V. V. operator, the passenger and the community, needs and expects from Bogdanova. Akademiia Nauk SSSR, lzvestiia, Mekhanika Zhidkosti i the aircraft industry. Customer needs are classified under the major Gaza, Mar.-Apr. 1971, p. 84-93. 8 refs. In Russian. headings of convenience, regularity, comfort, safety, community The motion of an incompressible fluid in the boundary layer on acceptance, low total cost, and flexibility. A number of the more a blade rotating uniformly about an axis perpendicular to the wing promising types of STOL and V/STOL aircraft are briefly described, span is analyzed. A solution is obtained by a parametric method and various configurations are presented. F.R.L. involving the introduction of the series in parameters that are functions of the boundary layer. A corresponding system of universal equations is derived and is integrated over a wide range of A71-30163 A B.A.C. view of VJS.T.0.L. John H. Quick # parameters. The influence of rotation on boundary layer separation (British Aircraft Corp., Ltd., Weybridge, Surrey, England). In: and other boundary layer characteristics is determined. V.P. Aviation's place in transport; Royal Aeronautical Society, Two Day Convention, London, England, May 12, 13, 1971, Proceedings. London, Royal Aeronautical Society, 1971. 58 A71-30227 ,! Motion of a viscous gas in sectorial gas P. bearings (Dvizhenie viazkogo gaza v sektornykh gazovykh podshipni- Results of an extensive comparative study of VTOL and STOL kakh). B. S. Grigor'ev. Akademiia Nauk SSSR, lzvestiia, Mekhanika aircraft. It is concluded that the STOL loses out on site area, but not Zhidkostii Gaza, Mar.-Apr. 1971. p. 167-171. 5 refs. In Russian. by a sufficient margin to be decisive. The STOL is much less costly, Investigation of the influence of clearance changes with time on and is at least equal to and possibly better than the VTOL on the the aerodynamic characteristics of a gas journal bearing where one of basis of noise production. It should also produce less toxic gas, and is the surfaces is divided by axial grooves into a number of sectors. The capable of being developed more quickly than the VTOL. F.R.L. groove widths are large in comparison with the clearance, and the
43 1 A71 -30239 surface between each groove has a characteristic profile. If the UV radiation emitted by a fire to detect engine combustion chamber rotating surface is the one that is grooved and profiled, the clearance flame burn through. An automatic extinguisher is used, and a fuel is time dependent, and the problem is nonstationary. When the fixed tank vent pipe ignition protection system is provided. Operation of surface is grooved and profiled, the clearance is independent of time, the system is only achieved if light in the wave band of 0.3 to 1.1 and the corresponding problem is stationary. A method is described microns passes in front of the detector's silicon cell. G.R. for calculating the aerodynamic lift and drag coefficients of such bearings. The problem is studied in a two-dimensional approxima- tion. and a sinusoidal surface profile is assumed T.M. A71-30301 # The Westland WG.13 Lynx. Aircraft Engineer- ing, vol. 43, May 1971, p. 32-36. The WG.13 is a high performance helicopter, the general A71-30239 # DClO airplane characteristics for airport plan- purpose version of which operates at a maximum all up weight of ning. Long Beach, Calif., Douglas Aircraft Co., 1971. 180 p. 8000 Ib. It is powered by two Rolls-Royce BS.360.07.26 free DC-IO airplane specifications required by airport operators, turbines, which are mounted side by side, behind the main rotor and airlines, and engineering consultant organizations for general airport on top of the fuselage upper decking. Conformal gears are employed planning information. Tables, graphs, and drawings illustrate general in the highly loaded output stage of the main gearbox and transmit dimensions, ground clearances, interior arrangements, access clear- the engine power to a four-bladed semirigid main rotor and a ances, payload-range characteristics, akeoff and landing distances, four-bladed tail rotor. The main rotor blades are constructed of ground maneuvering space requirements, and parking requirements. stainless steel, aluminum honeycomb, and glass reinforced plastic. Terminal servicing requirements, ground servicing connections, G.R. towing specifications, and ground pneumatic power needs are described, along with jet engine exhaust velocities, temperatures, and noise characteristics in terminal operating conditions. Pavement data A71-30302 The major development trends in air transport include footprint diagrams, maximum pavement loads, landing gear and European co-operation. H. Ziegler (SociBtB Nationale lndustrielle loading characteristics on pavement, and flexible and rigid pavement ABrospatiale. Paris, France). Aeronautical Journal, vol. 75, May requirements according to different design procedures. T.M. 1971, p. 309-319. Characteristics and aspects of air transport in the coming years are examined. Air transport will be used more and more. both for passengers and freight, and the major trends are increased speed and A71-30264 # Approximate method of calculating the aero- capacity, development of STOL aircraft, and a third level transport dynamic characteristics of a wing in the presence of a cylindrical serving small urban communities. The necessity of uniting the efforts body (Priblizhennyi metod rascheta aerodinamicheskikh kharak- of manufacturers and of a close European cooperation is emphasized. teristik kryla v prisutstvii tsilindricheskogotela). V. A. Graivoronskii. O.H. Samoletostroenie i Tekhnika Vozdushnogo Flora, no. 23, 1970, p. 3-8. In Russian. The attached steady flow of an ideal incompressible fluid past a low-aspect-ratiowing mounted on a cylindrical body is analyzed in a A71-30303 The progress and economics of the aero- linear formulation of the problem. The wing is assumed to be slender engine. M. Garnier (SNECMA, Paris, France). Aeronautical Journal, and slightly warped, and its surface to be located -lose to the vol. 75, May 1971, p. 320-326. meridional plane. The wing is simulated by a system of horseshoe Some of the outstanding features of technical progress in jet vortices, the free vortices trailing off at a certain angle to the plane of engines over the past 25 years are reviewed, and future prospects are the wing chord. The cylindrical body is simulated by plane dipole briefly outlined. Possible ways of limiting the steadily increasing cost with a vortex system obtained by mapping the wing vortices onto the of engines, which represent about 30% of that of aircraft, are cylinder. The direction of the free vortices is determined from the examined. Some examples of progress beneficial to the economics of local velocities at points behind the wing, while the intensity of the aircraft industry are prasented. O.H. Vortices is determined from the boundary conditions at certain points behind the wing. V.P. A71-30305 Some measured and calculated effects of runway unevenness on a supersonic transport aircraft. C. G. B. A71-30267 # Differential method of manufacturing com- Mitchell (Royal Aircraft Establishment, Farnborough, Hants., plex precision fuselage parts (Differentsial'nyi metod proizvodstva England). Aeronautical Journal, vol. 75, May 1971, p. 339-343. 9 slozhnykh pretsizionnykh korpusnykh detalei). V. la. Nevriuev and refs. 0. G. Korol'. Samoletostroenie iTekhnika Vozdushnogo Flora, no. Possible problems due to taxiing vibration on uneven runways 23, 1970, p. 34-37. In Russian. are discussed. Two available methods of calculation of taxiing A method, based on. the principles of group technology, is vibration are described and their accuracy is tested. The effect of proposed which makes it possible, by way of differentiation, to landing gear on taxiing vibration is examined. O.H. increase the dimensions of complex structural parts even during the test-and-trial production phase..The method is based on subdividing classes of parts into elements, and selecting such groups of elements A71-30308 Fluidic cabin pressure control systems for for which development and group production poses no problems. military and civil aircraft. 0. D. Furlong (Normalair-Garrett, Ltd., V.P. Yeovil, Somerset, England). Aeronautical Journal, vol. 75, May 1971, p. 361-374. Research supported by the Ministry. of Aviation PPlV . The design, operation, and performance features of two new A71-30300 # Concorde power plant fire protection system. pneumatic systems developed to control cabin pressure automatically R. A. Davis (Graviner /Colnbrook/, Ltd., Slough, Bucks., England). by throttling the outflow of the cabin conditioning air are discussed Aircraft Engineering, vol: 43, May 197 1, p. 26-30. in detail. Both the systems are characterized by extensively em- The prototype Concorde is fitted with a Graviner high tempera- ploying - for the first time with this type of equipment - low-cost and ture Firewire Triple F.D. continuous element system for fire robust integratedfluidic circuits. O.H. detection, and a similar medium-temperature system for engine bay overheat detection. On preproduction and production aircraft to comply with airworthiness requirements, these detection systems A71 -30309 Instrument Society of America, International have been augmented by a new Graviner optical system that uses the Aerospace Instrumentation Symposium, 17th, Las Vegas, Nev., May
43 2 A71 -30323
10-12, 1971, Proceedings. Edited by B. Washburn (California, Data obtained on a new Airborne Integrated Data System during University. Los Alamos, N. Mex.). Pittsburgh, Instrument Society of flight testing of commercial aircraft are producing meaningful results. America (Instrumentation in the Aerospace Industry. Volume 17), This report describes the capabilities of the system and traces the 1971. 391 p. $17.50. development program from receipt of equipment to its use on the The papers depict the application of aerospace instrumentation aircraft. The system is modularly constructed in 400-channel units technology to environmental problems, aercspace computer applica- and is capable of handling a variety of inputs in the range of 5 tions, in-flight instrumentation, engine testing, optical instrumenta- millivolts to 30 volts, with a separate amplifier for each channel. tion, wind tunnels, telemetry as related to integrated avionics and On-board monitoring includes time-of-day, decimal displays, and bar technology end applications, surface vehicle instrumentation, data chart displays. The airborne system is complemented by a telemetry- processing and display, and advances in measurement techniques and microwave link and a ground-based station having an on-line measurement devices. computer and displaying real-time graphic displays. (Author) F.R.L.
A71 -30320 'Safe Weigh' - An accurate and economical on A71-30311 * Airborne data acquisition system for atmo- board weighing system. S. B. Moore (Vought Aeronautics Corp., spheric and meteorological research. Michael R. Smith (Mississippi Dallas, Tex.). In: Instrument Society of America, International State University, State College, Miss.) and Richard A. Johnson Aerospace Instrumentation Symposium, 17th. Las Vegas, Nev., May (Mississippi State University, NASA Mississippi Test Facility, Bay St. 10-12, 1971, Proceedings. Edited by B. Louis, Miss.). In: Instrument Society of America, International Washburn. Pittsburgh, Instrument Society of America (Instrumenta- Aerospace Instrumentation Symposium, 17th. Las Vegas, Nev., May tion in the Aerospace Industry. Volume 17). 1971, p. 75-79. 10.12, 1971, Proceedings. Edited by B. An 'On Board' weighing system has been designed and proto- Washburn. Pittsburgh, Instrument Society of America (Instrumen- typed to determine the gross weight and center of gravity location of tation in the Aerospace Industry. Volume 17), 1971, p. 15-21. Grant a light helicopter. The'system consists of load sensors, basic electrical NO. NGL-25-001-32. circuitry, and visual indicators. The system components are described This paper presents the efforts of researchers at Mississippi State with particular emphasis on the unique sensor design and the total University to utilize space-age technology in the development of a simplicity of the system. Operational performance of the prototype self-contained, airborne data acquisition system for use in atmo- system is presented. Applications of the system to fixed wing aircraft spheric and meteorological studies. The compact, lightweight air- are cited and benefits of increased efficiency and safety are borne data acquisition system (ADAS) is capable of recording highlighted. (Author) variables or transmitting eighteen variables in its present configura- tion and is suitable for use in a single-engine aircraft. Utilizing both an on-board analog recorder and a telemetry system for data A71-30321 High frequency rake probes for inflight intake acquisition, the prototype system has undergone extensive bench and airflow distortion measurements. Amnon Brosh and John C. Kicks flight testing at the MSU-MTF Research Center at the NASA (Kulite Semiconductor Products, Inc., Ridgefield, N.J.). In: In- Mississippi Test Facility. The prototype system has been utilized in strument Society of America, International Aerospace Instrumenta- several environmental science investigations associated with atmo- spheric diffusion processes and weather modification. (Author) tion Symposium, 17th, Las Vegas, Nev., May 10.12, 1971, Proceed- ings. Edited by B. Washburn. Pittsburgh, In- strument Society .of America (Instrumentation in the Aerospace Industry. Volume 17). 1971, p. 80-86. 10 refs. A71 -30318 Realtime graphic flight test becomes a reality. The forthcoming application is discussed of the ultraminiature L. D. Crowley (Douglas Aircraft Co., Long Beach, Calif.). In: integrated sensor (IS) of the newly developed 'E' type, with Instrument Society of America, lnrernational Aerospace Instrumen- high-temperature capability, to a family of high-frequency rake tation Symposium, 17th. Las Vegas, Nev., May 10-12, 1971, probes to be used in the intakes of high-performance airplanes. It is Proceedings. Edited hy B. Washburn. Pittsburgh, shown how solutions to severe problems associated with high Instrument Society of America (Instrumentation in the Aerospace temperature flight operations may be obtained from such IS Industry. Volume 17), 1971, p. 61-68. applications. E-type IS calibration qualification testing and ground An integrated Flight Test Data System has been developed tests are in progress now. .M.V.E. which combines a digital airborne acquisition/recording system with a telemetry/microwave link to a computerized ground station A71-30322 Altimeter-airspeed and Mach number trans- featuring the latest cathode ray tube graphic display units. Data are ducers. Sidney Herman and Stephen A. Hluchan (Bourns, Inc., processed in realtime via the telemetry link and postflight via the airborne recorded data tapes. Flight test engineers control data Riverside, Calif.). In: Instrument Society of America, International Aerospace Instrumentation Symposium. 17th. Las Vegas, Nev., May processing via special keyboards permitting them to output finished time plots or tabulations of data. Although many problems were 10-12, 1971, Proceedings. Edited by B. Washburn. Pittsburgh, Instrument Society of America (Instrumenta- encountered during the design, development, and implementation phases, the data system has been operational since the first flight of tion in the Aerospace Industry. Volume 17). 1971, p. 87-95. the DC-IO aircraft and is presently in use on four aircraft involved in An improved pressure transducer is described that is constructed developmental and FAA certification test programs. The per- around a unique diaphragm design which accepts nonlinear pressure formance of this new system has permitted DC-10 test programs to inputs and provides an electrical potentiometer output linear with remain on or ahead of schedule and has gained widespread the desired variable. It consists of a diaphragm pressure sensor, a acceptance among flight crew, engineering, and administrative beam wiper actuator, and a continuous resolution potentiometric Dersonnel. (Author) output element. The convolution. design of the diaphragm sensor permits responses in an inverse relation to nonlinear inputs with a subsequently normalized element output. Inputs with slope devia- A71-3031 9 Airborne Integrated Data System. D. D. tions as great as 30:l have been compensated for by combinations of Crompton (Douglas Aircraft Go., Long Beach, Calif.). In: Instrument mechanical and electrical devices and methods. This unique, patent- Society of America, International Aerospace Instrumentation applied design results in inherent compensation for temperature and Symposium, 17th. Las Vegas, Nev., May 10-12, 1971 Proceedings. vibration effects. (Author) Edited by B. Washburn. Pittsburgh, Instrument Society of America (Instrumentation in the Aerospace Industry. A71 -30323 Atmospheric temperature deviations from the Volume 17). 1971, p. 69-74. International Standard and its effect on barometric altimeters. Peter
433 A71 -30324
Holman Smith (Boeing Co., Seattle, Wash.). In: Instrument Society Symposium, 17th. Las Vegas. Nev., May 10.12. 1971, Proceedings. of America, International Aerospace Instrumentation Symposium, Edited by B. Washburn. Pittsburgh, Instrument 17th. Las Vegas, Nev., May 10-12, 1971, Proceedings Society of America (Instrumentation in the Aerospace Industry. Edited by B. Washburn. Pittsburgh, Instrument Volume 17), 1971.p. 131-134. Society of America (Instrumentation in the Aerospace Industry. This paper describes a low cost, simply operated system for Volume 17). 1971, p. 96-102. 8 refs. evaluation of the condition of an aircraft engine. The self-contained This paper describes airplane altimeter errors caused by atmo- portable unit connected to engine mounted sensors automatically spheric temperature deviations from the International Standard computes critical engine characteristics and compares them to Atmosphere and suggests a system design to substantially reduce absolute limits prestored as a function of corrected speed. Character- them. In particular, the problem of providing accurate height values 'istics are also compared with values from previous tests to detect for airplanes on approaches and at cruise altitudes in horizontal abnormal trends. Current values of characteristics are displayed and temperature gradients is discussed. A schematic diagram of a then punched on a card for use as reference in subsequent tests. servo-operated altimeter with an integral temperature correction (Author) circuit is described. The method of correction is shown to be derived from a comparison between the actual Static Air Temperature (SAT) A71-30329 Holography and optical data processing in and the theoretical temperature value associated with the apparent aerospace instrumentation. Otto M. Friedrich, Jr. and Arwin A. altitude derived from the static pressure value sensed by the air data Dougal (Texas. University, Austin, Tex.). In: Instrument Society of computer. Other atmospheric variables and the means by which they America, International Aerospace Instrumentation Symposium, are accounted for in existing altimetry are briefly described. The 17th. Las Vegas, Nev., May 10-12, 1971, Proceedings. basic equation for the tropospheric pressure-height relationship is Edited by B. Washburn. Pittsburgh, Instrument quoted so as to demonstrate its dependence upon a standard Society of America (Instrumentation in the Aerospace Industry. temperature gradient. The appendix shows how curves of altimeter Volume 17), 1971, p. 141-153. 44 refs. Research supported by the reading errors versus true altitude for temperature deviations were Joint Services Electronics Program and the Texas Atomic Energy derived. Reference is made to an automatic temperature and pressure Research Foundation. data transmission system that could continuously correct airplane Recently developed holographic techniques, optical data pro- altimeters according to values detected at the touch-down point. cessing principles, and laser properties beneficial for aerospace (Author) instrumentation are reviewed. High intensity, highly collimated or directional, spatial- and temporal-coherentoptical beams are readily generated with present laser systems. In optical holography, both the A71-30324 The design and fabrication of transducers for phase- and the amplitude of optical waves are recorded as intensity the measurement of fluctuating pressures from DC to over 100 KHz variations that are produced by the interference of two or more in jet engine testing. Anthony D. Kurtz (Kulite Semiconductor optical waves. Optical data processors usually employ the optical Products, Inc., Ridgefield, N.J.). In: Instrument Society of America, diffraction produced by a simple lens. The ability of an optical lens International Aerospace Instrumentation Symposium, 17th, Las to perform two-dimensional Fourier transforms at the speed of light Vegas, Nev., May 10-12. 1971, Proceedings. is an advantage which optical processors have over conventional Edited by B. Washburn. Pittsburgh, Instrument Sociew of America electronic systems. Experimental and analytical investigations are (Instrumentation in the Aerospace Industry. Volume 171, 1971, p. being performed on several holographic techniques and on the 103-116. following optical data processing systems: optical analyzers, filters, This paper will deal with the design consideration= . volved in signal correlators, pattern recognition units, analog computers and making miniature pressure transducers in a wide variety of dimen- simulators. (Author) sions and configurations for jet engine testing. Attention will be given to solid state fabrication considerations as the diaphragm diameter is changed from ,200 in. to ,030 in. In particular, frequency A71-30333 * The dynamic characteristics of a five com- response, power dissipation, voltage capability, strain level, output ponent oscillating balance. Ping Tcheng (Old Dominion University, and compensation for thermal effects will be discussed. (Author) Norfolk, Va.). In: Instrument Society of America, International Aerospace Instrumentation Symposium, 17th. Las Vegas, Nev., May 10-12, 1971. Proceedings. Edited by 8. A71-30325 Fluctuating pressure measurements from DC Washburn. Pittsburgh, Instrument Society of America (Instrumenta- to over 100 KHz in jet engine testing. John E. Fischer (General tion in the Aerospace Industry. Volume 17). 1971, p. 184-190. Electric Co., Evendale, Ohio). In: Instrument Society of America, Contract No. NAS 1-9434. International Aerospace Instrumentation Symposium, I7th. Las The dynamic characteristics of a five-component strain-gaged Vegas, Nev., May 10-12, 1971, Proceedings. oscillating balance used in wind-tunnel stability testing are presented. Edited by B. Washburn. Pittsburgh, Instrument Society of America An experimental investigation was performed to determine the (Instrumentation in the Aerospace Industry. Volume 17), 1971, p. frequency response of the balance. The results indicated that the 117-1 23. 44 refs. balance response is like that of a multidegree-of-freedomvibrational Fluctuating pressure measurements have become a very impor- system. It was found that the interactions and the component tant and necessary tool in the development of advanced design jet sensitivities are frequency dependent. Peak interactions were general- engines at General Electric. Current miniature transducers used with ly found to be one order of magnitude larger than the corresponding very sophisticated calibration and data acquisition equipment cover static values at the natural frequencies of the system. In view of this an extremely wide range of frequencies and pressure levels. System finding it becomes apparent that the dynamic nature of the balance design, calibration and limitations are discussed and typical applica- should be considered in reducing dynamic stability data. (Author) tions are shown. In most applications measurement accuracy is now limited by errors introduced by interference effects from probes or rakes required for support and mechanical integrity in contrast to the A71-30334 Application of a digital computer to the limits which have been imposed by transducer capabilities in the closed-loop control of a wind tunnel model trajectory simulation past. (Author) system. J. A. Wolfe (Vought Aeronautics Corp., Dallas, Tex.). In: Instrument Society of America, International Aerospace Instrumen- tation Symposium, 17th. Las Vegas, Nev., May 10-12, 1971, A71 -30327 GOINO-GO engine tester. John F. Moran and Proceedings. Edited by B. Washburn. Pittsburgh, Harris P. Shay (General Electric Co., Utica, N.Y.). In: Instrument Instrument Society of America (Instrumentation in the Aerospace Society of America, International Aerospace Instrumentation Industry. Volume 17). 1971, p. 191-201.
434 A7 1-30398
A wind tunnel testing system, which obtains the motion of an A71-30383 # The MADAP air traffic control system as seen aerodynamic body by moving a sting supported model in response to by Eurosystem. Eurocontrol, vol. 3, no. 2, 1970, p. 23-29. the aerodynamic loads acting upon it is in use at the LTV High Speed Translation. Wind Tunnel. The instrumentation, system servo controls, and the Description of the Maastricht Automatic Data Processing and closed loop operating feature which includes a digital computer to Display System (MADAP) which employs eight digital computers solve the equations of motion are presented. Testing procedures, and is intended to facilitate the task of controlling aircraft in the operating experience, and system accuracy are discussed. (Author) upper air space of the Benelux countries and West Germany. The system aids the controller in this task of issuing instructions by relieving him of the effort involved in memorizing all factors of the air traffic situation; by presenting him with synthetic data enabling A71-30337 Sensing and communications technologies for him to make decisions swiftly and efficiently; and by warning him in wayside headway control systems. Gerald P. Esmer (Bendix Corp., advance of decisions that must be taken. There is no communication Ann Arbor, Mich.). In: Instrument Society of America, International of a digita! nature between MADAP and the aircraft being controlled, Aerospace Instrumentation Symposium, 17th. Las Vegas, Nev., May thus the controller remains the master link in the chain. F.R.L. 10-12. 1971, Proceedings. Edited by B. Washburn. Pittsburgh, Instrument Society of America (Instrumenta- tion in the Aerospace Industry. Volume 17). 1971, p. 255-270. 9 A71-30394 A note on the optimum averaging time of refs. wind information for conventional aircraft landings. W. R. Sparks The current status of sensors suitable for determining headway - and Barbara Keddie. Meteorological Magazine, vol. 100, May 1971, Le., the separation in time between two vehicles traveling on a p. 129-134. guideway - was surveyed with interest focused on short headways of Anemometer measurements are averaged over a certain time 10 to 500 ft. Technologies surveyed for applicable hardware included interval, and the resulting average wind speed for this interval is used rapid railroad traffic control, industrial control, and military and to estimate the average wind speedfar zQme future period of 4 to 5 aerospace instrumentation. Communication techniques and equip- sec just before touchdown when the aircraft is descending from ment applicable to personal rapid transit systems were also surveyed. about 30 to 15 m. During this period, the aircraft would travel about Modulation techniques investigated included: amplitude modulation, 300 m. An attempt is made to evaluate the optimal averaging time frequency shift keying, and phase modulation. Tone signaling was for the anemometer measurements from the viewpoint of ensuring also studied. Coding techniques were evaluated for personal transit maximum accuracy of the extrapolated average wind speed value for systems, with a burst noise model assumed. The use of open wire, the 300-m run. From a detailed analysis of wind measured by a single twisted pair, and coaxial cable for near term personal rapid transit anemometer 10 m above open level ground and by consideration of applications was studied and the limits of applicability of each Shiotani's (1966) observations with a horizontal array of anemom- determined. The limits of applicability of baseband data transmission eters, it is concluded that the optimal averaging time for wind were also reviewed, and modems for modulated data transmissions measured by a single anemometer should not be less than four were surveyed. O.H. minutes. T.M.
A71-30395 Some aspects of wind information required in the landing of aircraft. Barbara Keddie. MeteorologicalMagazine, vol. A71 -30341 MODAPS - Advanced instrumentation -71 100, May 1971, p. 134-143. 5 refs. automated modal vibration testing. Ronald W. Budd (Hughes Single-anemometer wind measurements were made each second Aircraft Co., El Segundo, Calif.). In: Instrument Society of America, over a period of about one hour for six independent wind regimes. A International Aerospace Instrumentation Symposium, 17th. Las detailed analysis was made of the maximum difference between a Vegas. Nev., May 10-12, 1971, Proceedings. mean wind speed U(t) measured over 4.5 min and the mean wind Edited by B. Washburn. Pittsburgh, Instrument Society of America speed U(300) occurring 10 min later over a period during which the (Instrumentation in the Aerospace Industry. Volume 17). 1971, p. aircraft descends from 30 to 15 m and travels a distance of 300 m. 327-338. 7 refs. The maximum value of U(300)-U(t) in various samples of sizes from The design, capabilities, and utilization of MODAPS, a system 4 to 20 min was predicted by assuming a normal distribution. designed to provide real-time engineering unit data to be used for Theoretical curves were derived which were in reasonable agreement timely decisions on mode acceptability and purity, are described. with curves drawn from the analyzed data. Comparisons were also This includes engineering unit data, mode shape data, generalized made between the actual and predicted values of (1) the maximum mass term data, orthogonality check data, and orthographic view deviation of U(300)-U(t) from the mean in various samples, and (2) plots. The system comprises analog subsystems, digital interfaces, the maximum difference in various samples. Finally, data from and an on-line miniature computer. It has a frequency response of different sampling periods or runs of wind were compared so that if 0.75 to 800 Hz and a dynamic range of 80 dtc. The system provides the maximum departure of one sample from the mean wind was more modes per day and more accurate data than was previously known the maximum departure for other samples could be esti- possible. A typical modal test is described and the advantages of mated. T.M. using an automated approach are discussed. O.H. A71-30398 # Computer aided design of civil transport plane. Jiro Kondo (Tokyo, University, Tokyo, Japan). Japan Society for A71-30382 # Air traffic control and data processing in Aeronautical and Space Sciences, Transactions, vol. 13, no. 23, 1970, France. J. Villiers and J. F. Vivier. Eurocontrol, vol. 3, no. 2, 1970, p. 37-46. 8 refs. p. 16-22. Translation. Discussion of CAD (Computer Aided Design), a program by Review of the basic ideas behind the installation of automatic which it is possible to conduct a fundamental design of an aircraft data processing equipment for the use of the French ATC services. meeting such specifications as number of passenger seats, maximum The use of computers to process the large volume of flight plan data range, maximum cruising speed, and takeoff or landing run. It can makes it possible to compensate for the limited processing capacity also take account of future technical advances. Airframe configura- resulting from the badly coordinated intellectual activi'ty of a team tion, aerodynamic performance, propulsion systems, weight, cost of of air traffic controllers. For the development of the French system construction, operating cost, and other capabilities are automatically experiments were conducted under conditions to be found in an obtained. In order to determine the accuracy of CAD, it was applied actual ATC environment. Details of methods and implementation are to civil transport aircraft of known specifications. Except for a rather presentcd, and variations of the CAUTRA (Automatic Traffic large discrepancy in field length, agreement of CAD results with the Coordinator) systems are described. F.R.L. specification of actual aircraft is satisfactory. F.R.L.
435 A71 -30420
A71730420 V-12 has civil, military missions. Donald C. lngknieurs et Techniciens de I'Adronautique et de /'€space and Winston. Aviation Week and Space Technology, vol. 94, June 7, Groupernent des Acousticiens de Langue Franpise, Colloque 1971, p. 14-19. d'Acoustique Adronautique, 2nd, Paris, France, May 4, .5, 1971, Description of the Soviet Mil V-12 heavy lift helicopter (88,000 Paper. 19 p. 7 refs. In French. Ib maximum payload), which is powered with four turbme engines Measurements of nonstationary pressures have been made at rated at 6500 shp each. The side-by-side rotor configuration is ONERA inside turbomachines by means of compact capacitive considered to offer the greatest stability and reliability. The two detectors. The characteristics of the pressure fields measured on rotors are cross-shafted, hence the V-12 can maintain flight on any stationary blades are compared with those of the sound field outside two engines. The cargo hold, entered by clamshells opening outward the machine in order to derive a first approximation of the location and upward, is more than 90 ft long. The civil missions of the V-12 of the noise sources. The characteristics of the space-time structure include transport of oil and gas equipment and pipe into isolated of the various vibrating modes in the duct in cylindrical coordinates areas, and supply of remote settlements north of the Arctic Circle. are studied. The propagation properties of the duct are derived and F.R.L. compared with theory. The measurements have been made partly in an experimental ONERA fan and then on a SNECMA compressor model. M.M. A71 -30443 Vortex theory for a propeller of constant aerodynamic pitch and study of the wake configuration with the aid of the smoke trail method (incompressible fluid) (Note sur la thborie A71-30518 # Experimental studies on absorbent materials tourbillonnaire de I'helice B pas abrodynamique constant et sur used in turboreactor ducts (Etudes experimentales sur les materiaux I'btude de la configuration du sillage d I'aide de la mbthode des film absorbants utilisbs dans les conduits de turboreacteurs). J.-P. Bernard de fumbe /fluide incompressible/). R. PBlissier (Aix-Marseille, Uni- (SNECMA, Paris, France). Association Franpise des Ingdnieurs et versit6, Marseille, France).Journalde Mkcanique, vol. 10, June 1971, Techniciens de I'Akronautique et de /'€space and Groupernent des p. 191-203.8 refs. In French. Acousticiens de Langue Francaise, Colloque d'Acoustique Adro- Approximate analytical expressions are derived for the pitch of nautique, 2nd, Paris, France, May 4,5,1971, Paper. 17 p. In French. vortex streets in the rotational plane of a propeller as a function of Resonators, as the only type of absorbing structures capable of the propeller's mode of operation and its geometrical characteristics. industrial utilization for the attenuation of sound produced by a Smoke-trail visualization of the pitch of vortex streets in the wake is turboreactor blower, have been investigated. A test installation in also described. The results are useful in studies of the pitch which the wall of an air duct situated between two reverberating distributions of vortex streets along the length of the blade and can chambers was clad with the absorbing structures was used for this be utilized for evaluation of the propeller's aerodynamic efficiency. purpose. Using this installation, the effects of the flow velocity, the T.M. characteristics of the absorbent structure, the transverse dimension of the dilct, and the cladding of two opposite surfaces of the duct were examined. Results are presented and compared with those A71-30454 The role of kinetics in engine emission of obtained using an experimental compressor, the ducts of which were nitric oxide. L. S. Caretto, L. J. Muzio, R. F. Sawyer, and E. S. lined with optimized absorbing structures taking into account the Starkman (California, University. Berkeley, Calif.). Combustion previously obtained parameters. A good agreement was achieved. Science and Technology, vol. 3, ncj. 2, Apr. 1971, p. 53-61. 27 refs. O.H. Research supported by the National Air Pollution CU, rol Admini- stration. The use of chemical kinetic calculations to predict the forma- A71-30519 # Noise measurements in the large Modane wind tion of nitric oxide in spark ignition engines and gas turbine tunnel (Mbsures de bruit dans la grande soufflerie de Modane). C. combustors is reviewed. Although the basic chemical kinetic mech- Broll (ONERA, Modane, Savoie, France). Association Franpise des anism is the same in both cases, differences in thermodynamics and lngknieurs et Techniciens de I'Adronautique et de /'€space and fluid mechanics account for different NO emission levels. In spark Groupernent des Acousticiens de Langue Francaise, Colloque ignition engines it is necessary to account for temperature gradients d'Acoustique Adronautique, 2nd, Paris, France, May 4, 5, 1971, in the engine. In gas turbines the NO kinetics are frozen before the Paper. 10 p. 5 refs. In French. (Author) NO is formed in equilibrium amouvts. Study of noise produced during a series of aerodynamic tests on a helicopter rotor. It was found that at frequencies below 2500 Hz the noise level of the rotor is greater by several dB than the noise A71-30473 French research on metallic matrix com- level of the wind tunnel and the driving motor. The results make it posites. Michel Sindzingre (Paris, Ecole Nationale Supbrieure des possible henceforward to correct rough measurements and to Mines, Corbeil-Essonnes, Essonne, France). (Deutsche Gesellschaft perform future acoustic tests on rotors and propellers under good fur Metallkunde, Tagung Verbundwerkstoffe, Konstanz, West conditions. F.R.L. Germany, Oct. 23, 1970.J Zeitschrift fur Metallkunde, vol. 62, May 1971, p. 365-371. 19 refs. The mechanical properties of composites consisting of an A71-30520 # Preliminary results in a study of the infrared aluminum matrix reinforced by boron fibers are presented. The emission of a hot jet (Rbsultats prbliminairesde 1'8tude de I'6mission experimental and control techniques used are described. The infrarouge d'un jet chaud). J.-F. de Belleval, M. Perulli (ONERA, different structures obtained by unidirectional eutectic solidification Chitillon-sous-Bagneux,Hauts-de-Seine, France), G. Richter, and C. of nickel and cobalt based alloys are shown. The resistance to tensile Schmidt (SNECMA, Paris, France). Association Francaise des deformation and creep of these alloys is reported. Finally some Ingdnieurs et Techniciens de I'Adronautique et de /'€space and investigations of new composite materials which are not reinforced Groupernent des Acousticiens de Langue Francaise, Colloque unidirectionally but rather isotropically within a plane are described. d'Acoustique Adronautique, 2nd, Paris, France, May 5, 1971, (Author) 4, Paper. 25 p. 9 refs. In French. IR and acoustic measurements were compared, and it was found A71-30517 # Use of miniaturized microphones in the study that the emissions of the electromagnetic and acoustic energies can of the sound radiation of vibrating modes in rotating machines be attributed to the same sources. On this basis, IR probing is used (Utilisation de microphone; miniaturisbs B I'btude du rayonnement for investigating the aerodynamic parameters of a hot jet. Crossed- sonore de modes vibratoires dans les machines tournantes). B. Baerd, beam IR measurements are made by means of two mirrors whose P. Harel, J. Lambourion, and M. Perulli (ONERA, Chbtillon-sous- axes are orthogonal to each other and perpendicular to the jet axis. Bagneux, Hauts-de-Seine, France). Association Francaise des The mirrors focus the IR emission from the jet onto lead sulfide IA
436 A71 -30529 detectors. The results obtained up to the present are discussed, and in the air (Verification experimentale et application d'une including axial and transverse profiles of the turbulence intensity and methode de calcul du spectre sonore des jets au sol et en vol). M. the axial profile and distribution of frequency. Z.W. Kobrynski (ONERA, Chitillon-sous-Bagneux, Hauts-de-Seine. France). Association Franqaise des lnginieurs et Techniciens de I'Aironautique et de I'Espace and Groupement des Acousticiens de Langue Francaise, Colloque d'Acoustique Aironautique, 2nd, Paris, A71-30521 # Determination of sound fields of aircraft in France, May4,5, 1971, Paper. 14 p. 9 refs. In French. flight by treatment of noise measurements (Determination des The work discussed is a continuation of an investigation by champs sonores des avions en vol par traitement des mesures de Kobrynski (1969). The sound pressure level at a point of the ground bruit). Jean Gaudron (SociBtB Nationale lndustrielle Aerospatiale, during the overflight of an aircraft is considered, and a mathematical Toulouse, France). Association Francaise des lnginieurs et Tech- relation for expressing the sound pressure level observed with niciens de I'Aironautique et de I'Espace and Groupement des satisfactory approximation is derived. The studies discussed are based Acousticiens de Langue Franqaise, Colloque d'Acoustique A&-0- partly on theoretical results reported by Ribner (1969) and partly on nautique, 2nd, Paris, France, May 4,5, 1971, Paper. 30 p. In French. experimental results. The method of calculations proposed utilizes a Study of the sound field attached to an aircraft, which involves new expression which is representativefor the directivity of jet noise. knowledge of the perceived noise level. Some test procedures The theoretical results are compared with experimental data, and the involving the flight path of the aircraft and the acquisition of flight areas of agreement are defined. G.R. parameters are described. Flight parameters to be controlled are the engine operating conditions and the speed of the aircraft. It is shown that the attitude of the aircraft is of importance in the production of A71-30526 Fluctuation of sound pressures created by a noise perceived on the ground. F.R.L. # fan in a very low speed subsonic wind tunnel test stream (0.10 less than V less than 20 mlsec) (Fluctuations de pressions sonores creees par un ventilateur dans une veine de soufflerie subsonique tres bases A71-30522 # Predictive calculations of attenuation of vitesses l0,lO less than V less than 20 mlsl). J. Moinard and C. absorbing ducts adaptable to bypass jet engines (Calculs de prevision Froger (Centre d'Etudes et Recherches des Charbonnages de France, d'attenuation de conduits absorbants adaptables B des reacteurs Verneuil-en-Halatte, Oise, France). Association Francaise des ln- double flux). F. Haffner (SociBtB Bertin et Cie., Plaisir, Yvelines, ginieurs et Techniciens de I'Aironautique et de I'Espace and France). Association Francaise des Inginieurs et Techniciens de Groupement des Acousticiens de Langue Franpise, Colloque I'Aironautique et de I'Espace and Groupement des Acousticiens de d'Acoustique Aironauiique, 2nd, Paris, France, May 4, 5, 1971, Langue Francaise, Colloque d'Acoustique Aironautique, 2nd, Paris, Paper. 21 p. In French. France, May 4,5, 1971, Paper. 31 p. In French. Discussion of anomalies which can cause large errors in the Classical Morse theory is used for calculating noise attenuation calibration of anemometers at very low wind speeds. The anomalies in the ducts of a compressor. According to this theory, a monochro- are due to a region of acoustic waves, the principal noise source being matic acoustic wave propagating in a duct is composed of a series of the fan which moves the air in the wind tunnel. To construct a high elementary waves called modes. In the case of sound-absorbingduct quality wind tunnel aerodynamic studies must be supplemented by walls, the modes are attenuated and their phase velocity is modified. acoustic studies which do not exclude adjustments on the full-scale Equations determining the attenuation of each mode are solved for model. F.R.L. rectangular, circular, and annular duct cross sections. Two hypo- theses are assumed for the energy distribution over different modes at the duct inlet: (1) energy is uniformly distributed over different A71-30527 Development progress . New transport modes, and (2) the propagating wave is a plane one. The theoretical engines: JTSD. G. P. Adamson (United Aircraft Corp., Pratt and and experimental results are compared for different materials and for Whitney Aircraft Div., East Hartford, Conn.). Society of Automotive rectangular duct cross sections. Z.W. Engineers, National Air Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710419. 12 p. Members, $1.00; nonmembers, $1.50. The means by which Pratt and Whitney Aircraft is bringing A71-30523 # Influence of the presence of a plane on the about improvements in its JT9D engine are described. The JT9D measurement of line-containing spectra (Influence de la presence engine, having accumulated a year and a half of commercial service, d'un plan sur la mesure de spectres contenant des raies). J. Jacques benefits both from a product improvement effort aimed at.develop- (CNRS, Centre de Recherches Physiques, Marseille, France) and P. ing fixes for current operating problems and from development work Thomas (SNECMA, Paris, France). Association Francaise des on advanced JT9D models designed to power future transport lnginieuts et Techniciens de I'Aironautique et de I'Espace and aircraft. An extended comparison between the current JT9D-3A Groupement des Acousticiens de Langue Franqaise, Colloque engine and the first advanced JT9D (the JT9D-7) illustrates the d'Acoustique Aironauiique, 2nd, Paris, France, May 4, 5, 1971, product improvement process in detail. (Author) Paper. 20 p. In French. Study of complex noise emission spectra resulting from the A71-30528 JTSD development for airline operation. G. E. superposition of a continuous component and peaks. Some ap- Woodger (United Aircraft Corp., Pratt and Whitney Aircraft Div., plicable theoretical expressions are established which make it East Hartford, Conn.). Society of Automotive Engineers, National possible to calculate the level separations due to the presence of a Air Transportation Meeting, Atlanta, Ga., May 70-13, 1971, Paper perfectly reflecting plane and relative to either all the spectrum, or to 710434. 13 p. Members, $1.00; nonmembers, $1.50. frequency bands corresponding to a chosen analytical mode. Experi- The Pratt and Whitney Aircraft JT9D engine is described, with mental confirmation was made in a soundproof room by measuring respect to the ways in which it has been designed to meet the the influence of reflection interfaces for the synthetic noise spectra requirements of airline operators. Chief emphasis is placed on the obtained either by means of electroacoustic sources or by use of a engine's simplicity of construction, provisions for condition moni- model jet and a compression chamber. The satisfactory agreement toring, and capability for maintenance, along with its improved noise between the theoretical and experimental results shows that the and smoke emission characteristics. Specific maintenance problems spectrum of a sound source in the presence of a perfectly reflecting and their solutions are presented. plane is predictable commencing with the knowledge of the free field (Author) spectrum. F.R.L. A71-30529 New developments in product support. H. A71-30524 # Experimental verification and application of a Bayer (Douglas Aircraft Co., Long Beach, Calif.) and J. Woodworth method of calculation for the sound spectrum of jets on the ground (National Airlines, Inc., Miami, Fla.). Society of Automotive
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Engineers, National Air Transportation Meeting, Atlanta, Ga., May 710448. 11 p. Members, $1.00; nonmembers, $1.50. 10-13, 1971, Paper 710437. 10 p. Members, $1.00; nonmembers, A new systems approach has been developed and applied to $1.50. achieve the inspection, diagnosis, and prognosis of gas turbine engine The use of maintenance cost data can be successfully employed health by electronic means. The approach combines the power of the as a design constraint for product support. This paper summarizes special purpose digital computer together with advanced engine fault the process used in translating quantitative maintenance cost isolation techniques to achieve a complete operational and main- requirements into specific design criteria. It describes the airline tenance interface. System elements are described and typical operator’s use of such data and how he then passes cost objectives on examples discussed. Practical applications of the system to several to the aircraft manufacturer. The various steps used in the design engine models have been made with favorable results. (Author) process are described from a manufacturer’s standpoint. Examples are given to show the relationship of cost to resulting maintainability improvements. Finally, the airline operator‘s viewpoint is presented A7130533 Area navigationsystems and displays. Frank F. which calls for more stringent compliance with previously deter- Wright, William R. Beckman (Lockheed-California Co., Burbank, mined maintenance concepts and procedures. The paper closes with a Calif.), and T. J. Newman (AMBAC Industries, Inc., Arma Div., look at future program requirements. (Author) Garden City, N.Y.). Society of Automotive Engineers, National Air Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710457, 20 p. Members, $1.00; nonmembers, $1.50. A71-30530 Powered wheels - A concept for parking and Description of different classes of area navigation systems taxiing of commercial transport airplanes. B. C. Hainline, 8. K. (RNAV), and review of the operational advantages of pilot displays. Sellereite, K. V. Swanke (Boeing Co., Commercial Airplane Group, The use of National Airspace System ground radio navigation aids by Renton, Wash.). Society of Automotive Engineers, National Air airborne navigation receivers and other sensors forms the basis for Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper the RNAV systems that, coupled with appropriate air traffic control 710446. 14 p. 8 refs. Members, $1.00; nonmembers, $1.50. techniques, promise to improve the movement of aircraft throughout are The concept of powered wheels as applied here is the propelling the national airspace. Three classes of RNAV equipment of an airplane on the ground by direct traction of landing gear wheels reviewed: the Mark I, simple yet requiring considerable pilot manual using onboard power and under direct control of the pilot. This operation; the Mark II, virtually automatic with new cyhode-ray tube multifunction/navigation displays for the pilot; and the Mark concept suggests an improvement in economic and ecologic factors Ill, based upon use of self-contained inertial navigation systems associated with ground operation of commercial transport airplanes. installed in today’s large jets. M.V.E. For the concept to be economically feasible, penalties for addition of airborne equipment must be overbalanced by savings in fuel, engine operating time, ground equipment, ground personnel, and terminal space and by increased airplane productivity. The use of direct wheel A71-36534 INS projections and improvements - Capabili- traction can improve the airport and terminal environment by ties in the future. Christopher L. Bearden (American Airlines, Inc., reducing air pollution, jet blast, and noise from main propulsion New York, N.Y.). Society of Automotive Engineers, National Air engines during taxi and parking. This paper is a preliminary look at Transportation Meeting, Atlanta, Ga., May le13, 1971, Paper requirements, configurations, and trades that require further in- 710458. 6 p. Members, $1.00; nonmembers, $1.50. vestigation to establish the role of powered wheels ip “iture air ARlNC 561 Inertial Navigation Systems (INS) have received transportation. (Author) wide acceptance in the Commercial Air Transport Industry. Many innovative improvements to these systems have been developed in recent years. Increased functional capability is planned for the near future such as vertical navigation and accuracy improvement using A7130531 Design integration - The key to effective engine condition monitoring. K. B. Kochanski and D. W. Leiby radio navigation aids. (Author) (General Electric Co., New York, N.Y.). Society of Automotive Engineers, National Air Transportation Meeting, Atlanta, Ga., May 10-13, 1971, Paper 710447. 12 p. Members, $1.00; nonmembers, A71-30535 The future of STOL. Richard D. FitzSimmons $1.50. and William E. Thurman (National Aeronautics and Space Council, As aircraft increase in size and required capital investment, the Washington, D.C.). Society of Automotive Engineers, National Air incentives for development and application of techniques and Transportation Meeting, Atlanta, Ga., May lel3, 1971, Paper methods for optimizing the availability of the aircraft become 710464. 6 p. Members, $1.00; nonmembers, $1.50. increasingly attractive. Currently, a family of techniques, which can Individual DOT, DOD, and NASA STOL roles and missions are be broadly defined as engine condition monitoring, is being applied discussed, including the supporting rationale that will allow the to reduce the downtime assignable to the aircraft power plant. The agencies to collectively address STOL systems implementation and mechanical health of the engine is assessed through such techniques create an environment in which the free enterprise system can as parameter monitoring, vibration analysis, oil monitoring, bore- assume its rightful role and provide a profitable, safe, environmental- scope inspection, and radiography to provide problem detection, ly satisfactory new air transportation service that is truly responsive isolation, and trend monitoring. The effectiveness of a condition to the desires of the public. It is felt that appropriate involvement of monitoring system depends upon the realization of a compatible the Federal Government is essential for defining a STOL- interface between the basic engine design and installation, and the development timetable. M.V.E monitoring system, as well as the application of effective diagnostic logic to the acquired data. The purpose of this paper is to examine the design interface requirements for selected monitoring techniques A71-30536 Comparison of STOL design criteria for com- and the analytical methods for data interpretation, and to recom- mercial and military transport aircraft. Jesse C. Peaslee (Boeing Co., mend the design features needed to enhance the monitoring Seattle, Wash.). Society of Automotive Engineers, National Air capabilities to approach the optimum overall condition monitoring Transportation Meeting, Atlanta, Ga., May 1013, 1971, Paper system. (Author) 710465. 13 p. Members, $1.00; nonmembers, $1.50. The characteristics of STOL transport aircraft designed for military missions resemble those developed for commercial air A71-30532 Electronic Engine Condition Analysis System. transport. A military aircraft with approximately 30,000-lb payload H. J. Moses (United Aircraft Corp.. Hamilton Standard Div., Windsor capacity correlates reasonably well with 120-150 passenger com- Locks, Conn.). Society of Automotive Engineers, National Air mercial aircraft. When reasonable margins of safety are applied to Transportation Meeting, Atlanta, Ga., May 10- 13, 1971, Paper takeoff and landing criteria, the military transport designed for
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2000-ft landing and takeoff distances could probably be certified at simulation problems. The potential tradeoff between individual about the same landing and takeoff distances for civil use. However, model engine simulator complexity and test program complexity many STOL military design details are not defined well enough to that will provide the required simulation is introduced. Various assure that similar commercial aircraft would be economical in airline model support techniques and engine simulation techniques that use. Conversely, the criteria for acceptable levels of noise for might be used are described. Test program designs that could yield commercial STOL aircraft might result in a less than optimum aircraft force coefficient data are presented, and finally, the choice aircraft for military service. (Author) of an engine simulator and test program design is considered for three specific aircraft configurations. (Author)
A71-30537 Lift ratings of V/STOL propulsion units. W. W. Thomas (General Electric Co., Aircraft Engine Group, West Lynn, A71-30606 # Combined inertial - ILS aircraft navigation Mass.) and E. G. Smith (General Electric Co., Cincinnati, Ohio). systems. James W. Burrows (Boeing Co.. Seattle, Wash.). Journal of Society of Automotive Engineers, National Air Transportation AircraFt, vol. 8, June 1971, p. 439-443. 7 refs. Meeting, Atlanta, Ga., May 10.13, 1971, Paper 710471. 31 p. Error models for the Instrument Landing System (ILS) and Members, $1.00; nonmembers, $1.50. Inertial Navigation System (INS) are discussed. A method for Lift ratings for V/STOL propulsion units are identified based on combining the two systems using the theory of optimal linear the requirements of the aircraft system. Typical V/STOL handling estimation is given. Results of tests of the combined navigation criteria are applied in the derivation of the lift rating method. system using a ground vehicle operating on runways and in- Analytical techniques are presented for the evaluation of contribut- strumented with an inertial navigator, radio receivers, and a ing factors associated with both the aircraft and propulsion system computer are given with emphasis on the effects of initialization and characteristics. Two typical aircraft systems are used to determine unmodeled errors. The results indicate that use of the combined representative levels of lift ratings for the propulsion units. (Author) system during landing approach would simultaneously reduce the cross-runway position and velocity (track angle) errors. The com- bined system is relatively insensitive to the choice of initial values of A71-30538 Development of an individualized ground certain parameters. Results are still good when the initial parameter training program for DC-10 flight crews. W. P. Moran (American values are chosen t3 approximate a real-time least square fit of INS Airlines, Inc., New York, N.Y.). Swiety of Automotive Engineers, position and velocity to the ILS localizer signal. The effects of the International Simulation and Training Conference, 4th, Atlanta, Ga., principal unmodeled error, platform tilt, are such that the tilt would May 13, 1971, Paper 710472. 9 p. Members, $1.00; nonmembers, have to be precorrected or included in the error model during $1.50. approach if a poorer INS were to be employed. (Author) In an effort to reduce flight crew ground training time, while at the same time maximizing learning efficiency, American Airlines is making use of specialized, individualized, programmed instruction, A71-30607 # Flutter of clamped skew panels in supersonic with increased emphasis on the use of 'hands-on' training equipment, flow. Somayajulu Durvasula (Indian Institute of Science, Bangalore, to transition experienced crewmen to the DC-10 airplane. This paper India). JournalofAircraft, vol. 8, June 1971, p. 461-466. 28 refs. explains the concept of identifying the specific operating require- The supersonic panel flutter problem of clamped skew panels ments unique to this airplane and the development of a program to with in-plane forces is formulated on the basis of the classical, small train crewmen to proficiently perform these operating requirements. deflection, thin plate theory using oblique coordinates. The two- It also covers briefly the principal training hardware developed to dimensional, static approximation is made use of for the aero- support this program. (Author) dynamic loading. Galerkin method with the flutter mode represented in terms of a double series of beam characteristic functions is employed. Results of numerical calculations made for unstressed A71-30604 # Approximate transfer functions for large panels for different combinations of side ratio, angle of skew, and aspect ratio wings in turbulent flow. L. T. Filotas (Toronto, angle of yaw are presented here. The majority of the calculations University, Toronto, Canada). Journal of Aircraft, vol. 8, June 1971, were made using 16 terms in the series. Convergence is examined in a p. 395-400. 19 refs. National Research Council of Canada Grant No. few typical cases. The dynamic pressure parameter for flutter is A-2003; Grant No. AF AFOSR 67-0672A. found to increase mono'onically with the angle of skew for side ratio The fundamental aerodynamic problem associated with flight 1 and to decrease initially before beginning to increase for side ratio through atmospheric turbulence is calculation of the response of a 0.5. The results are also compared with those obtained earlier for wing flying through a single sinusoidal wave of upwash with lines of simply supported panels. (Author) constant phase arbitrarily inclined to the flight path. Approximate closed form expressions for the 'gust transfer functions' relating the lift and moments to the upwash in such a wave are derived for large aspect ratio rectangular wings in incompressible flow. The lift transfer function is expressed as the usual two-dimensional Sears A71-30609 # Energy state approximation and minimum-fuel function multiplied by a factor to correct for finite span and a fixed-range trajectories. Nelson R. Zagalsky, Robert P. Irons, Jr., and further factor to account for the spanwise gust wave number. Robert L. Schultz (Honeywell Systems and Research Center, Multiplying this expression by the chordwise (or spanwise) center of Minneapolis, Minn.). Journal of Aircraft, vol. 8, June 1971, p. pressure leads to the pitching (or rolling) moment transfer function. 488-490. 5 refs. Contract No. N 00014-69-C-0101. Some simple scaling laws, based on these results, are then suggested Search for remedies to the limitations of the energy-state for flight through large-scale turbulence. (Author) approximation in its performance optimization capability for super- sonic aircraft. It is shown that for supersonic aircraft the velocity set is not convex and relaxed controllers are allowed that attain fuel A71-30605 # Designing jet aircraft wind-tunnel test pro- economies superior to any control satisfying the principle of the grams with propulsion system simulation. James L. Grunnet maximum. This results in the failure of this principle to yield any (FluiDyne Engineering Corp., Minneapolis, Minn.). Journal of Air- solutions to the problem of maximum range cruise. It is also shown craft, vol. 8, June 1971, p. 421-427. 8refs. that, in default of an optimal control, there are suboptimal This paper discusses the design of wind-tunnel force test trajectories that contain a minimum fuel cruise segment, and achieve programs for jet aircraft configurations where propulsion system fuel economies very close to those of the optimum relaxed aerodynamic effects must be evaluated in the testing. The simulation controller. An appropriate treatment of the minimum fuel problem requirements of present day jet aircraft are discussed, as are the with range constraints is derived therefrom. M.V.E.
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General discussion of navigation techniques as they have been A71-30610 * # Sonic boom reflection factors for flight near developed since the earliest days of flying. Before WW II the radio the threshold Mach number. Charles L. Thomas (NASA, Ames range had become practical, and during the war radar and hyperbolic Research Center, Aerodynamics Branch, Moffett Field, Calif.). systems were developed which are briefly described. international Journal of Aircraft, vol. 8, June 1971, p. 490. agreements formulated after the war are discussed, as well as Study of the reflection of a very weak shock wave off a smooth short-range aids, long-range navigation, and air traffic control. surface for the condition in which the incident shock wave is nearly Position finding, automatic dead reckoning, automatic landing, the perpendicular to the surface. It is found that in this situation the functions of computers and displays, and area navigation are pressure rise across the reflected shock can be up to twice the reviewed. The future roles of Doppler and inertial navigation, and pressure rise across the incident shock, indicating that sonic boom astronavigation by means of satellites are considered. F.R.L. reflection factors as large as three are possible for aircraft traveling near the threshold Mach number. M.V.E.
A7130725 # Evaluation of American Airlines’ B747 proto- A71-30681 Installation and testing of strain gages for * # type AIDS Engine Monitoring Program. H. D. Kruckenberg high-temperature aircraft applications. Earl J. Wilson (NASA, Flight (American Airlines, Inc., Tulsa, Okla.). American Institute of Research Center, Edwards, Calif.). In: Strain gages and extreme Aeronautics and Astronautics and Society of Automotive Engineers, environments; Society for Experimental Stress Analysis, Technical Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, Session, Huntsville, Ala., May 19, 1970, Proceedings. Edited by L. 0. June 14-18, 1971, AIAA Paper 71-648. 11 p. Members, $1.50; Gillette. Westport, Conn., Society for Experimental Stress Analysis, nonmembers, $2.00. 1970, p. 1-7; Discussion, p. 7-10. 5 refs. American is currently entering the evaluation phase of its 8747 Survey of a research program conducted to define the optimal AIDS (Aircraft Integrated Data System) Program. Attention has been selection, installation, and calibration criteria for strain gages used in focused on expansion of the number of engine parameters to be aircraft flight-load measurements in a high-temperature environment monitored including parameter accuracy and repeatability. Depend- caused by aerodynamic heating. Tests have been made to determine ing upon the parameter, the sampling rate for a 4 second data frame apparent strain, hysteresis, gage factor, insulation resistance, and varies from a minimum of 4 to a maximum of 32. The experience attachment methods. Most of the tests involved apparent strain for gained to date from this program is portrayed including the status of the purpose of matching the thermal expansion coefficients of the the B747 AIDS program objectives. Data utilization is briefly gage and structure materials. A setup for simulating the flight heating discussed. (Author) of an X-15 horizontal stabilizer is described, and measured tempera- ture vs apparent strain curves are shown for two different free- filament types of gages and one weldable type of gage. As a result of A71-30726 # Automatic inspection, diagnostic and prognos- the evaluation program, the weldable platinum-alloy strain gage was tic systems for Army aircraft. Joseph P. Poynton (US. Army, chosen for measurements in area where the temperature was not Aviation Systems Command, St. Louis, Mo.). American Institute of expected to exceed 900 F. Some fatigue problems associated with Aeronautics and Astronautics and Society of Automotive Engineers, using weldable gages are examined, and recommendations are given Propulsion Joint Specialist Conference, 7th, Salt Lake City, IJtah, for strain gage installation. T.M. June 14-18, 1971, AIAA Paper 71-649. 7 p. Members, $1.50; nonmembers, $2.00. The US. Army Aviation Systems Command has been conduct- ing two major pre-engineering development efforts into automated A71-30710 Guidance is forever. C. Draper (Charles S. maintenance monitoring systems. Feasibility, technical approach, Stark Draper Laboratory, Cambridge, Mass.). Navigation, vol. 18, and effectiveness studies are now in progress. Stateof-the-art test bed Spring 1971, p. 26-50. hardware has been applied to four UH-I helicopters. The approach Review of the fundamentals that are alike for all control, was premised on being able to establish a signature norm and discern navigation and guidance problems, showing how the laws of nature detectable differences between this norm and discrepant component lead to patterns mechanization that may be generalized for OF signatures. Degraded parts were implanted in the helicopter engines/ equipment to satisfy the requirements of all missions. Similarities of power-trains and operated in test cells and in flight. Results will be function are stressed rather than differences in design details. discussed based on available data to date. (Author) Guidance translates deviations into correction commands and applies these as input to the control subsystem which changes vehicle velocity toward conditions for mission requirement. Application of earth reference coordinates for aircraft, missiles and spacecraft is A71-30727 # On-board checkout approach to engine diag described from the standpoint of initial orientation to earth nostics - It can work. William Brenner (Grumman Aerospace Corp., Bethpage, N.Y.). American Institute of Aeronautics and Astronautics coordinates. F.R.L. and Society of Automotive Engineers, Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, AIAA A71-30711 The development of longrange hyperbolic Paper 71-651. 7 p. Members, $1.50; nonmembers, $2.00, navigation in the United States. J. A. Pierce (Harvard University, Description of the techniques required to use an on-board Cambridge, Mass.) and R. H. Woodward. Navigation, vol. 18, Spring computer to provide coordinated testing, monitoring, data reduction, 1971, p. 51-62. 19 refs. and analysis. Emphasis is placed upon the need and techniques for Review of the development of navigation by the timing of radio automatic in-flight recording (periodically and when limits are signals, which must be accomplished with an accuracy of a very few exceeded); individual baseline engine performance and Vibration microsec if positional accuracy comparable to other methods of signatures; fault isolation; and trend analysis. The purpose is to navigation is to be achieved. Some details of the British Gee systems provide post-flight displays in the aircraft for use by maintenance and the early developments which led to Loran are discussed. As personnel. The results of implementing this design approach sholrld Loran was perfected, many stations and many thousands of receivers culminate in an operational airborne engine diagnostic system that were placed in operation. The major advantage of Loran is the long will provide the necessary information to determine a scheduled baseline possible. Several improved versions of Loran are described. engine maintenance program. F.R.L. Other systems discussed are Radux and Omega. F.R.L. A71-30728 # A systems approach to engine condition moni- A71-30712 Air navigation techniques. E. W. Anderson toring. K. 6. Kochanski and D. W. Leiby (General Electric Co., (Smiths Industries, Ltd., Cheltenham, Glos., England). Navigation, Cincinnati, Ohio). American Institute of Aeronautics and Astro- vol. 18, Spring 1971, p. 77-92. nautics and Society of Automotive Engineers, Propulsion Joint
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Specialist Conference, 7th, Salt Lake City, Utah, June 14- 18, 1971, included. The key conclusion is that delays in blade separation are AIAA Paper 71-65.?. 10 p. Members, $1.50; nonmembers, $2.00. too short to play a direct role but that delays in stage rotating stall A condition monitoring maintenance concept is being con- development influence the transient compressor response. (Author) sidered or proposed for almost all new commercial or military aircraft. The complexity of jet engines, the engindaircraft interfaces, and the marriage of airborne instrumentation and electronic equip- # Simulation and measurement of pressure tran- ment with ground based electroniclcomputer hardware requires the A71-30735 sients in a mixed-compression supersonic intake during engine surge. use of a systems approach for the development and implementation C. R. Dawson (Boeing Co., Seattle, Wash.). American Institute of of a condition monitoring system. This paper describes how a Aeronautics and Astronautics and Society of Automotive Engineers, systems approach has been used in developing condition monitoring Propulsion Joint Specialist Conference, 7&h, Salt Lake City, Utah, techniques for the CF6 engine as a means of having a workable and June 14-18, 1971,AIAA Paper 71-671. 12 p. 9 refs. Members, $1.50; effective condition monitoring capability available early in its service nonmembers, $2.00. operation. (Author) The flow reduction associated with engine surge was simulated using a high speed mass-flow control coupled to an lll8-scale wind tunnel model of the SST intake. The valve design and the A71-30731* # Shuttle airbreathing propulsion. Warner L. experimental technique are discussed. Intake/airplane interference Stewart, Arthur J. Glassman, and Stanley M. Nosek (NASA, Lewis resulting from the transient was studied using a twin-intakdwing Research Center, Cleveland, Ohio). American Institute of Aero- configuration. Test data indicated lower levels of internal over- nautics and Astronautics and Society of Automotive Engineers, pressure than predicted by a theoretical analysis which used inviscid Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, conservation equations. Transient pressure differences across internal June 14-18, 1971, AIAA Paper 71-662. 11 p. Members, $1.50; doors were experimentally determined and used to establish full-scale nonmembers, $2.00. SST intake load levels. Studies of external interference effects Airbreathing gas turbine engines to provide cruise, landing, enabled a suitable fence to be defined to prevent mutual intake go-around, and ferry capability for the shuttle vehicles face new interference. (Author) requirements such as launch, space residence, and reentry. Also, hydrogen is being considered as an alternate fuel for the engines. It becomes necessary to determine which engines are most suitable and A71-30744* # Use of the gas generator method to calculate to examine them for modifications and technology required to meet the thrust of an afterburning turbofan engine. Frank W. Burcham, Jr. the new requirements. This paper reviews the requirements imposed (NASA, Flight Research Center, Edwards, Calif.). American Institute on the engine, the effect of fuel selection, and the design studies of Aeronautics and Astronautics and Society of Automotive Engi- currently being conducted to assess candidate engine designs in light neers, Propulsion Joint Specialist Conference, 7th, Salt Lake City, of the mission requirements. (Author) Utah, June 14-18, 1971, AIAA Paper 71-680. 11 p. 11 refs. Members, $1.50; nonmembers, $2.00. The feasibility of using the gas generator method to calculate A7130733 * fi Instantaneous and dynamic analysis of suwr- the thrust of an afterburning turbofan engine was investigated. The sonic inlet-engine compatibility. James E. Calogeras, Paul L. NASA Flight Research Center's F-ll1A airplane, powered by TF30 Burstadt, and Robert E. Coltrin (NASA, Lewis Research Center, afterburning turbofan engines, was used. Two variations of the gas Cleveland, Ohio). American Institute of Aeronautics and Astro- generator method were utilized, one based primarily on the exhaust nozzle pressure and area and the other on the nozzle total nautics and Society of Automotive hgineers, Propulsion Joint temperature and weight flow. An influence coefficient study was Specialist Conference, 7th. Sa:t Lake City, Utah, June 14- 18, ?971, performed for static and flighr conditions. Results showed that the AIAA Paper 71-667. 11 p. 9 refs. Members, $1.50; nonmembers, accuracy of the two calculation methods was about equal at static $2.00. conditions, but for flight conditions the total temperature and An experimental wind-tunnel investigation was made to deter- weight flow calculation was superior. Two ground thrust stand tests mine the effects of time-variant distortions produced in a supersonic were also performed, and the thrust calculated by using both inlet on a J85-GE-13turbojet engine. Results are presented principal- methods was compared to the measured thrust; results using either ly in terms of 'instantaneous' distortion amplitudes and contours method were generally within plus or minus 3 percent except at low measured through compressor stall. They indicate that although a power settings. High inlet flow distortion caused an additional scatter time-averaged distortion may be far from a stall-inducing value, of as much as plus or minus 2 percent. (Author) corresponding instantaneous distortion amplitudes can approach or exceed this value. A film made by combining instantaneous distortion contours demonstrates that severe total pressure fluctua- A71-30745 * # Nozzle performance measurement on under- tions at the compressor face can result in an instantaneous distortion wing nacelles on an F-106utilizing calibrated engines and load cells. of a type completely different from the time-averaged distortion. Harold W. Groth (NASA, Lewis Research Center, Cleveland, Ohio). (Author) American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1977,AIAA Paper 71-681. 13 p. 6 A71-30734 # Compressor sensitivity to transient and dis- refs. Members, $1.50; nonmembers, $2.00. torted transient flows. Willem Jansen, Michael C. Swarden, and A flight research program is underway at the Lewis Research Albert W. Carlson (Northern Research and Engineering Corp., Center to study installation effects on turbojet engine exhallst Cambridge, Mass.). American Institute of Aeronautics and Astro- nozzles over a range of flight Mach number from 0.60 to 1.30. Two nautics and Society of Automotive Engineers, Propulsion Joint J85-13 afterburning turbojet engines were mounted in underwing Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, nacelles. Exhaust nozzle propulsion efficiency is being measured AIAA Paper 71-670. 18 p. 14 refs. Members, $1.50; nonmembers, using load cells, calibrated engines, and flight calibrated nacelle tare $2.00. forces. Reference nozzles of known performance were used to The problem is treated with an analytical model which considers determine nacelle tare forces. Analysis of flight calibration data the islet duct, compressor stages, and combustor up to the turbine shows that the system is capable of determining nozzle efficiency to nozzles. Results include compressor stalling sensitivity as a function a one-sigma random error of plus or minus 1.5 percent. (Author) of pressure and temperature amplitude, rotor-speed excursions, pulse duration, circumferential distortion extent, and pulse frequency, as well as blade geometry (such as blade chord length and solidity), and A71-30756 # Systems aspects of augmentor combustion inlet duct geometry. Comparisons with some experimental results are instability. Kervyn D. Mach (USAF, Aero Propulsion Laboratory,
44 1 A71-30157
Wright-Patterson AFB, Ohio). American Institute ofAeronautics and An evaluation was made of analytical and empirical methods Astronautics and Society of Automotive Engineers, PropulsionJoint suitable for predicting the performance of isolated jet engine exhaust Specialist Conference, 76, Salt Lake City, Utah, June 14-18, 1971, nozzles operating in the subsonic, transonic and supersonic flight AIAA Paper 71-697. 4 p. 7 refs. Members, $1.50; nonmembers, regimes. Among the methods examined were those for predicting $2.00. internal thrust, ejector pumping, exhaust plumes, surface pressure The improved performance capability demanded of future distribution, boattail and base drags, and flow separation. The most turbopropulsion systems requires that the major engine components promising methods were evaluated by comparison with data obtained operate at increased levels of performance. Problems, hitherto easily from the testing of variations of convergent, convergent-divergent, overcome during engineering development, can now become major and plug nozzles at Mach numbers ranging from 0.6 to 3.0 in the obstacles. Nearly all augmentor development programs have ex- AEDC 16-Foot Propulsion Wind Tunnels. It was concluded that perienced combustion instability problems (for example, screech), theoretical methods predict pressure distributions, thrust, supersonic often of destructive magnitude. Because combustion instability is an boattail drag, and plume shapes, whereas, the empirical correlation extremely complex phenomenon and not at all well understood, its methods provide good predictions of base drag, subsonic and elimination often entails performance compromises or expensive transonic boattail drags, and flow separation. (Author) schedule slippages. Extensive research into its causes and behavior is necessary to reduce the element of uncertainty in augmentor development programs. (Author) A71-30771 # Predicting airframelexhaust nozzle interac- tions at transonic Mach numbers. E. Grund, W. Presz, Jr., and M. Konarski (United Aircraft Corp., Pratt and Whitney Aircraft Div., A71-30757 ft Combustion instability in turbojet and tur- East Hartford, Conn.). American Institute of Aeronautics and bofan augmentors. John M. Bonnell, Richard L. Marshall, and George Astronautics and Society of Automotive Engineers, Propulsion Joint T. Riecke (United Aircraft Corp., Pratt and Whitney Aircraft Div., Specialist Conference, 7th. Salt Lake City, Utah, June 14- 18, 1971, East Hartford, Conn.). American Institute of Aeronautics and AlAA Paper 71-720. 10 p. 10 refs. Members, $1.50; nonmembers, Astronautics and Society of Automotive Engineers, Propulsion Joint $2.00, Contract No. AF 33(657)-700-0511. Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, An analysis is presented which predicts pressure distributions AIAA Paper 71-698. 9 p. 9 refs. Members, $1.50; nonmembers, and drags over arbitrary slender axisymmetric fuselages and after- $2.00. bodies at transonic Mach numbers. Spreiter and Alksne's method of The state-of-the-art knowledge of high frequency transverse local linearization has been modified to obtain a more accurate and modes (screech) and low frequency longitudinal modes of com- numerically stable flow field solution at all transonic Mach numbers. bustion instability encountered in the development of modern This inviscid solution is iteratively coupled with turbulent boundary turbofan and turbojet augmentors is presented. The operating layer and method of characteristic calculations thereby accounting conditions and design parameters conducive to combustion instabil- for viscous effects and variations in jet plume shape. Analytical ity in turbojet afterburners, turbofan mixed-flow afterburners, and results are compared with experimental data for a variety of turbofan duct burners are discussed. The nature of screech and low applications. After first showing the validity of the theoretical frequency pressure oscillations, as well as possible mechanisms for predictions for basic fuselage and afterbody shapes at approach sustaining the waves, are described. Methods of elis,.' iating high velocities below and above the speed of sound, the effects of varying frequency oscillations, either by utilizing wide bandwidth screech nozzle pressure ratio on boattail pressure-distributionsand drags are liners or by altering the flameholder design are described. Low presented. Plume shapes for static conditions as well as those frequency oscillations are attenuated primarily by tailoring the influenced by external transonic flow are defined. The analytic fuel-air ratio distribution and altering the flameholder design. method is also used to predict the effects of different boundary layer (Author) characteristics and different forebody shapes on afterbody pressure drags. Finally. an example is provided that demonstrates how the analysis can be applied to point up the performance differences A71-30766 # A mathematical model for jet engine com- between a propulsion system in an isolated or airplane installed flow bustor pollutant emissions. Raymond Edelman and Constantino field. (Author) Economos (General Applied Science Laboratories, Inc., Westbury, N.Y.). American Institute of Aeronautics and Astronautics and A71730775 # Flowfields produced by multiple jets in a Society of Automotive Engineers, Propulsion Joint Specialist Con- supersonic stream. James M. Kallis (McDonnell Douglas Astronautics ference, 7th, Salt Lake City, Utah, June 14-18, 1971, AIAA Paper Co., Huntington Beach, Calif.). American Institute of Aeronautics 71-714. 21 p. 24 refs. Members, $1.50; nonmembers, $2.00. and Astronautics and Society of Automotive Engineers, Propulsion This paper presents a mathematical model based on a modular Joint Specialist Conference, 7th, Salt Lake City, Utah, June 14- 18, concept which describes the combustion and pollution formation 7971, AIAA Paper 77-728. 7 p. 20 refs. Members, $1.50; non- processes in a jet engine combustor. The model includes turbulent members, $2.00. Research supported by the McDonnell Douglas mixing, and reaction kinetics appropriate to the coupled fuel Astronautics Independent Research and Development Prograh. oxidation and pollutant species formation process as well as the The situation investigated occurs with jet control of a supersonic effects of two phase flow, recirculation and swirl. The modular vehicle, with supersonic-combustionramjets, and with fluid injection concept is unique and permits each relevant process to be studied for thrust-vector control of solid-propellant rockets. The ultimate individually or coupled as a function of operating and geometric objective of the research is to develop a method or methods for parameters. The importance of 'primary' zone parameters upon CO, predicting the effect on the control force of th interacrion between NOx, CxHy, and soot formation are delineated. (Author) flowfields produced by adjacent jets. The approach taken is to conceptually replace the jets by equivalent solid obstacles and to neglect boundary-layereffects. This makes it possible to reduce the A71-30770 # Analytical and experimental evaluation of problem to that of calculating the inviscid flowfield between performance prediction methods applicable to exhaust nozzles. E. R. multiple solid blunt bodies in a supersonic stream. The results of a Glasgow. J. S. Divita (Lockheed-CaliforniaCo., Burbank, Calif.), P. three-part study of this problem are described. A method is C. Everling, and J. A. Laughrey (USAF, Flight Dynamics Laboratory, developed for calculating the interference flowfield between bodies Wright-Patterson AFB, Ohio). American Institute ofAeronauticsand spaced far enough apart that the shock-wave pattern is regular Astronautics and Society of Automotive Engineers, Propulsion Joint reflection. This calculation is based on the method of characteristics. Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, An evaluation is made of the suitability of available blunt-body AIAA Paper 71-719. 13 p. 29 refs. Members, $1.50; nonmembers, methods for computing the input lines for the characteristics' $2.00. Contract No. AF 33(657)-70-C-0511. calculations. M.M.
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A71-30776 # Aviation and environmental quality (A survey A theory of combustion noise is developed in order to overcome of the SAE/DOT Conference on Aircraft and the Environment). the apparent lack of understanding of the mechanism by which this Robert L. Paullin (US. Department of Transportation, Regulatory type of noise is generated. The theory follows rigorously from the Policy and Standards Div., Washington, D.C.). American Institute of principles of fluid mechanics. Lighthill's approach (1952). used in his Aeronautics and Astronautics and Society of Automotive Engineers, studies of aerodynamic noise, is closely followed. The sound radiated Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, from open, turbulent flames is found to depend strongly upon the June 14-18, 1971, AIAA Paper 71-729. 7 p. Members, $1.50; structure of such flames; presently their structure is not well known. nonmembers, $2.00. However, meaningful bounds and scaling rules for the sound power The SAE/DOT Conference on Aircraft and the Environment, output and spectral content are derived, based upon the present held in Washington, D.C., Feb. 8-10, 1971, brought together for the limited knowledge. A framework is developed which explains past first time those parties interested in problems associated with the experimental work and the origin of combustion noise. O.H. environment, generated by aircraft and airports. This paper sum- marizes the results of that Conference, delineates conclusions and recommendations, and highlights future courses of action laid out by the Conference. The questions of noise pollution and the question of A7130784 * # Some experimental results on lift fan noise air and other types of pollution were directly reviewed during the reduction. M. J., Benzakein and S. 6. Kazin (General Electric Co., course of the Conference. Technical papers were presented and Cincinnati, Ohio). American Institute of Aeronautics and Astro- workshop sessions were held on the source, distribution and receipt, nautics and Society of Automotive Engineers, Propulsion Joint as well as legal and economic aspects of broad problem areas. These Specialist Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, subjects are surveyed in this paper. (Author) AlAA Paper 71-743. 8 p. Members, $1.50; nonmembers, $2.00. Contract No. NAS 2-5462. The results of an extensive experimental program on lift fan A71-30777 # The prediction of the spectral content of noise suppression are presented. The program was carried out on a combination tone noise. Gordon F. Pickett (United Aircraft Corp., tip turbine driven 36-in. lift fan research vehicle propelled by a J85 Pratt and Whitney Aircraft Div., East Hartford, Conn.). American engine. The fan has a design pressure ratio of 1.3 and a design tip Institute of Aeronautics and Astrcnautics and Society of Automotive speed of 950 ft/sec. The comparative results on the relative benefits Engineers, Propulsion Joint Specialist Conference, 7th, Salt Lake of vanelblade ratio, vane lean, rotor stator spacing, fan frame City, Utah, June 14-18, 1971, AlAA Paper 71-730. 7 p. 6 refs. treatment and acoustically treated splitters on fan radiated noise are Members, $1.50; nonmembers, $2.00. Contract No. FA-69-WA-2045. discussed. (Author) The essential features of combination tone noise which is generated from turbofan engines when the relative tip speed of the fan blades is supersonic are examined. A method for determiningthe A71-30785 * # Blown flap noise research. R. G. Dorsch, E. A. expected distribution of sound power among the harmonics of Krejsa, and W. A. Oisen (NASA, Lewis Research Center, Cleveland, engine rotation frequency is presented. The distribution is found to Ohio). American Institute of Aeronautics and Astronautics and depend on two statistical parameters representing the variations in Society of Automotive Engineers, Propulsion Joint Specialist Con- shock strength and the intervals between successive shock waves. The ference, 7th, Salt Lake City, Utah, June' 14-18, 1971, AIAA Paper spectral dependence is shown to be more critical on interval varidl.,e. 71-745. 19 p. 6 refs. Members, $1.50; nonmembers, $2.00. Estimates for typical blade geometries are obtained. O.H. Noise data were obtained with models of both internally and externally blown jet-flaps of the type currently being developed for STOL aircra'ft. The principal tests were conducted with an A71-30778 * # Theoretical and experimental analysis of augmentor-wing model and with an externally-blown double-slotted- acoustic linings for ducts with flow. Walter Eversman (Boeing Co.; flap model. Secondary tests were conducted with a jet flap model. Wichita State University, Wichita, Kan.), M. Dean Nelsen, Denis The interaction between the jet and the flap assembly caused both Armstrong, and Orville J. Hall, Jr. (Boeing Co., Wichita, Kan.). redirection and generation of noise. The data were extrapolated to American Institute of Aeronautics and Astronautics and Society of representative full scale STOL airplane flap systems. It is shown that Automo rive Engineers, Propulsion Joint Specialist Conference, 7th, with a quiet engine the blown flap noise can be the major Salt Lake City, Utah, June 14-18, 1971, AlAA Paper 71-731. 14 p. contribution to the total aircraft noise. Suppression techniques will 26 refs. Members, $1.50; nonmembers, $2.00. NASA-supported therefore be required. (Author) research. A theoretical and experimental program for the design of acoustic linings for the attenuation of fan generated noise in turbo A71-30791 * # Acoustic liner design from a fluid mechanics fan engines is described. This program is based on an interaction approach. T. S. Tonon, W. A. Sirignano, D. T. Harrje (Princeton between an extensive analytical lining performance prediction University, Princeton, N.J.), and P. K. Tang. American Institute of capability and flow duct testing. The theoretical basis for lining Aeronautics and Astronautics and Society of Automotive Engineers, analysis in rectangular, circular, and annular ducts with either Propulsion Joint Specialist Conference, 7th, Salt Lake City, Utah, uniform or sheared flow is formulated and the results of the June 14-18, 1971, AlAA Paper 71-757. 15 p. 13 refs. Members, development of a lining mathematical model are presented. The $1.50; nonmembers, $2.00. NASA-supportedresearch. predictive capability is employed in conjunction with a least Design procedures and recommendations are presented for the attenuated mode lining optimization scheme to determine the lining construction of acoustic liners in the suppression of combustion impedance which will provide the required attenuation spectrum. A instability in liquid and solid propellant combustors and of high flow duct test facility is described and results of the testing of lining intensity noise in air-breathing jet aircraft. The liner geometry may designs and the comparison with theoretical predictions is presented. consist of Helmholtz resonators or quarter-wave tubes. Liner Current developments for the improvement of the design capability cross-flow effects as well as oscillatory pressure effects are considered are discussed. IAuthorl in the methods presented. (Author)
A71-30780 # On combustion generated noise. Warren C. A71-30792 # Experimental correlation of installation effects Strahle (Georgia Institute of Technology, Atlanta, Ga.). American for inlet/airplane integration. W. H. Ball and P. A. Ross (Boeing Co., Institute of Aeronautics and Astronautics and Society of Automotive Seattle, Wash.). American Institute of Aeronautics and Astronautics Engineers, Propulsion Joint Specialist Conference, 7th, Salt Lake and Society of Automotive Engineers, Propulsion Joint Specialist City, Utah, June 14-18, 1971, AlAA Paper 71-735. 11 p. 23 refs. Conference, 7th, Salt Lake City, Utah, June 14-18, 1971, AlAA Members, $1.50; nonmembers, $2.00. Paper 71-759. 10 p. 5 refs. Members, $1.50; nonmembers, $2.00.
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Results of a test of a closely related series of propulsion and Brief description of the research projects concluded and aerodynamic wind tunnel models to investigate installation effects initiated by the Institute in the 1960s. The results obtained so far are for a multimission strategic aircraft configuration. The tests were summarized, and a bibliography is provided for details. The projects designed to yield, in a related fashion, flowfield definition; inlet deal with the interaction of supersonic and subsonic fluid streams, internal performance; and inlet/aircraft drag as a function of inlet even at the boundaries of different surfaces, the fatigue strength of position, forebody shape, and orientation. A semiempirical analysis thin stiffened shells subjected to compressive or tensile loads, as well procedure was derived from the results to predict installed inlet as preliminary, methodologic, theoretical, and experimental investi- performance. The cases examined with this approach show excellent gations on V/STOL aircraft and their use. The experimental correlation with measured installed performance. F.R.L. equipment, partly original, which was designed and built to carry out the investigations. is hriefly described. M.M.
A71-30799 Optimal and suboptimal control synthesis for minimum time VTOL transition. Louis R. Nardizzi, Ming Y. Tarng A71-30824 Conceptual lines for the definition of an (Southern Methodist University, Dallas, Tex.), and Robert J. Parker aeronautical project (Linee concettuali per la definizione di un (LTV Aerospace Corp., Dallas, Tex.). I€€€ Transactions on Aero- progetto aeronautico). Gian Battista Nicolb (Napoli, Universiti, space and Electronic Systems, vol. AES-7, May 1971, p. 506-520. 7 Naples, Italy) and Licio Giorgieri (Trieste, Universiti, Trieste, Italy). refs. NSF Grant No. GK-5608; Contract No. AF 44(620)-68-C-0023. L'Aerotecnica - Missili e Spazio, vol. 50, Feb. 1971, p. 73-84. In Optimal open-loop and suboptimal closed-loop controls for a Italian. VTOL aircraft in a minimum climb-to-cruise time transition are The criteria to be followed in order to convert operational presented in this paper. The optimal open-loop controls. are targets into actual requirements and technical specifications are synthesized by a proposed gradient technique which provides for the outlined, attaching the utmost importance to the achievement of selection of desired changes in physically meaningful parameters optimal cost effectiveness. A rational scheme of research, which has during each iteration step. The suboptimal closed-loop controls are been applied successfully to the definition of the multinational, synthesized as integral mean-square approximations to the optimal multirole combat aircraft MRCA, is described in its general4ines and open-loop controls over the minimum time-toclimb interval. complexities. The setting up of a parametric analysis, which Piecewise-constant feedback gains and switching times are syn- constitutes the central phase of the research, through which thesized for multidimensional control vectors which are linear requirements and specifications are correlated in the most feasible combinations of observable states. Several computational results are solution, is described in detail. M.M. presented for optimal and suboptimal minimum time controls with constrained and unconstrained terminal flight-path angles. (Author) A71-30825 Influence of structural nonlinearities on panel A71-30820 * Practical aspects of sonic boom problems flutter (Influenza delle nonlinearitri strutturali sulle vibrazioni aero- (Aspetti pratici dei problemi del boom sonico). Antonio Ferri (New elastiche dei pannelli). Paolo Santini (Roma, Universiti, Rome, York University, New York, N.Y.). L'Aerotecnica - Missili e Spazio, Italy). L'Aerotecnica - Missi/i e Spazio, vol. 50, Feb. 1971, p. 85-90. 19 refs. In Italian. vol. 50, Feb. 1971, p. 37-45. 15 refs. In Italian. Grant No. Investigation of the problem of the flutter of a flat or curved NGL-33-016-119. panel, with emphasis on the effect upon it of structural and inertial Investigationof SST configurations selected from the standpoint nonlinearities. Geometrical nonlinearities, which can be treated with of minimizing sonic boom. It is shown that, for an overall aircraft sufficient confidence, are discussed, and the lack of information length of 300 ft and a total weight comparable to that of current existing in the area of physical nonlinearities is pointed out. Some U.S. SST designs, sonic booms having shock overpressures of the methods of solution are briefly discussed. M.M. order of 0.6 Ib/sq ft can be obtained. Values as low as 0.3 Ib/sq ft are oossible for aircraft designed for cross-country flights. M.M.
A71-30855 # A solution for an axisymmetrical three. component flow of incompressible viscous fluid (Ob odnom reshenii A71-30821 Shape of the fuselage of modern passenger trekhkomponentnogo osesimmetrichnogo techeniia viazkoi-neszhi- transports (Sulla forma delle fusoliere dei moderni velivoli da maemoi zhidkosti). G. I. Nazarov and A. K. lanko (Kievskii lnstitut trasporto passeggeri). Giuseppe Gabrielli (Torino, Politecnico. Turin, lnzhenerov Grazhdanskoi Aviatsii, Kiev, Ukrainian SSR). Prikladnaia Italy). L'Aerotecnica - Missili e Spazio, vol. 50, Feb. 1971, p. 46-52. Mekhanika, vol. 7, Apr. 1971, p. 123.126. In Russian. 6 refs. In Italian. Derivation of an exact solution to a system of equations Due to the increased efficiency of modern wing flaps and the describing the axisymmetrical motion of the components of an need for larger cargo and passenger spaces, the influence of wings on incompressible viscous fluid flow in a cylinder with a rotating disk of total aircraft drag has been reduced, while fuselage influence has paddles and a mesh preventing the circular motion of the flow. The increased in modern fast subsonic airliners. Some geometric charac- equations contain an arbitrary function which depends only on the teristics of present fuselages are analyzed, and the reasons for new axial coordinate of the mass forces. The solution can be used in prospects regarding the fuselage shape of large airlines are outlined. calculating the parameters of an air flow in the cylindrical com- The expediency of proceeding with the present philosophy of pressor cascade of a turbofan engine. V.Z. cylindrical fuselages with high aspect ratio, as compared with fuselages with a much lower aspect ratio, is discussed. The paucity of experimental data from individual fuselage models, primarily in the A71-30874 # Hypersonic flow past a delta wing. A. L. range of Reynolds numbers close to the real numbers, and the lack of Gonor. (Prikladnaia Matematika i Mekhanika, vol. 34, May-June experimental facilities are stressed. A proposal for a wind tunnel to 1970, p. 481-490.) PMM - Journal of Applied Mathematics and be built as a European cooperative effort is advanced. M.M. Mechanics, vol. 34, no. 3, 1970, p. 452-461. 6 refs. Translation. Analysis of the flow pattern at the windward side of a wing with A71-30822 Aeronautical Institute of the University of Pisa supersonic leading edges, with particular reference to the difficulties associated with obtaining a correct solution to the problem. These ~ Activities of the 1960.70 decade: %Projectscurrently under way (L'lstituto di Aeronautica dell'Universit8 di Pisa - Attiviti ne1 difficulties arise due to the fact that in the flow field behind a strong decennio 1960-70: Programmi in atto). Lucio Lazzarino (Pisa, shock wave, there exist simultaneously uniform potential regions and Universiti, Pis, Italy). L'Aerotecnica - Missilie Spazio, vol. 50, Feb. vortex regions which must be smoothly joined. An analytical theory 1971, p. 53-62. 63 refs. In Italian. of hypersonic flow past a wing with an attached shock wave is
444 A7l-31026
proposed which makes it possible to join the potential and vortex High Frequency (HF) and Synchronous Satellite Readout of remote regions behind the shock wave. V.P. data collection platforms is presented. The HF link analysis is concerned with surface wave transmission for path lengths less than 200 n mi and for ionospheric mode transmission for path lengths A71-30888 Calculation of three-dimensional Structures between 200 and 2000 n mi. The satellite link analyzed is the Number 13 (Raschet prostranstvennykh konstruktsii. Number 13). Synchronous Meteorological Satellite (SMS) currently being built by Edited bV S. A. Alekseev, V. V. Novozhilov, and A. A. Umanskii. NASA/NOAA. Based on this analysis, platform transmitter power Moscow. Izdatel'stvo Literatur PO Stroitel'stvu, p. in 1970. 295 requirements are defined and required SNR margins delineated to Russian. combat the combined effects of high sea state variations and low Survey of the strength and stability of compound-curvature elevation angle operation. Cost considerations based on the differ- shells, bodies of revolution, and multilayer plates. Topics treated ence in platform requirements for each type of link are presented. include (1) the use of analytic functions for solving (Author) three-dimensional problems in the theory of elasticity, (2)stability of Plates, rods. and shells during creep, (3) new applications of photoelastic coatings for studying large and small deformations, and (4)determination Of aerodynamic loads acting on spherical shells, A71-31021 Wake induced flutter of circular cylinders - T.M. Mechanical awcts. Alan Simpson (Bristol, University. BristoL England). Aeronautical Quarterlv, VOI. 22, May 1971, P. 1°1-118. A71-30896 NTC '71; institute of Electrical and The class of cases wherein the mechanical Support System for Electronics Engineers, National Telemetering Conference, the leeward cylinder exhibits static cOUPling is studied using Washington, D.C., April 12-15, 1971, Record. New York, Institute of undamped flutter theory. It is demonstrated that the appearance of Electrical and Electronics Engineers, Inc., 1971. 346 p. Members, couplingterms can lead to quite dramatic changes in the flutter nonmembers. $17.50; $20. characteristics and that considerable care must be fxercised in the Theoretical and experimental research on ,transmission codes, design and operation of wind-tunnel dynamic models if meaningful data processing techniques, sensors, transmitters, receivers, and are to be obtained. An Appendix deals with the general system design procedures for telemetry applications in medicine, problem of mechanical coupling, using the normal coordinates industry, law enforcement, transportatim, earth resources, and approach, and aspects of the problem which bear on the sub- environmental monitoring. Detailed descriptions are given of systems conductor oscillations phenomenon experienced on bundled Owr- used for satellite data collection, seismic data acquisition, weather head power transmission lines are highlighted. G.R. observations, petroleum surveys, air traffjc control, urban traffic measurement, image processing, emergency medical communications, A71-31022 Experimental study of the thermal wake inter- and biological observations. FM threshold extension, random ference between closely spaced wires of an X-type hot-wire probe. F. multiple access, asynchronous TDM, and color .TV transmission E. Jerome (British Columbia, University, Vancouver, Canada), D. systems are outlined. Some studies are directly concerned with E. Guitton (McGill University, Montreal, Canada), and R. P. Patel. increasing the efficiency of electromagnetic spectrum utilization in Aeronautical Quarterty, vol. 22, May 1971, p. 119-126.5 refs. areas of high message traffic density. Research supported by the Department of Transport of Canada; I .Id. Defence Research Board of Canada Grant No. 9551-12. A Disa X-type probe, with the wires 0.15 mm apart, is tested A71-30898 * Results of an experiment to locate ana reaa and found to have a static sensitivity to small angles of pitch, which data from unmanned transponders using satellites. Roy E. Anderson is very sigcificant for Reynolds numbers under 5 but becomes small (General Electric Co., Schenectady, N.Y.). In: NTC '71; Institute of for Reynolds numbers greater than 10. The experiments with the Electrical and Electronics Engineers, National Telemetering Con- Disa X-wire probe were performed in the McGill 0.91 m x 0.61 ference, Washington, D.C., April 12-15, 1971, Record. suction wind tunnel. Two simple modifications were used in order to New York, Institute of Electrical and Electronics avoid the thermal wake effects of the X-wire probe in its original Engineers, Inc., 1971, p. 15-28. Contract No. NAS 5-11634. form. A modified probe, having the wires one wire length apart, is The vhf transponders of NASA's ATS-1 and ATS-3 satellites suggested. This probe was found to have no pitch sensitivity. G.R. have been used to locate and communicate with ships and aircraft and to locate and read sensor data from a buoy moored at sea. The A7131024 The strongly controlled aircraft. R. D. Milne remote platforms have included a buoy moored in deep water near and G. D. Padfield (Queen Mary College, London, England). Bermuda, Coast Guard cutters in the Gulf of Mexico and Pacific AeronauticalQuarterly, vol. 22, May 1971, p. 146-168.7 refs. Ocean, aircraft in flight over the continental United States and the The analysis described shows how the motion of a strongly North Atlantic, and a natwork of ground-based transponders at controlled aircraft can be described in terms of simpler subsystems. Ireland, Greenland, Iceland, Newfoundland, the state of Washington, The sum of the dimensions of the subsystems is equal to the total and Argentina. Position fix accuracies were approximately 1 n mi, 1 dimension of the aircraftkontrol system. The technique, under sigma, using ordinary vhf band mobile communications equipment suitable conditions, yields an approximation to all the modes of with simple, inexpensive tone-code responders connected between motion of the system. In the limit of infinitely strong control the the receivers and transmitters. Much better accuracy would be results agree with Newmark's theory (1957). The theory of kine- obtained using wider bandwidth at higher radio frequencies. The matic constraint serves as a useful indicator for the application of the tests confirmed that a network of remote, unmanned platforms can approximation described. The role of the pilot in applying strong be interrogated at any time, in any sequence with the location of control is placed' in the context of the general thecry. G.R. each platform and its sensor data immediately available at the ground station. (Author) A71-31026 The dynarnical behaviour of a flexible cable in a uniform flow field. R. R. Huffman (Whirlpool Gorp., Benton A71-30900 Design tradeoffs for HF and synchronous Harbor. Mich.) and Joseph Genin (Purdue University, Lafayette, satellite data collection systems. Bernard A. Mitchell and Francis P. Id.). Aeronautical Quarterly, VOI. 22, May 1971,p. 783.195, 12 Cullen (Sanders Associates, Inc., NaShua, N.H.). In: NTC '71; refs. Institute of Electrical and Electronics Engineers, National Telemeter- A nonlinear mathematical model for the study of the dynamics ing Conference, Washington, D.C., April 12-15, 1971, Record. Of an extensible cable subjected to aerodynamic forces generated by New York, Institute of Electrical and Electronics a uniform flow field is formulated. Solutions are found considering Engineers, Inc., 1971, p. 37-45. large displacement caused by suddenly applied loads (i.e,, gusts, The results of a performance and cost tradeoff study between shock WaV.vBS. turbulence) for a range of flow speeds and cable
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lengths. Transition from overdamped to oscillatory motion is Structural design concepts, mechanical stability requirements, observed when flow speed and cable length are increased and and aircraft compatibility considerations are explained for airborne decreased, respectively. The stability of the system is discussed. side-looking radar antennas consisting of end-fed slotted waveguide (Author) arrays. Control of the azimuth and vertical patterns is describid in terms of slot positioning and spacing effects, the use of dielectric lenses and broadside horns, and the stacking of linear arrays. A71-31 034 Institution of Electrical Engineers, Conference Methods used for indication of moving targets are outlined, together on Aerospace Antennas, London, England, June 8-10, 1971, Pro- with mechanical solutions to the problem of compensating for ceedings. London, Institution of Electrical Engineers (IEE Confer- aircraft roll, yaw, and other instabilities. T.M. ence Publication, No. 77). 1971. 286 p. Details of satellite, aircraft, and rocket antenna systems intended for navigational, communications, and telemetry applica- A71-31043 Flush mounted aeronautical antenna. G. A. tions. Structural design features, materials specifications, and elec- Hockham (Standard Telecommunication Laboratories, Ltd., Harlow, trical characteristics are outlined for end-fed slotted waveguide Essex, England). In: Institution of Electrical Engineers, Conference arrays, blade antennas, omnidirectional cylindrical arrays of slot on Aerospace Antennas, London, England, June 8-10, 1971, radiators, Luneberg lenses, conical spiral antennas, and various Proceedings. London, Institution of Electrical antennas developed to meet specific environmental and electrical Engineers (IEE Conference Publication, No. 771, 1971, p. 49-53. requirements. Extensive theoretical and experimental research is An experimental investigation has demonstrated that waveguide described on the effects of radomes, polarization requirements, antennas are feasible at much lower frequencies than usual by using mechanical and electrical scanning procedures, numerical prediction electrically small elements and without the necessity of completely of radiation patterns, and stabilization mechanisms. loading the waveguide with high-permittivitv material. A T.M. flush-mounted airborne antenna was designed which consists of a short length of waveguide with a thin dielectric plug in the aperture. The use of the plug results in a purely real input impedance which A71-31036 A high speed airborne scanning aerial with gives rise to complete energy transfer through the structure when matched patterns. R. H. J. Cary and A. M. Munro (Royal Radar matched to the feed. The plug also provides protection from the Establishment, Malvern, Worcs., England). In: Institution of environment and provides continuity of the flange. Measured Electrical Engineers, Conference on Aerospace Antennas, London, characteristics are given for operation at 5 GHz. T.M. England, June 8-10, 1971, Proceedings. London, Institution of Electrical Engineers (IEE Conference Publication, No. 77), 1971, p. 7-12. A71-31044 An airborne blade antenna for 26-100 MHz. C. Description of a navigational radar antenna consisting of an E. Cooper (Chelton /Electrostatics/, Ltd., Marlow, Bucks., England). offset horn fed reflector and featuring choice of polarization and In: Institution of Electrical Engineers, Conference on Aerospace faster scanning for improved visual display. Right-hand and left-hand Antennas, London, England, June 8-10, 1971, Proceedings. circular, vertical, and horizontal polarization modes are available, and London, Institution of Electrical Engineers (IEE the reception of cross-polarized components is possible in each case. Conference Publication, No. 77). 1971, p. 54-59. The horn is so positioned as to reduce aperture blocking,and to be of Description of a tunable antenna covering either 30-100 or long focal length, enabling a minimum reflector curvature for 26-76 MHz by 35 or 45 individual bands, respectively. Individual minimum cross polarization. T.M. bandwidth varies from less than 0.5 MHz up to 5 MHz at the low and high frequency extremes, respectively. Radiation is from an elevated plane whose capacitance is series-resonated by a combination of from A71-31 038 An airborne electronically scanned X band one to six binary-related inductors, switched by miniature narrow beam circular antenna array. R. H. J. Cary (Royal Radar high-vacuum relays. The entire radiation-tuning-switching mechanism Establishment, Malvern, Worcs., England). In: Institution of is contained within an aerodynamically shaped fiberglass shell. T.M. Electrical Engineers, Conference on Aerospace Antennas, London, England, June 8-10, 1971, Proceedings. London, Institution of Electrical Engineers (IEE Conference Publication, No. A7l-31046 An aerial module for the uhf band. G. Bagley 77). 1971, p. 19-24. (Royal Aircraft Establishment, Farnborough, Hants., England). In: Three different. electronically scanned, X-band, antenna array institution of Electrical Engineers, Conference on Aerospace Anten- configurations which provide all-round coverage when mounted nas, London, England, June 8-10, 1971, Proceedings beneath the nose or fuselage of an aircraft are compared in order to London, Institution of Electrical Engineers (IEE evaluate the advisability of replacing a conventional, mechanically Conference Publication, No. 77), 1971, p. 66-70. scanned 5-ft diam antenna. The configurations include (1) three Preliminary test results are given for an airborne communica- separate planar arrays arranged in a triangular form, (2) a tions system being developed in an attempt to determine the near-hemispherical sectional Luneberg lens antenna, and (3) a efficiency of a relatively low rf carrier power which is applied circular array of 240 radiators switched in a 120-deg arc of 80 directly to the aerial. A composite aerial was mounted on the radiating elements. The Luneberg lens antenna is the most suitable of underside of a Hastings aircraft during the tests while rf drive, power the three configurations, but the overall conclusion is that none of supply and modulation were furnished by a modified 12 channel uhf the three offer enough advantages over the mechanically scanned equipment. Some field strength measurement data obtained on the system to be cost effective at present. T.M. ground for the communications system are given. V.Z.
A71-31047 Fincap communication aerials. J. Mahoney A71-31041 Antennas for sideways looking airborne radar. (Standard Telephones and Cables, Ltd., London, England). In: R. H. J. Cary (Royal Radar Establishment, Malvern, Worcs., England) Institution of Electrical Engineers, Conference on Aerospace Anten- and J. Thraves (EM1 Electronics, Ltd.. Feltham, Middx., England). nas, London, England, June 8-10, 1971, Proceedings. In: Institution of Electrical Engineers, Conference on Aerospace London, Institution of Electrical Engineers (IEE Antennas. London, England, June 8-10, 1971, Proceedings. Conference Publication, No. 77). 1971, p. 71-76. London, Institution of Electrical Engineers (IEE An empirical approach to designing vhfhhf fincap aerials is set Conference Publication, No. 77), 1971, p. 37-42. forth and practical environmental tests of fincap aerials for vibration,
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acceleration, waterproofness, salt corrosion, ice formation and College, London, England). In: Institution of Electrical Engineers, compass safe distance are indicated. Radiation patterns and struc- Conference on Aerospace Antennas, London, England, June 8-10, tural and impedance problems are covered. Simulation and scale 1971, Proceedings. London, Institution of Elec- models are essential in this fincap design technique. V.Z. trical Engineers (IEE Conference Publication, No. 77). 1971, p. 127- 129. Consideration of 3-bit phase shifters giving relative phase shifts of 180, 90, and 45 deg. Their purpose is to steer the beam from the A71-31048 A review of helicopter aerial problems. W. A. phased array as the orientation of the aircraft relative to the satellite Kelly (Ministry of Aviation Supply, London, England) and R. A. changes. Each phase shift bit uses a 3-dB coupler with two arms Burberry (Standard Telephones and Cables, Ltd., London, England). terminated by switching circuits. The 3-dB couplers considered are In: Institution of Electrical Engineers, Conference on Aerospace the two-branch line coupler and the hybrid ring coupler. Both these Antennas, London, England, June 8-10, 1971, Proceedings. couplers may be fabricated by using thin or thick film techniques. London. Institution of Electrical Engineers (IEE F.R.L. Conference Publication, No. 77). 1971, p. 77-82. Difficulties to be overcome for proper accommodation of all the required aerials on modern helicopters are discussed. The multiplicity A71-31 056 A high efficiency Cassegrain aerial design. C. of the aerials, their multiband designs, the extensive use of Dawson (Elliott-Automation Radar Systems, Ltd., Borehamwood, nonmetallic structures, and the increased complexity of airborne Herts., England). In: Institution of Electrical Engineers, Conference radio systems are noted as sources of aerial-siting problems. It is on Aerospace Antennas, London, England, June 8-10, 1971, Pro- suggested that designers bear in mind the limitations of aerials and ceedings. London, Institution of Electrical Engi- treat their siting problems not in isolation but as ingredients of neers (IEE Conference Publication, No. 77), 1971, p. 130-135. helicopter designs as units. V.Z. Description of a compact Cassegrain antenna which has a high efficiencyharrow beam characteristic which illuminates the horizon without excessive ground illumination. It has an oval-shaped An31049 On the uncertainty limit of high speed elec- aperture; only the central circular section has a uniform amplitude tronic scanning. S. Cornbleet (Surrey, University, Guildford. Surrey, distribution. This configuration was chosen in order to make England). In: Institution of Electrical Engineers, Conference on optimum use of radome space. F.R.L. Aerospace Antennas, London, England, June 8-10. 1971, Proceed- ings. London, Institution of Electrical Engineers A7131 060 The antenna performance of the L-1011 (IEE Conference Publicaiion, No. 77). 1971, p. 83-88. 5 refs. Tristar. F. R. Zboril (Lockheed-CaliforniaCo., Burbank, Calif.). In: Element error and angular error analysis for phase and fre- Institution of Electrical Engineers, Conference on Aerospace Anten- quency scanned arrays, covering linear arrays and static matrix-fed nas, London, England, June 8-10, 1971, Proeeedings. and monopulse arrays. An equation is given to show that an array London, Institution of Electrical Engineers (IEE element frequency discrepancy and thus an uncertainty in the beam Conference Publication, No. 77), 1971, p. 157-163. position arise when the array pattern is scanned through an angle of One-year test results are discussed for the antenna arrangement 2 psi in T seconds. The nonexistence limit of angular uncertainty in developed for the aircraft. The arrangement was found to be well the static case is shown to correspond to the classical time-freqL- ?y consistent with weight, aerodynamic and structural design require- uncertainty relation T delta f = 1. V.Z. ments: It is anticipated that the antenna arrangement will provide adequate radiation patterns in the complexity of the aircraft structure in compliance with the required performance of the L-1011 A71-31 053 Hf notch aerials for small aircraft. C. G. communication and navigation systems. V.Z. Fitzpatrick and R. A. Burberry (Standard Telephones and Cables, Ltd., London, England). In: Institution of Electrical Engineers, Conference on Aerospace Antennas, London, England, June 8-10. A71-31062 Design of a linear array of blade antennas for 1971, Proceedings. London, Institution of Elec- aircraft-satellite communication. J. P. B. Vreeburg, 0. B. M. trical Engineers (IEE Conference Publication, No. 77). 1971, p. Pietersen, and F. Klinker (National Luchtvaartlaboratorium, 112-1 17. Amsterdam, Netherlands). !n: Institution of Electrical Engineers, Investigation of notch antennas, which provide one solution to Conference on Aerospace Antennas, London, England, June 8-10, the problem of inefficient radiation at the lower end of the hf band. 1971, Proceedings. London, Institution of E:x- The notch antenna has the additional merit of minimal interference trical Engineers (IEE Conference Publication, No. 77). 1971, p. with primary aircraft structure. Work on a number of small (less than 176-185. The power gain of an antenna system can be expressed in wave 50-ft length) high performance aircraft is described. F.R.L. parameters by assuming that the system can be considered as a linear microwave network. Various simplifications are made resulting in an A71-31054 An airborne phased array for use in an ATC expression for the array factor which takes into account mutual satellite system in L-band. W. M. Fraser and N. C. Williams (British effects of the elements. These mutual influences are determined by a Aircraft Corp., Ltd., Bristol, England). In: Institution of Electrical small number of measurements on the array in its simulated electrical Engineers, Conference on Aerospace Antennas, London, England, environment. Comparison with measured values shows that the side June 8-10, 1971, Proceedings. London, Institu- lobe levels of the radiation pattern of the array are predicted better tion of Electrical Engineers (IEE Conference Publication, No. 77). than when mutual effects are neglected. It is expected that the 1971, p. 118-126. information from an array consisting of a few elements is sufficknt Use of a phased array on board the aircraft to alleviate prbb\ems to predict the performance of a similar array with more elements. of power budget and vulnerability to multipath and interference. A (Author) phased array provides the required hemispherical coverage in a number of manually steered, high gain, narrow bandwidth steps. A7131074 The L band aircraft antenna of the 'Dioscures Major design constraints are aircraft mounting, airframe visibility, System' (Electronic scanning for satellite-aided navigation system). and pattern interference in addition to airline operator considera- B. Dorier (SNECMA, Suresnes, Hauts-de-Seine, France). In: Institu- tions. F.R.L. tion of Electrical Engineers, Conference on Aerospace Antennas, London, England, June 8-10, 1971, Proceedings. A71-31 055 A microstrip p.i.n. diode controlled L-band London, Institution of Electrical Engineers (IEE Conference Publica- digital phase shifter. P. A. Matthews and D. Markopoulos (University tion, No. 771, 1971, p. 259-264.
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Discussion of an L band antenna which is based on the use of a The behavior of a specially stiffened hingeless rotor operating at convex array consisting of left- and right-hand circularly polarized discrete rpm, over a wide range of rpm, at airspeeds sufficiently high radiating elements and of static electronic steering circuits. This for conversion from helicopter to airplane flight to take place has makes it possible to scan two antenna beams independently in two been studied analytically and experimentally. The rotor shaft was directions. Such an aircraft-integrated equipment permits simulta- fixed against pitching and rolling motion in both studies. Aeroelastic neous L band radio links with two synchronous satellites. A ground derivatives of the 33-foot, 3-bladed rotor with irreversible swashplate station can then ensure accurate aircraft location by electronic control were predicted analytically and verified by tests over an methods. Practically worldwide coverage is possible with 6 synchro- airspeed range of 50 to 120 knots in the Ames 40 x 80 foot wind nous satellites. F.R.L. tunnel. A constant speed gyroscope was introduced into the cyclic feathering system and the swashplate position control released so that the swashplate became free to take up positions dictated by A71-31 075 A circular slot aperture with arbitrary polariza- rotor and gyroscope moment equilibrium. The system automatically tion for aerospace applications. Richard E. Herskind (Avco Corp., trimmed hub moments to near zero. Rotor control was then Systems Div., Wilmington, Mass.). In: Institution of Electrical introduced in the form of moments applied to the free swashplate, Engineers, Conference on Aerospace Antennas, London, England, and the control effectiveness was measured. The control system is June 8-10, 1971, Proceedings. London, Institu- shown to be stable, to provide almost zero phase shift and to exhibit tion of Electrical Engineers (IEE Conference Publication, NO. 77). nearly constant hub moment to control moment gain over wide 1971, p. 265-275. ranges of rpm and advance ratio. (Author) Description of a one-wavelength circular slot aperture radiation from the surface of a circular cylinder. It is shown that the single circular slot has radiation characteristics which offer a lower A71-31079 HLH primary flight control system design. ellipticity ratio than that of a crossed linear slot radiating under Richard W. Sanford, Peter R. Venuti, and Derek Wood (Boeing Co., similar conditions. It is suggested that a circular slot aperture can be Vertol Div., Philadelphia, Pa.). American Helicopter Society, Annual used to approximate the pattern characteristics of an Archimedian or National V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, log spiral on a cylinder over a wide range of frequencies. F.R.L. Preprint 503. 15 p. Members, $1.25; nonmembers, $2.00. Demonstration that the most attractive primary flight control system for the Heavy Lift Helicopter (HLH) is a fly-by-wire electrical analog of the conventional mechanical control linkage. This type of A71-31076 Army helicopter performance trends. Richard system can be mechanized using known techniques, and in many B. Lewis, II (U.S. Army, Edwards AFB, Calif.). American Helicopter cases identifiable components. It is pointed out that the only Society, Annual National V/STOL Forum, 27th, Washington, D.C., remaining step required for acceptance of this fly-by-wire system is May 19-21, 1971, Preprint 500. 10 p. 15 refs. Members, $1.25; construction and flight demonstration of a complete operational nonmembers, $2.00. prototype. M.M. Performance data of seven different types of current Army rotorcraft, based on US. Army Aviation Systems Test Activity test A71-31080 Development of the ABC rotor. Robert K. experience, are summarized. Nondimensional presentations are em- Burgess (United Aircraft Corp., Sikorsky Aircraft Div., Stratford, ployed to generalize the data. Several aspects of both : wring and Conn.). American Helicopter Society, Annual National V/STOL forward flight performance are first discussed. Out-of-ground effect Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 504. 17 hover power required, compressibility effects on hovering perfor- p. 6 refs. Members, $1.25; nonmembers, $2.00. mance, and the influence of ground proximity are examined. Level Description of the development of the ABC rotor from flight power required, drag effects, and compressibility trends in conception through small-scale model wind-tunnel testing, full-scale forward flight are shown. Finally, a discussion of autorotational analysis, design, fabrication, and ultimate wind-tunnel testing of a descent performance is presented. O.H. 40-ft-diam rotor in a 40 x 80 ft wind tunnel. The principal design tradeoffs resulting from the early analyses and testing are discussed, along with their expected impact on the full-scale rotor charac- A71-31077 Full-scale proprotor development Kenneth G. teristics. Materials and manufacturing methods employed are Wernicke and H. Kipling Edenborough (Bell Helicopter Co., Fort covered, including the more important difficulties surmounted Worth, Tex.). American Helicopter Society, Annual National during the development. The major test programs are outlined, V/STOL Forum, 27th. Washington, D.C., May 19-21, 1971, Preprint including blade balancing, turbine test bed operation and full-scale 501. 16 p. 27 refs. Members, $1.25; nonmembers, $2.00. wind-tunnel testing in the wind tunnel at speeds up to 180 knots and An advanced-design, 25-foot-diameter, flightworthy proprotor at advance ratios up to .91. A.B.K. was tested in the NASA-Ames Large-Scale Tunnel, and reached a simulated speed of 408 knots. The tests were part of an Army/NASA Proprotor Technology Program, the objective of which is to develop A71-31081 * Application of a liftingsurface theory to the technology for an aircraft which will meet the civil and military need calculation of helicopter airloads. Wayne Johnson (MIT, Cambridge, for VTOL transportation. The proprotor, suitable for a demonstrator Mass.). American Helicopter Society, Annual National V/STOL aircraft, displayed good stability and performance. Measured Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 510. 10 damping of the major coupled modes agreed with theoretical p. 14 refs. Members, $1.25; nonmembers, $2.00. Grant No. predictions and one-fifth-scale model tests. Propulsing efficiencies NGR-22-009-303;Contract No. N 00019-69-C-0219. exceeding 90% were measured and agreed closely with theory. A method is described for the application of a lifting-surface Operation of the proprotor, satisfactory in each flight mode, met or solution of a model problem for vortex-induced airloads to the exceeded all design requirements. The proprotor is ready for flight calculation of the airloading on a helicopter rotor blade. A test. O.H. comparison of the loads calculated for a simplified vortex and rotor blade configuration, using the lifting-surface solution and the usual A71-31078 * Horizontal stoppable rotor conversion. George lifting-line theory, indicates that the former should be used for A. Watts (Lockheed-California Co., Burbank, Calif.) and James C. vortices closer than about five chord lengths to the blade. A Biggers (NASA, Ames Rqsearch Center, Moffett Field, Calif.). comparison of the lifting-surface-theory results with experimental American Helicopter Society, Annual National VETOL Forum, data shows good agreement. Some results of the calculation of 27th, Washington, D.C., May 19-21, 1971, Preprint 502. 12 p. 6 refs. helicopter airloads using the lifting-surface-theory solution are Members, $1.25; nonmembers, $2.00. Army-supported research; presented. These results indicate that a very accurate wake geometry Contract No. NAS 2-5168. model will be required to make full use of the accuracy of the
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lifting-surface-theorysolution. They also show that there is yet much An analytical/ground test program has succeeded in isolating more to learn about the phenomenon of vortex/blade interaction. vertical and in-plane main rotor-head vibratory forces from a (Author) helicopter fuselage without introducing static deflection. This was achieved by using a hydropneumatic, servo-centered isolation system installed at the transmission/airframe interface. Shake tests showed A7131082 # A study of the effects of nonuniform swash- overall reductions of approximately 70% in fuselage response to main plate stiffness and out-of-blade track on rotor dynamics and stability. rotor 6p force excitations using a CH-53A test vehicle. These tests Vincent Piarulli (Rochester Applied Science Associates, Inc., .!. showed that significant reductions can be achieved over the complete Rochester, N.Y.). American Helicopter Society, Annual National range of excitation frequency above the isolator resonances. Step V/STOL Forum, 27th, Washington. D.C., May 19-21, 1971, Preprint load and shake tests demonstrated that the isolated aircraft had 571. 12 p. Members, $1.25; nonmembers, $2.00. near-rigidcharacteristics for transient and 1p excitations. The aircraft This paper presents the results of a study directed at investigat- isolator modes were stable, and analysis established that aircraft ing the effects of an anisotropically mounted flexible swash-plate, mechanical stability characteristics remain unchanqed. (Author) including blade out-of-track, on the vibratory and mechanical stability characteristics of helicopter rotor systems. The analysis which has been developed is based on a combined Laplace transform and associated matrix approach. The program yields complex A71 -31086 Analytical investigation of the effects of blade eigenvalues which indicate frequency and rate of growth or decay of flexibility, unsteady aerodynamics, and variable inflow on helicopter a natural mode of the complex system. Blade modal response and rotor stall characteristics. E. D. Bellinger (United Aircraft Research swash-plate motion corresponding to a given eigenvalue are pre- Laboratories, East Hartford, Con n. ) . American Helicopter Society, dicted. (Author) Annual National V/STOL Forum, 27th, Washington, D. C., May 19-21, 1971, Preprint 520. 14 p. 21 refs. Members, $1.25; A7131083 * # The method of multiblade coordinates in the nonmembers, $2.00. , linear analysis of lifting rotor dynamic stability and gust response at An analytical study was conducted to investigate systematically high advance ratio. Sheng-Kuang Yin and Kurt H. Hohenemser the relative importance of blade flexibility, unsteady aerodynamics, and variable inflow (with and without wake distortions) in deter- (Washington University, St. Louis, Mo.). American Helicopter mining predicted helicopter rotor stall characteristics. The theoretical Society, Annual National V/STOL Forum, 27th, Washington, D.C., results of this study were compared with corresponding full scale May 19-21, 1971, Preprint 512. 14 p. 7 refs. Members, $1.25; wind tunnel results for the H-34 rotor system. Various levels of rotor nonmembers, $2.00. Contract No. NAS 2-4151, stall were investigated at forward speeds of 117 knots and 194 knots. The dynamic linearized or perturbation problem of a lifting The classical theory (rigid blades, steady aerodynamics, and constant rotor with rigid flapping blades having elastic restraints, with rigid inflow) produced good correlation at nominally unstalled operating hub and with four types of control feedback is solved for high rotor conditions. However, rotor lifts significantly lower than the test advance ratio with the method of multiblade generalized coordinates, values were predicted at high blade angles of attack. The use of using the Floquet state transition matrix. Numerical examples unsteady airfoil data provided the most significant improvement in assuming three and four blades per rotor show considerable correlation by allowing higher section lift coefficients to be reached differences in the modal function columns and in the gain factors at due to the 'stall delay' phenomenon associated with unsteady the stability limits depending on the number of blades. A rotor operating conditions. The primary effect of blade flexibility was due representation with constant coefficients in the differential equd.. Jns to blade torsional deflections, which, as with blade pitch changes, for the multiblade coordinates gives for a rotor advance ratio of .8 a had a direct effect on performance. It was found that the deflections, good approximation for some modes but does not account for the and therefore performance, were sensitive to the chordwise location substantial effects of blade number and is in some cases unconserva- tive. The method of multiblade coordinates is applied to the analysis of the mass axis, indicating the need for accurately defining this of random blade flapping from continuous atmospheric turbulence parameter. Variable inflow, although producing significant changes in to obtain the effectiveness of the various feedback systems in the angle of attack distribution over the disk, did not appreciably affect rotor performance. (Author) reducing the root mean square flapping amplitudes. (Author)
A71-31084 Prediction of control loads due to blade stall. F. J. Tarzanin, Jr. (Boeing Co., Vertol Div., Philadelphia, Pa.). A71-31087 * Detailed aerodynamic measurements on a American Helicopter Society, Annual National V/STOL Forum, model rotor in the blade stall regime. Richard K. Fisher, Jr. (Boeing 27th, Washington, D.C., May 1921, 1971, Preprint 513. 14 p. 12 Co., Philadelphia, Pa.) and W. J. McCroskey (U.S. Army, Mobility refs. Members, $1 25; nonmembers, $2.00. Research and Development Laboratory, Moffett Field, Calif.). Description of a semiempirical aerodynamic theory for eliminat- American Helicopter Society, Annual National V/STOL Forum, ing the prime limitation to the operational boundaries of helicopters 27th, Washington, D.C., May 19-21, 1971, Preprint 521. 14 p. 13 represented by the sharp growth of control loads due to retreating refs. Members,.$l.25; nonmembers, $2.00. Army-supported research; blade stall. The theory includes unsteady aerodynamics with linear Contract No. NAS 2-5473. shed wake, stall hysteresis for lift, drag, and pitching moment, and An investigation of retreating blade stall on a model helicopter three-dimensional flow. This theory was incorporated into an rotor has shown that a series of separate pressure distribution and aeroelastic rotor analysis program that can now predict the high boundary layer events lead up to ccmplete blade stall. This pitch link loads associated with blade stall. This aeroe!astic rotor experimental picture of the local flow field was gleaned from analysis was then used to study how the aerodynamic and structural measurements of blade element pressure and skin friction distr,ibu- characteristics of the rotor system influence the stall-induced high tions, surface streamline directions, and local angle of attack. The control loads. This investigation led to suggestions that may results of the experiment also demonstrate the limitations of significantly reduce or eliminate stall flutter loads. M.M. contemporary empirical corrections in accounting for three- dimensional and unsteady effects on classical airfoil data after complete stall occurs. The measurements further indicate that some A71-31085 Preliminary development of an active trans- of the most significant unknowns in the problem are the local mission isolation system. Paul von Hardenberg and Paul B. W. blade-element velocities and angles of attack. From the results of this Saltanis (United Aircraft Corp., Sikorsky Aircraft Div., Stratford, test, it is postulated that the basic retreating blade stall mechanisms Conn.). American Helicopter Society, Annual National V/STOL become increasingly dominated by dynamic vortex-shedding from Forum, 27th, Washington, D.C., May 1921, 1971, Preprint 514. 1I the leading edge as advance ratio increases. (Author) P. Members, $1.25; nonmembers, $2.00.
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A71-31088 * Tip vortices - Velocity distributions. N. A. A71-31091 Day and night fire power of the Cheyenne. Chigier and V. R. Corsiglia (NASA, Ames Research Center, Moffett Bernard J. Merritt (US Army, St. Louis, Mo.) and John C. Kirby Field, Calif.). American Helicopter Society, Annual National (Lockheed-California Co., Burbank, Calif.). American Helicopter V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint Society, Annual National V/STOL Forum, 27th, Washington, D.C., 522. 14 p. 9 refs. Members, $1.25; nonmembers, $2.00. May 19-21, 1971, Preprint 530. 13 p. Members, $1.25; nonmembers, Detailed measurements of velocity distributions have been made $2.00. in vortices generated at the tip of a square-tip, 18-in.-chord, 48-in. The Army/Lockheed Cheyenne attack helicopter, with its semispan blade mounted in the NASA-Ames 7- by IO-foot wind integrated complement of armament, fire .control, and navigation tunnel. Time-mean-averagevelocity components were measured using equipment, has been designed to obtain high first round hit a triple-sensor hot wire probe operated by three separate anemom- probabilities at long ranges. The fire control system has been eters. With the blade at an angle of attack of 12 deg, traverses were developed to include a night capability with approximately the same made through the vortex centers at six axial stations, corresponding accuracy as in daylight. The details of the Cheyenne weapon system to x/c ratios of -0.75, -0.50, -0.25, 0.0, 2.0, and 4.0, where x/c equal and the system engineering tools used during the design/development to 0 is the trailing edge. The dimensions of the vortex increase with process are discussed. O.H. distance downstream over the blade surface, and at x/c equal to 4 the vortex core radius is 0.7% of the span. Maximum circumferential velocity of 42% of mainstream velocity was measured at x/c equat to -0.50, over the wing surface, followed by decay to 24.0% of A71-31 092 An attack helicopter weapons delivery com- mainstream velocity at x/c equal to 4. Axial velocity in excess of puter. John A. Simpson (United Aircraft Corp., Radar Research free-stream velocity was measured in the vortex core with maximum Group, Norwalk, Conn.). American Helicopter Society, Annual axial velocity of 140% of free-stream velocity at x/c equal to -0.25. National V/STOL Forum, 27th, Washington, D.C., May 19-21, 7971, The vortex center moved inboard from the tip at x/c equal to -0.75 Preprint 531. 7 p. Members, $1.25; nonmembers, $2.00. to 2.9% of span at x/c equal to 4. A secondary vortex was located A system of computation suitable for both bombing and gun outboard of the main tip vortex. (Author) laying is described. It is based upon the use of the planar distributed function generator, and gives a general, closed-form, virtually instantaneous solution capability. It can provide an automatic or A7131089 * # A method for predicting helicopter wake manual release for bombs, or laying cues for guns, in milliseconds. It geometry, wake-induced flow and wake effects on blade airloads. S. is shown that by using the low-cost analog system described, mission G. Sadler (Rochester Applied Science Associates, Inc., Rochester, tactics will not be constrained and the helicopter's guns and bombs N.Y.). American Helicopter Society, Annual National V/STOL can be deployed with full flexibility. The computer is essentially Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 523. 11 made of solid-state components and photoetched metal film re- p. 16 refs. Members, $1.25; nonmembers, $2.00. Contract No. NAS sistors. It is thus inherently reliable, and the projected mean time 1-8448. between failure is 4,070 hr. G.R. Rotor wake geometries are predicted by a process similar to the start-up of a rotor in a free stream. An array of discrete trailing and shed vortices is generated. Vortex strengths correspond to stepwise A71-31094 # AN/ASN-86 Inertial Navigation Set. J. 8. radial and azimuthal blade circulations, and this array is .' iited to an Hughes (Litton Industries, Inc., Guidance and Control Systems Div., arbitrary number of azimuthal steps behind each. blade. The Woodland Hills, Calif.) and R. W. Creed (US. Army, Avionics remainder of the wake model for each blade is an arbitrary number Laboratory, Fort Monmouth, N.J.). American Helicopter Society, of trailed vortices. Vortex element end points are allowed to be Annual National V/STOL Forum, 27th, Washington, D. C., May transported by the free stream and vortex-induced velocities. Wake 19-21, 1971, Preprint 533. 14 p. Members, $1.25; nonmembers, geometries, wake flows, and wake-induced velocity influence coef- $2.00. ficients for use in blade loads calculations were determined and Description of a purely inertial navigation system consisting of measured. Computed and measuied average wake velocities are an inertial platform, a digital computer, and a control-indicator unit. compared and indicate that the wake model is satisfactory for The computer has the necessary interface circuitry for nonuniform inflow calculations. These velocities and the correspond- interconnection to 11 other systems. The control-indicator unit ing computed wake geometries are discussed. Wake geometries are provides capability to enter or read out position information in presented and discussed for various rotor configurations, including lathong or UTM (universal transverse mercator) coordinates. It also rotor systems having shaftwise separations, nonuniform azimuthal contains controls for performing all navigation operations. The spacing, counter rotating blades with different rotor lengths and system has a built-in self test which is capable of isolating other physical differences. (Author) malfunctions to the unit level. Technical details of the system and a description of the system's operational application to both fixed-wing aircraft and helicopters are presented. It is considered that A71-31090 Forward flight performance of a coaxial rigid there should be many commercial applications of this equipment. rotor. Vincent M. Paglino (United Aircraft Corp., Sikorsky Aircraft F.R.L. Div., Stratford, Conn.). American Helicopter Society, Annual National V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 524. 16 p. 7 refs. Members, $1.25; nonmembers, $2.00. A71-31095 The night rescue terminal navigation problem. A brief review is presented of basic aerodynamic principles Cecil S. Richardson (United Aircraft Corp., Sikorsky Aircraft Div., differentiating conventional rotors and coaxial rigid rotors. Stratford, Conn.). American Helicopter Society, Annual National Performance data obtained from a recent test of a full-scale coaxial V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint rigid rotor (ABC) system in the NASA/Ames wind tunnel are given 534, 11 p. 10 refs. Members, $1.25; nonmembers, $2.00. and discussed. These data, ranging to advance ratios of .91, are In night rescue, visual contact has to be replaced by compared with conventional rotor data and with blade element rotor instrumented techniques that enable precise destination definition, theory at various stages of refinement. A parametric study is approach, and hover. Initial efforts culminated in design, presented to illustrate the influence of a number of blade geometric development, and test of the Limited Night Recovery System properties on ABC propulsive efficiency. At all advance ratios tested, (LNRS), for the HH-53 aircraft. The functional requirements of the ABC system was aeromechanically stable; it had superior loading improved sensors for homing and approach have been presented capability and more favorable stall characteristics when compared to along with functional requirements for a positional hover sensor an H-34 rotor. Of the geometric changes investigated, blade twist was system. A currently available set of sensor systems has been found to have largest influence on predicted performance. O.H. described and a LORAN retransmission concept for solving some of
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the remaining problem areas has been presented. Sufficient flapwise bending modes to predict hub moments. Third is the information has been provided to enable prospective manufacturers question of blade/fuselage dynamic coupling, which arises owing to of terminal navigation sensor aids to initiate development of the more powerful hub moments which are generated by a hingeless solutions to the night rescue terminal navigation problem as it applies rotor. Blade/fuselage coupling can be of considerable importance. to the current rescue helicopter system. G.R. (Author)
A71 -31099 Feel augmentation and sensitivity control in A71 -31096 Synthesis of an electromechanical control high speed helicopters. Sean J.. O'Connor (United Aircraft Corp., system for compound hingeless rotor helicopter. R. L. Heimbold a Sikorsky Aircraft Div., Stratford, Conn.). American Helicopter (Lockheed-CaliforniaCo., Burbank, Calif.) and C. D. Griffith (Sperry Society, Annual National..V/STOL Forum, 27th, Washington, D. C., Rand Corp., Flight Systems Div., Phoenix, Ariz.). American Heli- May 19-21, 1971, Preprint 542. 8 p. Members, $1.25; nonmembers, copter Society, Annual National V/STOL Forum, 27th. Washington, $2.00. D.C., May 19-21, 1971, Preprint 536. 13 p. Members, $1.25; Handling qualities problems associated with changing control nonmembers, $2.00. sensitivity accompany the increased speed capabilities of high A study was conducted to configure an electromechanical performance helicopters. Two approaches to the problems have been control system for a hingeless rotor compound helicopter. Emphasis presented. In the case of the pitch control, a constant pitch stick was placed on control system synthesis using the root locus method force per resultant load factor characteristics has been implemented. with transfer functions derived from a linear model of the six This feel augmentation approach masks the sensitivity problem airframe degrees of freedom and the fundamental rotor flapping effectively. In the case of the collective control, the collective blade modes. An attitude or quasi-attitude feedback is required to pitch vs stick displacement transient has been modified. This counteract the strong divergent tendency of hingeless rotor about the approach compensates for the increased sensitivity to changes in pitch axis. Feedback from both pitch rate and pitch hub moment collective setting at high speeds. A number of conclusions are were evaluated and the latter was chosen for use in the pitch axis presented which have been gathered from extensive flight testing. because of its ability to relieve high airframe moments when in G.R. ground contact as well as to provide damping for the attitude feedback. The roll axis is stabilized with rate feedback alone. Effects of the control system feedbacks on loads and rotor stability are briefly covered. An analogue computer program was employed to A71-31100 Rotor stability derivatives determined from refine control system parameters. (Author) wind tunnel tests of an instrumented helicopter. Robert E. Rohtert and Sally V. LaForge (Hughes Tool co., Culver City. Calif.). American Helicopter Societf, Annual National V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 543. 10 p. A71-31097 IFR hover for heavy lift helicopterswith slung Members, $1.25; nonmembers, $2.00. Contract No. NOW-66-0657-f. load. William P. Keane and R. Joseph Milelli Army, Avionics (U.S. Tests of an operational prototype OH-6A helicopter were Laboratory, Fort Monmouth. N.J.). American Helicopter Society, conducted in the Ames 40- by 80-foot wind tunnel. From these tests, Annual National V/STOL Forum, 27h, Washington, C., May D. experimental stability derivatives were obtained. Analytical studies 19-21, 1971, Preprint 540, 11 p. Members, $1.25; nonmembers, were conducted using a simplified digital computing technique for $2.00. comparison with these wind tunnel experimental data. The results of A man-machine simulation program has been completed which this investigation indicated that the simplified computer program can indicates the feasibility of developing an IFR hover capability with be used to predict rotor stability derivatives. The agreement between properly chosen sensors, controls and displays. Display alternatives theory and test was excellent at advance ratios from 0.25 to 0.35, included a simple hover indicator, a flight director and a fully even though the theory used an assumed uniform induced velocity integrated multicolored CRT display. IFR hover was shown to be a reasonable task from a pilot workload standpoint. A wide range of rather than a variable induced velocity. A limited amount of data was performance was achieved with the best systems providing a obtained at an advance ratio equal to 0.4, and the results are helicopter hover accuracy from 1 to 2 feet. All tests were performed inconclusive. The numerical program, which also was simplified in under simulated gust conditions. The results obtained indicate the not accounting for blade flexibility, predicted the blade flapping for feasibility of accomplishing more precise construction and logistic unstalled conditions but did not predict the large increase in blade tasks by the helicopter in the near future through the use of flapping due to retreating tip stall. However, comparison of data and instrument hover. The unloading of containerized ships by the theory indicated that retreating tip stall did not significantly change helicopter is a possible application with both commercial and the rotor pitching moment about the aircraft center of gravity. military advantage. G.R. Pitching moment derivatives, horizontal stabilizer on and off, were used to estimate the stabilizer effectiveness and downwash. (Author)
A71 -31098 A stability and control theory for hingeless rotors. H. C. Curtiss, Jr. (Princeton University, Princeton, N.J.) and A7131101 * Factors affecting handling qualities of a lift- N. K. Shupe (US. Army, Avionics Laboratory, Fort Monmouth, fan aircraft during steep terminal area approaches, Ronald M. Gerdes N. J.) . American Helicopter. Society, Annual National V/STOL and Charles S. Hynes (NASA, Ames Research Center, Moffett Field, Forum, 27h, Washington, D.C., May 19-21, 1971, Preprint 541. 12 Calif.). American Helicopter Society, Annual National V/STOL p. 10 refs. Members, $1.25; nonmembers, $2.00. Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 544.,9 p. Some fundamental aspects relating to the prediction of the Members, $1.25; nonmembers, $2.00. stability and control characteristics of hingeless rotor helicopters are The XV-5B lift-fan aircraft was one of four NASA V/STOL discussed. In particular, areas are examined which require a different research vehicles recently used to explore the factors affecting analytical treatment from the articulated rotor. Three areas are handling qualities in the terminal area. The objectives of the program examined as having potential importance. First, the induced flow were to define the limitations of powered-lift VTOL aircraft that field of the rotor is considered. It is shown that the hingeless rotor prevent full exploitation of their low-speed capabilities, and to will give rise to a first harmonic variation in the induced flow field develop operationally feasible techniques for performing simulated which can be included in the analysis through an effective Lock precision instrument landing approaches. A 10 deg ILS approach task Number. The second area involves consideration of the number of was selected as representing a typical steep-angle approach with flapwise bending modes required to represent the hingeless rotor for which to explore these problems. Three major phases of the stability and control studies. It is desirable to include at least two approach were considered: (1) interception of the glide slope at 1500
45 1 A71 -31102 ft, (2) glide-slope tracking, (3) deceleration along the glide slope to a loading, disk loading, tip speed, number of blades, blade width/sq ft, spot hover. Variations in airplane deck angle, deceleration schedule, etc., are discussed. Trends toward new types of rotor retention and and powered-lift management were studied to mess their effects on component design configurations to avoid size-effect weight handling qualities. The overall descent perfo nance envelope was penalties, such as sandwich construction, multicell structures, identified on the basis of such operational limitations as fan stall, advanced composites, and articulated hub/retention systems are maximum comfortable descent rate, and controllability restrictions. reviewed. It is concluded that the changes in the structural and The 'collective-lift' stick provided precise glide-slope tracking capa- dynamic parameters of rotor systems due to large size increases are bility (to within plus or minus 20 ft) through direct control of fan fundamental in nature and will require thorough investigation and lift, but the pilot tended to 'chase' glide slope if engine power understanding before it is possible to arrive at the optimum design. (throttle} was modulated. The pilot preferred a deck-parallel (to glide F.R.L. slope) attitude, for which he used powered lift (collective) to control glide slope and pitch attitude (stick) to keep the angle of attack near zero, which minimized his workload. This technique also provided a A71-31106 Preliminary design methods of V/STOL greater angle-of-attackmargin from fan stall. Workload was reduced prop/rotors. Warren K. Stratton and Richard B. Freeman (Boeing when the deceleration schedule was delayed until the aircraft was Co., Vertol Div., Philadelphia, Pa.). American Helicopter Society, well established on the glide slope, since thrust vector changes Annual National V/STOL Forum, 27th, Washington, D. C., May induced flight path disturbances. (Author) 19-21, 1971, Preprint 554. 7 p. Members, $1.25; nonmembers, $2.00. A method is presented for the rapid evaluation of the potential A71-31102 Evaluation of rotor controls designed for for composite materials applied to V/STOL propfrotors. The results increased safety. Lawrence D. Barrett and John C. Mack (Boeing Co., are displayed in a form suitable for easy comparison with criteria and Vertol Div., Philadelphia, Pa.). American Helicopter Society, Annual for selection of those material options with the best potential. The National V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, parametric effect that material properties have on frequencies and Preprint 550. 10 p. Members, $1.25; nonmembers, $2.00. weight is determined using Southwell coefficients. Blades which meet Experience gained during analysis, design, and testing of failsafe the frequency requirements are then evaluated in terms of wength helicopter rotor controls is reviewed. Analysis of field experience and requirements. O.H. accident and discrepancy reports emphasized the need for damage- tolerant mechanical components with special features that make maintenance errors less likely to occur. Flight control experience in A71-31107 Factors affecting fuel control stability of a transport aircraft and design requirements of current helicopter turbine engine/helicopter rotor drive system. C. Fredrickson (Boeing specifications also helped formulate design guidelines. A mechanical- Co., Vertol Div., Philadelphia, Pa.), K. Rumford (Avco Corp., ly redundant rotor control system with inherent component failure Lycoming Div., Stratford, Conn.), and C. Stephenson (AVSCOM, St. warning is shown and discussed. From this design, four major Louis, Mo.). American Helicopter Society, Annual National V/STOL components were selected. These components were designed, fabri- Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 560. 10 cated and fatigue-tested. Test results were measured against the p. Members, $1.25; nonmembers, $2.00. criteria that secondary load paths should have fatigue ..ves many Despite positive results from all normal stability criteria, the times that of the normal reinspection interval, and that load path interaction of rotor, engine and control on the Boeing/Vertol condition should be determinable without special diagnostic equip- CH-47C helicopter resulted in unacceptable torque and fuel flow ment. The test specimens met these criteria. It is concluded that the oscillation in early flight test aircraft. A flight test program was designs represent practical approaches to failsafe and damage-tolerant undertaken and analytical capability at Lycoming and Vertol was rotor control components. (Author) upgraded to determine the cause of the oscillations. To analytically reproduce the phenomenon, inclusion of the hydraulic spring effect of the rotor blade lag damper, in addition to its normal damping A71-31103 Fail-safety for the H-46 rotor blade. George H. representation, was found to be necessary. Based on this analysis, Thompson and William L. Weiss (Boeing Co., Vertol Div., fuel control gain and time constant changes were suggested, Philadelphia, Pa .) . American Helicopter Society, Annual National evaluated in flight test, and a solution found. V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint (Author) 557. 8 p. Members, $1.25; nonmembers, $2.00. Description of a system to make the H-46 rotor blade fail safe which has been designed, fabricated, qualified, and placed in service. A71-31108 Turbofan engine considerations for reaction This system, designated ISIS (Integral Spar inspection System), is a drive rotors. R. J. Sullivan (Hughes Tool Co., Aircraft Div., Culver continuously functioning inspection system, integral to the rotor City. Calif.). American Helicopter Society, Annual National V/STOL blade, which will detect spar cracks in the early stages. A ground Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 561. 7 p. inspection at each rotor shutdown will provide ample warning of 8 refs. Members, $1.25; nonmembers, $2.00. impending blade fracture. This system has provided fail-safety for an Optimum combinations of major turbofan engine and rotor existing structure with little modification. The developmental testing variables necessary to obtain a good helicopter design are examined. and analytical. techniques resulting from this program have broad It is found that blade duct area must be,large enough to permit flow application to the achievement of structural fail-safety in existing as at a reasonable duct Mach number. The resultant rotor solidity must well as new helicopter component designs. F.R.L. not be so high as to cause excessive blade profile power. and rotor weight. In addition, fuel consumption must be considered. An arbitrary family of turbofan engines is studied in a simplified manner to illustrate the relationship of the variables. It is shown that a value A71-31 104 Size effects on the design of large rotor of rotor solidity that is a good compromise of aerodynamic. systems. Henry G. Smith (Hughes Tool Co.. Culver City, Calif.). thermodynamic, and mission considerations can be obtained with the American Helicopter Society, Annual National V/STOL Forum, newer, high-compression turbofan engines of low (0.7 to 0.8) bypass 27th, Washington, D.C., May 19-21, 1971, Preprint 552. 12 p. 11 ratio. O.H. refs. Members, $1.25; nonmqmbers, $2.00, Review of the fundamental effects of size upon the relationship of the rotor system structural and dynamic parameters to weight. Of A71-31109 VTOL propulsion system development. Paul particular concern are the significant deviations from structural and C. Setze, Jacob L. Browne, and Robert C. Turnbull (General Electric dynamic scaling similarity that occur as a result of the degree to Co., Aircraft Engine Group, Lynn, Mass.). American Helicopter which cube-square law weight growth is avoided. The effects of blade Society, Annual National V/STOL Forum, 27th, Washington, D.C.,
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May 19-21, 1971, Preprint 562. 11 p. Members, 51.25; nonmembers, stability and control, reduced noise and vibration levels, and a flight $2.00. path control system incorporating extended navigation and IF R Several major aspects that have to be taken into account in (instrument flight rules) capability, resulting in a reduced pilot designing VTOL propulsion systems powered by turboshaft engines workload. M.M. are discussed. General features of these systems and their operation are outlined. Problems involved in the system development - i.e., design requirements, development program planning, component development, system integration development and qualification - are A71-31113 United States Coast Guard evaluates hover- examined in detail. Detailed attention is also given to system craft. Thomas C. Lutton (U.S. Coast Guard, Air Cushion Vehicle vibration, in particular, to vibration analyses using a computer Evaluation Unit, San Francisco, Calif.). American Helicopter Sociery, Annual National V/STOL Forum, 27th, Washington, D. C., May model, and to vibration testing. O.H. 19-21, 1971, Preprint 572. 7 p. Members, $1.25; nonmembers, 52.00. When three Navy SK-5 air cushion vehicles became available in late 1969, the Coast Guard commenced an expanded ACV evaluation A71-31110 Strain gauge torquemeters for use in helicopter program. The first two hovercraft were scheduled for operational transmission systems. Dennis P. Hames {British Hovercraft Corp., evaluation in the San Francisco Bay area and the third for Arctic Ltd., Experimental and Electronic Laboratories, East Cowes, Isle of trials at Point Barrow, Alaska. Tentative results of the evaluation in a Wight, England). American Helicopter Society, Annual National number of fields are discussed including search and rescue, aids to V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint navigation, law enforcementloil pollution, marine safety, and 563. 11 p. Members, $1 25; nonmembers, $2.00. logistics. An analysis of the relative effectiveness of the ACV The use of a strain gauge torquemeter as the primary power compared to helicopters and boats is also presented. The greater indicating instrument in a helicopter gives the pilot a direct and speed advantage of the ACV over the Coast Guard’s patrol boats accurate indication of the torque in the transmission system, and makes it particularly attractive in response time and search area provides several advantages for the helicopter designer and operator. covered in responding to search and rescue. G.R. An accuracy of indication of plus or minus 1-1/2% of full load torque, under all operating conditions, has been achieved with production equipment. Resistance foil strain gauges are attached to A71-31114 Army/Navy operational evaluation of offshore the shaft transmitting torque. The electrical supply to the rotating discharge of containerships. L. J. McConnell (U.S. Army, shaft and the output signal from it are inductively coupled to an Washington, D.C.). American Helicopter Society, Annual National electronic amplifier unit through a rotating transformer assembly. V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint The pilot is given an immediate audible warning of overtorque. 573. 5 p. Members, $1.25; nonmembers, $2.00. Torquemeters operating at shaft speeds to 30,000 rpm are described. A detailed discussion of the offshore discharge of containerships G.R. by helicopter is presented. It is shown that while helicopters demonstrated a virtually all weather, day and night capability to transport the containers, the capability of the current helicopter is A71-31 1 11 Results of high-speed flight research with the limited to containers of ten tons gross weight. Z.W. high performance UH-1 compound helicopter. Waiter F 0. Sonneborn and Louis W. Hartwig (Bell Helicopter Co., Fort Worth, Tex.). American Helicopter Society, Annual National V/STOL Forum, 27th, Washington, D.C., May 19-21, 7971, Preprint 570. 1% A71-31115 AH-56A vehicle development. J. F. Johnston p. 6 refs. Members, 51.25; nonmembers, $2.00. Contract No. and J. R. Cook (Lockheed-CaliforniaCo., Burbank, Calif.). American DA-44-177-AMC-364(T). Helicopter Society, Annual National V/STOL Forum, 27h, This paper discusses a high-speed compound-helicopter flight Washington, D.C., May 19-21, 1971, Preprint 574. 11 p. Members, research program. This program was conducte’d to determine the $1 25; nonmembers, $2.00. behavior of rotors at combinations of advance ratios and advancing- The rotor stability and handling qualities of the AH-56A blade tip Mach numbers beyond those attainable in existing full-scale compound helicopter are discussed. Four different devzlopment wind tunnels. A level flight speed of 274 knots was achieved with a areas are considered, The first two involve the dynamics of rigid or two-bladed semirigid rotor. A four-bladed flexbeam rotor was also hingeless rotors: the 1P x 2P phenomenon of produced blade evaluated at speeds up to 220 knots. An integrated control system flapping and in-plane motions which compromised the blade feather- allowed inflight changeover from helicopter to airplane-typecontrols ing feedback at reduced rpm, and the ‘hop’ phenomenon at near - i.e., from tail rotor and longitudinal cyclic control to a rudder and a one-half cycle per revolution which involves both the cyclic and the stabilator with the longitudinal swashplate fixed. Results in the areas collective modes of rotor and body motion. The remaining two areas, of structural loads, vibrations, performance, control and stability, in which new data were added, concern antitorque rotor effective- and correlation of flight and wind-tunnel data are discussed. (Author) ness and pilot/vehicle matching for maximum roll rates in nap-of-the- earth flight. O.H.
A71-31112 The Boeing Model 347 advanced technology helicopter program. Frank H. Duke and W. Euan Hooper (Boeing Co., Vertol Div., Philadelphia, Pa.). American Helicopter Society, Annual National V/STOL Forum, 27th, Washington, D.C., May 19-21, 1971, Preprint 571. 10 p. Members, 51.25; nonmembers, $2.00. This program consists of an integrated effort covering analysis, simulation, wind tunnel, whirl tower and bench test, plus the modification of a CH-47 airframe to permit flight verification and demonstration of advanced technology. The program consists of two phases. The first phase will explore the capability of the pure helicopter configuration, and the second phase will investigate the potentials of the winged helicopter. The prime objective of the 347 program is to integrate recent transport helicopter experience with the latest technology and demonstrate a helicopter with improved
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N71-243'86
of the publ. 'Vidimost v Atmosfere' Leningrad, Gidrometeorol. Izd., 1966 (AD-719502; FSTC-HT-23-052-71) Avail: NTlS HC $6.00/MF $0.95 CSCL 412 The author gives a description of present-day ways of, determining visibility through the atmosphere. He explains how atmospheric transmissivity. the visibility of actual objects. and the range of visibility on landing an aircraft are measured. He emphasizes particularly the methods for determining the level of visibility. In a number of cases he concludes that problems which STAR ENTRIES he regards as being important have not yet been satisfactorily solved. Author (GRA)
N71-24379# Army Test and Evaluation Command, Aberdeen Proving Ground, Md. N71-24351# Army Foreign Science and Technology Center, MAINTENANCE TOOL SETS, AVIATION Final Report Charlottesville. Va. 16Dec. 1970 20 p PARACHUTE [PARASHYUT] (AD-719103; MTP-7-3-057) Avail: NTlS CSCL 1319 A. Khorobrykh 24 Sep. 1970 14 p Transl. into ENGLISH from Procedures are described for evaluating the adequacy of Starshina-Serzhant (USSR), no. 8,1969 p 20-22 maintenance tools sets. Considerations of tool set durability and (AD-719480: FSTC-HT-23-400-70) Avail: NTlS CSCL 1/3. Brief historical remarks concerning parachute development compatibility with aircraft maintenance characteristics are discussed. in the Soviet Union are followed by a functional description of the (Author) G RA basic components of standard personnel parachutes. Devices and methods employed to open parachutes, including manual and automatic methods are discussed and illustrated. Specific attention is devoted to a device which is pressure-controlled, with automatic N71-24385# Deutsche Gesellschaft fuer Luft- und Raurnfahrt. timing for canopy deployment. The application and role of the Stuttgart (Westtermany). parachute in areas other than aviation are discussed briefly. Author (GRA) HE LI COPTER FATI 0 UE TEST1 NG [BETRIEBSFESTIGKEITSPROBLEMEBE1 HUBSCHRAUBERN] Dec. 1970 187 p refs In GERMAN; ENGLISH summary Proc. of the DGLR Symp. on Helicopters and Propellers, Immenstaad, West Ger., 24 Jun. 1969 N71-24357# IIT Research Inst., Chicago, 111. (DLR-MITT-70-01) Avail: NTIS: ZLDl Munich: 38.85 DM AVIONICS INTERFERENCE PREDICTION MODEL . G. Morgan Annapolis, Md. Electromagnetic Compatibility Analysis CONTENTS Center Nov. 1970 140 p refs 1 DETERMINATION OF THE LIFETIME OF HELICOPTER (Contract F19628-70-C-0291) COMPONENTS R Prinz (DFVLR, Brunswick) p 7-76 refs (AD-718997; ESD-TR-70-286) Avail: NTlS CSCL20/14 An interference prediction model developed for use in 2 SrRUCTURAL STABILITY OF THE ROTOR SYSTEM evaluating expected interactions between avionics equipments on an OF THE HOT-GAS REACTION HELICOPTER DO 132 L Brenner airplane is described. The model is substantially automated and (Dornier-Werke, Friedrichshafen, West Ger ) p 77 -96 refs includes subroutines which calculate expected path losses between aircraft antennas and the rejection offered by the receivers to the 3 DYNAMIC CESTlNG OF HELICOPTER COMPONENTS undesired emissions from transmitters on the aircraft. An analysis H SCHUMACHER (Messerschmitt-Boelkow) p 97 - 123 of the interactions between the equipments installed on an FAA Sabreliner has been made using the prediction model and the 4 EVALUATION OF FLIGHT MEASUREMENTS AND results of the analysis are described. Requirements for expansion of THE PLOTTING OF LOADING COLLECTIVES H Strehlow the prediction model are established. Author (GRA) (MesserschmittBoelkow)and N Mihalcea (Messerschmitt-Boelkow) p 124-156 refs 5 STRUCTURAL STABILITY INVESTIGATIONS OF THE HELICOPTER VFW-H3 W Paul (Ver Flugtech Werke. Bremen) p 157-174 N71-24369# Army Test and Evaluation Command, Aberdeen Proving Ground, Md. NAVIGATION EQUIPMENT, AUTOMATIC Final Report 17 Dec. 1970 26 p refs (AD-7 19096; MTP-6-3-205) Avail: NTlS CSCL 17/7 N71-24386# Deutsche Forschungs- und Versuchsanstalt fuer Procedures are identified for service test evaluations of Luft- und Raumfahrt. 8runswtck (West Germany) Army sircraft navigation systems. Author (GRA) DETERMINATION OF THE LIFETIME OF HELlCOPfER COMPONENTS [DIE ERMITTLUNG DER LEBENSDAUER VON H U BSCHRAU BER BAUTEI LE N 1 Rudolf Prinz In DGLR Helicopter Fatigue Testing Dec 1970 p 7-76 refs In GERMAN Avail NTIS, ZLDl Munich 38.85 DM N71-24375# Army Foreign Science and Technology Center, Charlottesville. Va. A survey IS glven of methods used for the determination VISIBILITY IN THE ATMOSPHERE of the fatigue life of helicopter rotor blades exposed to vibrational stresses, present during normal flight conditions ESRO V. A. Gavrilov 28 Jan. 1971 390 p refs Transl. into ENGLISH
455 N71-24387
~-,1-24387# Dornier-Werke G m b H , Friedrichshafen (West The existing aviation requirements for weather radar, either Germany) ground-based or airborne. in connexion with performance criteria, range and accuracy, are reviewed. The detection and identification STRUCTURAL STABILITY OF THE ROTOR SYSTEM OF of regions of hail and turbulence associated with thunderstorms. THE HOT-GAS REACTION HELICOPTER DO 132 these being considered dangerous phenomena for aviation are [BETRIEBSFESTlGKE17SBETRACHTUNGEN AM discussed. It is shown through intensive surveys on hail detection ROTORSYSTEM DES that echo intensity, as an indicator of hail, observed using 10 cm HEISSGAS-REAKTIONSHUBSCHRAUBERS DO 1321 wavelength radar exhibited a similar trend to that observed using L Brenner In DGLR Helicopter Fatigue Testing Dec 1970 3 cm radar, but very little change in intensity with height. Several p 77-96 refs InGERMAN case studies of the probability of hail as a function of height are Avail NTIS. ZLDI Munich 38.85 DM also illustrated for assessment of hail. Brief mention is made of A survey is given of the operatlonal demands made on the use of airborne radar for detection of hail and the avotdance the rotor system DO 132, especially the rotor blades as well as the of turbulence by aircraft in flight. The question of measuring the determination of the structural stabllity under special conditions height of echoes observed by radar, which represents an index of ESRO storm activity is considered and the interpretation of echoes for different types of radar is discussed. The processing and transmission of radar information is discussed in detail and transmission of radar N71-24388# Messerschmitt-Boelkow G m b H Ottobrunn (West information to aircraft in flight is also considered. New techniques Germany) developed for radar observations are also presented. DYNAMIC TESTING OF HELICOPTER COMPONENTS [DYNAMISCHE ERPROBUNG VON Author (ESRO) HUBSCHRAUBERKOMPONENTEN] H Schumacher In DGLR Helicopter Fatiaue Testina Dec 1970 p 97-123 In GERMAN N71-24433# Army Natick Labs.. Mass. Avail NTIS, ZLDl Munich 38.85 DM A GENERALTHEOhY OF PARACHUTE OPENING A survey is given of the essential dynamic tests in connection Edward W. Ross, Jr. Jan. 1971 42 p refs with the development of the Messerschmitt-Boelkow BO 105 (AD-719698; USA-NLABS-TR-7 1-32-OSD) Avail: NTIS CSCL helicopter. as an example of a testing program, which may be more 113 generally applied to helicopter development ESRO A simple mathematical model of the opening behavior of parachutes is presented. The model predicts the drag and velocity as functions of time and also gives an estimate of opening time. The model is very general and applicable to almost any parachute. N71-24389# Messerschmitt-Bcelkow G m b HI Ottobrunn (West The characteristics of a specific parachute enter the model by Germany) means of certain constants that have to be chosen: Values of these constants are found for flat. circular parachutes, partly by estimation EVALUATION OF FLIGHT MEASUREMENTS AND THE PLOTTING OF LOADING COLLECTIVES [AUSWFRTUNG and partly by numerical experimentation. The resulting model of VON FLUGMESSERGEBNISSEN UND ERSTELLUNG VON the opening behavior of flat. circular canopies gives reasonable BELASTUNGSKOLLEKTIVEN] agreement with experiments for several parachutes of different sizes. H Strehlow and N Mihalcea In DGLR Hellcopter Fatigue Testing Insofar as generality and flexibility are concerned, this model seems to be superior to present methods of predicting opening behavior Pec 1970 D 124-156 refs In GERMAN of parachutes. Author (GRA) Avail: NTIS; ZLDl Munich: 38.85 DM Classification results and frequency analyses of flight load data of the Messerschmitt-Boelkow BO 105 helicopter are reviewed. N71-24446# Glasgow Univ. (Scotland). Dept. of Aeronautics The applicability to the solution of several structural stability and Fluid Mechanics. problems is pointed out. The applied evaluation methods and the THE ROLE OF HEAT CONDUCTION IN LEADING EDGE necesssry use of electronic data processing are briefly described. HEATING THEORY AND EXPERIMENT ESRO T. R. F. Nonwdler, H. Y. Wong, and S. R. Aggarwal London Aeron. Res. Council 1970 52 p refs Supersedes ARC- 31445 (Contract PD/48/09/ADM) N71-24390# Vereinigte Flugtechnische Werke G.m.b.H., Bremen (ARC-CP-1126; ARC-31445) Copyright. Avail: NTIS; HMSO: 75p; (West Germany). BIS: $3.00 STRUCTURAL STABILITY INVESTIGATIONS OF THE The effect of heat conduction of material on the temperature HELlCOPTER VFW-H3 distribution in the vicinity of a wing leading edge in hypersonic [BETRIEBSFESTIG KEITSUNTERSUCHUNGEN VON flight is investigated. The theory is based on a conducting plate KOMPONENTEN DES FLUGSCH RAUB E RS VFW- H3] subjected to aerodynamic heating. It is found that the role played W. Paul In DGLR Helicopter Fatigue Testing Dec. 1970 by the conductivity of the material and the leading edge thickness p 157-174 InGERMAN in moderating the nose temperature is very significant., Detailed Avail: NTIS; ZLDl Munich: 38.85 DM discussions of the numerical solutions for various shapes of leading Structural stability tests of components of the Vereinigte edge aie given. An experimental technique has been developed by Flug Werke helicopter family H3/H5 are reported on. One of the which a number of models representing a wing leading edge can major problems during the development stage was the detection be tested and the results thus obtained are compared with those of a sufficient security against rotor blade fatigue, including the connections. ESRO predicted by the theory. Author (ESRO)
N71-24394 World Meteorological Organization. Geneva N71-24447# European Space Research Organization, Paris (Switzerland). (France). USE OF WEATHER RADAR FOR AVIATION EUROPEAN SPACE RESEARCH ORGANISATION General H. Treussart. W. B Beckwith, S. G. Bigler, K. Otanl, V. V. Kostarev Report, 1969 et ai 1970 92 p refs Its Tech. Note 110 1970 204 p (WMO-264-TP-148) Copyright. Avail: Issuing Activity Avail: NTIS
456 N71-24483
This report summarizes the scientific results achieved by 25Jan. 1971 18 p the ESRO satellites (IRIS. AURORAE, HEOS 1) and from the (AD-719101; MTP-7-3-051) AvuI: NTlS CSCL 13/1 sounding rocket campaign. A status report is given of satellites Procedures are described for evaluating aircraft ventilation under development. namely BOREAS, TD-1, HEOS-A2. and ESRO-4 heating,, moisture and contamination control. cooling and heating and the feasibility studies presented on future satellites in the equipment or any combination of these systems. The evaluation is telecommunications, meteorological and aeronautical fields. A descrihed under simulated tactical conditions. Author (GRA) summary is also given of the maqagement problems involving buildings. staff, and legal matters. ESRO N71-24479# Army Aviation Systems Test Activity, Edwards AFB. Calif. EVALUATION OF FUELFLOWMETER N71-24451# Army Test and Evaluation Command, Aberdeen INSTRUMENTATION Final Report, 5 Aug. -20 Oct. 1970 Proving Ground, Md. Albert L. Winn and Robert P: Jefferis Jan. 1971 30 p refs APPROACH SYSTEMS (TERMINAL AIR TRAFFIC CONTROL (AD-719280; USAAST-70-33) Avail: NTlS CSCL 1412 FACILITY) Final Report Flight tests on the Flow Technology lnc. standard line 15 Dec. 1970 24 p refs turbine flow transducer were conducted between 5 August and 20 (AD-719104: MTP-7-3-066) Avail: NTiS CSCL 1717. October 1970 to determine its acceptability as a test instrument. The A basic guide for preparation of test plans for terminal evaluation was conducted at Edwards Air Force Base, California, by air traffic control facility equipment is given. Provides for testing the US Army Aviation Systems Test Activity. Ground calibrations shelters containing ground to air communication, acquisition showed that the sensor can be used with precision equal to equipment. and meteorological equipment. Compatibility of the shelter present flow measurement methods. The testing consisted of 2.9 with associated transportation media are considered. flight hours with the measurement systems mounted in a UH-1 C Author (GRA) helicopter. The Flow Technology sensor performance was compared to that obtained with standard Potter and Revere flight test systems. Results show that the sensor is acceptable as a flight test N71-24452# Army Test and Evaluation Command, Aberdeen instrument. The indicator sensitivity is excellent and there was no Proving Ground, Md degradation of meter performance with variations in engine power AIRCRAFT DEFOGGER/DEFROSTER (TRANSPARENT or flight conditions. Although the indicator scale range was suitable AREAS) Final Report for this test, the range is not large enough to be operable on all 25 Jan 1971 18 p refs Army aircraft. Author (GRA) (AD-719 109, MTP-7-3-522) Avail NTlS CSCL 1 /3 Procedures are described for evaluating aircraft defogger/defroster equipment operated in conjunction with N71-24482# National Physical Lab., Teddington (England). environmental control units. or as an independent electrical system Aerodynamics Div. Author (GRAI THE BEHAVIOUR OF THE LEADING-EDGE VORTICES OVER A DELTA WING FOLLOWING A SUDDEN CHANGE OF INCIDENCE N71-24457# Army Test and Evaluation Command, Aberdeen N. C. Lambourne, D. W. Bryer. and J F. M. Maybrey London Aeron Proving Ground, Md. Res. Council 1970 47 p refs Supersedes NPL-AERO-1294: COMPATIBILITY OF AVIATION MATERIEL WITH RELATED ARC-31056 EQUIPMENT Final Report (ARC-R/M-3645: NPL-AERO-1294. ARC-31056) Copyright Avail. 8 Dec. 1970 11 p refs NTIS; HMSO: f: 1.25; BIS: $4.50 (AD-719107; MTP-7-3-509) Avail: NTlS CSCL 1/3 The transient behavior of leading-edge vortices over a delta The document defines procedures for evaluating the wing subject to a sudden change of incidence is of importance in compatibility of aviation materiel with related equipment. understanding the wing loadings that can occur in unsteady Compatibility aspects are physical and technical characteristics, conditions of flight. In the experiments reported changes of incidence installation and removal. 'operation and performance, and have been imposed on delta-shaped plates by application of a maintenance. Incompatibility ranges from a simple nuisance factor constant-velocity plunging motion for a limited time; other related to complete negation of the item under test, and concerned aircraft, unsteady motions are discussed in the appendix. Cine records of armament, avionics and personnel materiel. Author (GRA) particle tracks and of dye filaments in a water tunnel have been analyzed to trace the time history of vortex centres in cross-flow planes following the application of step-changes of incidence. The flows for various combinations of initial incidence, planform, plunging N71-24459# Army Test 'and Evaluation Command, Aberdeen velocity. and chordwise position have been examined. Results Proving Grbund. Md. indicate that after the start of the plunge an effectively steady vortex SERVICING UNITS (AVIATION) Final Report system is established over the plate in a time approximately equal 10Dec. 1970 18 p to that required for one chord length of relative forward travel. (AD-719102; MTP-7-3-055) Avail: NTlS CSCL 1/3 Where comparisons can be made, Dore's theoretical calculations of Procedures are defined for evaluating the degree of the manner in which the vortices move show fair agreement with effectiveness of both portable and self-propelled ground servicing the experiment. Effects of the transient movements of the vortices units for Army Aircraft. This procedure is concerned with on lift distribution are discussed and the inference is drawn that improvements and modification to existing equipment, as well as the changes in the distribution of wing loading occurring for an new types of heaters. auxiliary power, and servicing equipment increase of incidence are not simply reversed when the incidence resulting from change in aircraft configuration or methods of tactical is decreased. Author (ESRO) operations. Author (GRA)
N71-24483# National Physical Lab.. Teddington (England). Div. N71-24461# Army Test and Evaluation Command, Aberdeen of Numerical and Applied Mathematics. Proving Ground Md. NUMERICAL EVALUATION OF THE DOWNWASH ENVIRONMENTAL CONTROL UNIT (ECU) Final Report INTEGRALFOR A LIFTING RECTANGULAR PLANFORM
457 N71-24488
Valerie A. Ray and G. F. Miller Dec. 1970 24 p refs Lynn B. Fricke, Peter T. Wooler. and Henty Ziegler Wright-Patternon (NPL-Ma-90) Copyright. Avail: NTlS AFB, Ohio AFFDL Dec. 1970 200 p A method is described for the accurate evaluation of the (Contract F33615-69-C-1602) downwash integral of Multhopp's lifting surface theory for wings (AD-718123: AFFDL-TR-70-154-Vol-4) Avail: NTlS CSCL 20/4 of rectangular planform subjected to very general loadings. In the A low speed wind tunnel test of a four-foot diameter circu!ar form in which it was origi.nally derived the integral defining the plate model with up to three exhausting jets was conducted to downwash alpha(x.y) at points on the wing surface is unsuitable for determine surface static pressure distributions, jet paths. and jet numerical calculation because of the presence of a strong singularity decay characteristics in the presence of a crossflow. Three-jet of the integrand at the point (x.y). The basis of the present method configuration data were obtained with the jets exiting normal to the is to transform the integral by removing certain terms which plate for a number of velocity ratios and sideslip angles. As a result (subject to natural assumptions regarding the form of the loading of this investigation. several conclusions are deduced pertaining to function alternate theta(x,y) can be evaluated in closed form, while the interaction of multiple jets exhausting into a crossflow. the remaining integral is only weakly singular and is amenable to Author (GRA) numerical evaluation. The method has been embodied in a KDF 9 program which computes the downwash, for arbitrary values of the N71-24492# Northrop Corp., Hawthorne, Calif. Aircraft Div. aspect ratio. to high precision. Tables and digrams are appended, giving values of the downwash at a representative set of points A WIND TUNNEL INVESTIGATION OF JETS EXHAUSTING on the wing for several aspect ratios and loadings. A basic aim INTO A CROSSFLOW. VOLUME 1: TEST DESCRIPTION has been to provide a definitive set of results of substantial AND DATA ANALYSIS precision against which results obtained by other methods (possibly Lynn 6.Fricke. Peter T. Wooler, and Henry Ziegler Wright-Patterson AFB, Ohio AFFDL Dec. 1970 448 p refs applicable to more general shapes) may be tested. Author (ESRO) (Contract F33615-69-C-1602) (AD-7 18122; AFFDL-TR-70-154-Vol-1) Avail: NTlS HC $6.00/MF $0.95 CSCL 2014 A low speed wind tunnel test of a four-foot diameter circular N71-24488# Royai Aircraft Establishment, Farnborough plate model with up to three exhausting jets was conducted to (England). Aerodynamics Dept. determine surface static pressure distributions, jet paths, and jet THE TWO-DIMENSIONAL CHARACTERISTICS OF A 12.2 decay characteristics in the presence of a crossflow. Data were PERCENTTHICK RAE 100 AEROFOICSECTION obtained for the one-jet configuration with the jet exiting at a D. S. Woodward London Aeron. Res. Council. 1971 71 p number of angles to the plate and at various velocity ratios and refs Supersedes RAE-TR-68303; ARC-31 374 sideslip angles. Two-jet arrangements were tested with the jets (ARC-R/M-3648; RAE-TR-68303: ARC-31374) Copyright. Avail: exiting normal to the plate for three different spacings between the NTIS; HMSO: sl.75: BIS: $6.30 two jets and at a number of velocity ratios and sideslip angles. The 12.2% thick RAE 100 airfoil section was chosen as Three-jet configuration data were obtained with the jets exiting being likely to fulfil the requirements for the basic airfoil section normal to the plate for a number of velocity ratios and sideslip of a series of sweptback wings designed to provide fundamental angles. As a result of this investigation. several conclusions are information on the high lift and stalling behavior of swept wing deduced pertaining to the interaction of multiple jets exhausting into aircraft. The choice was based upon previously published work on a crossflow. The test model, instrumentation. test procedure, and the stall characteristics of twodimensional airfoils. and the results reduction and accuracy of the test data are discussed in this presented show thar the desired behavior at high lift has been volume. A summary and discussion of the test results are also obtained. The measurements of the airfoil characteristics were presented. Author (GRA) obtained by surface pressure plotting. Not only were the overall forces and moments obtained from these measurements, but also the pressure distributions were analyzed in three ways intended to N71-24498# Glasgow Univ. (Scotland). provide information on the changes from the potential flow pressure A NEW SERIES OF LOW-DRAG AEROFOILS distribution which are produced by the displacement thickness of T. R. F. Nonweiler London Aeron. Res. Council 1971 107 p the boundary layer. Author (ESRO) refs Supersedes ARC-30528 (ARC-R/M-3618; ARC-30528) Copyright. Avail: NTIS; HMSO: $22.70: BIS: $10 A series of low drag airfoils, modelled roughly on the NACA N71-244898 Deutsche Forschungs- und Versuchsanstalt fuer 6-series. is described. It appears to offer theoretical advantages over Luft- und Raumfahrt, Stuttgart (West Germany) Abteilung its progenitor, and allows flexibility in the choice of leading-edge Aerodynamik thickness and trailing-edge angle. Airfoils of this series are SURVEY OF DIFFERENT MODELS FOR COMPUTING specified five parameters, and the aerodynamic and geometrical THE FLOW OF A LIFTING ROTOR [UEBERBLICK UEBER by characteristics of about 1000 of the sections are listed. The VERSCHIEDENE MODELLE ZUR BERECHNUNG DER mathematical derivation of their shape (by the Lighthill method) is ROTORDURCHSTROEMUNG] described in detail. and an ALGOL 60 procedure for the computation Alfred Kussmann Dec 1970 74 p refs In GERMAN, ENGLISH of their ordinates is included; care has been taken to construct this summary procedure so that it may be of general use in other applications (DLR-MITT-70-19) Avail NTIS. ZLDl Munich 13.70 DM A survey of the essential features of several methods for of the Lighthill method of design. Author (ESRO) computing the induced velocity field and blade loads of a lifting rotor is given, especially in the forward flight regime. with particular consideration of the different wake model configurations N71-24500# Deutsche Forschungs- und Versuchsanstalt fuer Author (ESRO) Luft- und Raumfahrt. Goettingen (West Germany). Abteilung Raumfahrt-Aerodynamik. AN INVESTIGATION OF A WAVE-RIDER AT LOW REYNOLDS NUMBERS [UNTERSUCHUNG EINES N71-24491# Northrop Corp.. Hawthorne, Calif. Aircraft Div. WELLENREITERS BE1 KLEINEN REYNOLDSZAHLEN] A WIND TUNNEL INVESTIGATION OF JETS EXHAUSTING G. Hefer Sep. 1970 32 p refs In GERMAN: ENGLISH summary INTO A CROSSFLOW. VOLUME 4: ADDITIONAL DATA (DLR-FB-70-46) Avail: NTIS: ZLDl Munich: 9.60 DM FOR THE THREE JET CONFIGURATION A Nonweiler-wing was investigated at rarefied flow conditions
458 N7 1-24571 in order to determine the influence of small Reynolds numbers on PITCHING-MOMENT DERIVATIVES ON A SERIES OF THREE the aerodynamic properties of wave-riders. The measurements. DELTA WINGS IN INCOMPRESSIBLE FLOW (IN FOUR comprising pitot pressure surveys in the flow field. static pressure PARTS) measurements. and force measurements, were performed in the London Aeron. Res. Council '1971 78 p refs Part 1 slip flow region at Mach numbers of 11.5 and Reynolds numbers supersedes NPL-AREO-1276: ARC-30359; Pt. 2, NPL-AERO-1274; from 5000 to 50,000. Author (ESRO) ARC-30357. Pt. 3, NPL-AERO-1275; ARC-30358; and Pt. 4. NPL-AERO-1289: ARC-30955 Copyright. Avail: NTIS; HMSO: f2;BIS: $7.20 (ARC-R/M-362B-Pt-1-4; NPL-AERO-1276; NPL-AERO-1274; N71-24555# Litchford Systems, North Port, N.Y. NPL-AERO-1275; NPL-AERO-1289 et al) NEW DEVELOPMENTS IN SCANNING BEAM LANDING GUIDANCE SYSTEMS, PART2 Final Annual Report CONTENTS: George B. Litchford Wright-Patterson AFB. Ohio AFFDL Dec. 1. PART 1: MEASUREMENTS OF THE OSCILLATORY 1970 255 p refs PITCHING MOMENT DERIVATIVES ON A DELTA WING WITH (Contract F33615-69-C-1110) ROUND LEADING EDGES IN INCOMPRESSIBLE FLOW L. (AD-7 18972; L-AF-04-Pt-2; AFFDL-TR-69-107-Pt-2; AR-2) Avail: Woodgate p 3-21 ref? NTIS CSCL 1717 2. PART 2: MEASUREMENTS OF THE OSCILLATORY Design details are given of a CW microwave scanning-beam PITCHING-MOMENT DERIVATIVES ON A SLENDER system operating at C and bands. Many of the available design Ku SHARP-EDGED DELTA WING IN INCOMPRESSIBLE FLOW L. options are noted that apply to the solution of certain engineering Woodgate p 22-38 refs problems. One of the virtues of the plan is that several options 3. PART 3: MEASUREMENTS OF THE OSCILLATORY exist for rapid validation of all critical matters. Consequently the PITCHING-MOMENT DERIVATIVES ON A SHARP-EDGED DELTA total risks, both economically and technically. now appear much WING AT ANGLES OF INCIDENCE FOR WHICH VORTEX lower than previously. Possible designs of angle-data modulation, BREAKDOWN OCCURS L. Woodgate p 39-57 refs dual-band receivers, angle-data processors, etc., are reviewed as are several validation tests and ekperiments now needed to tie down 4. PART 4: MEASUREMENTS OF LIFT, DRAG, AND engineering parameters before a firm national signals-in-space PITCHING MOMENT ON A SERIES OF THREE DELTA WINGS standard can be approved. The important advances in the last L. Woodgate and A. S. Halliday p 58-75 refs year toward planning a national system for aircraft landing in all environments suited to all physical types and operations of aircraft are identified. Author (GRA) N71-24570# National Physical Lab.. Teddington (England). Aerodynamics Div. N71-24565# Royal Aircraft Establishment, Farnborough PART 1: MEASUREMENTS OF THE OSCILLATORY (England). Aerodynamics Dept. PITCHING-MOMENT DERIVATIVES ON A DELTA WING LOW-SPEED WIND-TUNNEL TESTS ON A SWEPTBACY WITH ROUND LEADING EDGES IN INCOMPRESSIBLE WING MODEL (BUCCANEER MARK 1) WITH BLOWING AT FLOW THE WING LEADING EDGE AND BLOWING OVER THE L. Woodgate In its Meas. of the Oscillatory Pitching-Moment FLAPS AND DROOPED AILERONS Derivatives on a Series of Three Delta Wings in Incompressible S. F. J. Butler London Aeron. Res. Council 1971 54 p refs Flow 1971 p 3-21 refs Supersedes RAE-TR-67223; ARC-29976 Copyright. Avail: NTIS; HMSO: f2; BIS: $7.20 (ARC-R/M-3655: RAE-TR-67223; ARC-29976) Oscillatory pitching-moment derivatives have been measured Low-speed longitudinal stability measurements are described on a round-leading-edged delta wing of aspect ratio 1.484 and of on a fifth-scale half-model including some comparisons with thickness to chord ratio 0.06. Mean incidence was varied from 0 complete-model tests and the measured aircraft performance. Shroud to 15 deg. and frequency parameter and Reynolds number, based blowing over the trailing-edge flap. and drooped aileron nearly on the mean chord, were varied from 0.2 to 0.1 and from 1.28 doubled the C sub I (lift coefficient) increment, to as much as 1.O, million to 2.56 million respectively. Comparisons are made with with adequate aileron roll control effectiveness at a mean aileron similar measurements on a sharp-edged delta wing of the same angle of up to 30 deg. Trimming reduced the lift increments by aspect ratio. Differences between the results for the two models are about 20 per cent. Despite considerable aerodynamic objections found for both pitching axes used in the tests. From the results associated with the thin wing and small nose radii, and integral for h = 1.5 mean chord and from surface flow patterns. it (nondeflecting) leading-edge blowing arrangement was specified for appeared that for low angles of incidence the round leading edge aircraft structural reasons. Although an acceptable arrangement suppressed the development of vortex flow sufficiently for it to was developed. this necessitated the selection of a safe compromise have no effect on either.deriv.ative. Above alpha = 5 deg. vortex position for the blowing nozzle to avoid adverse compressibility flow was gradually established, giving a change in ea&, deridatiw effects at aircraft takeoff and landing speeds. Typically. a stalling with incidence similar to that found on the sharp-edged model. incidence of 20 deg [C sub I max (maximum lift coefficient) = 1.81 Author (ESRO) was achieved for the proposed takeoff configuration 30 deg flap; 20 deg mean ail was achieved for the proposed takeoff configuration (30 deg flap; 20 deg mean aileron droop). With the prescribed N71-24571# National Physical Lab., Teddington (England). integral leading edge, wing pitch-up at the stall was not avoided. Aerodynamics Div. although initial wing flow separations were confined to the inboard PART 2: MEASUREMENTS OF THE OSCILLATORY wing. In general. the aircraft high-lift performance confirms the PITCHING-MOMENT DERIVATIVES ON A SLENDER results of the tests on this half-model. Author (ESRO) SHARP-EDGEP DELTA WING IN INCOMPRESSIBLE FLOW L. Woodgate In its Meas. of the Oscillatory Pitching-Moment Derivatives on a Series of Three Delta Wings in Incompressible Flow 1971 p 22-38 refs Copyright. Avail: NTIS; HMSO: f2: BIS: $7.20 N71-24569# National Physical Lab., Teddington (England). Oscillatory pitching-moment derivatives have been measured Aerodynamics Div. by an inexorable forcing method on a delta wing of aspect ratio MEASUREMENTS OF THE OSCILLATORY
459 N71-24572
0.654 in pitching motion. Mean incidence has been varied from Ming H. Tang Washington May 1971 43 p refs 0 to 75 deg, frequency parameter from 0.2 to 1.0, and Reynolds (NASA-TM-X-2286; ti-650) Avail: NTlS CSCL 01A number from 1.28 million to 2.30 million. The derivatives showed Outboard fin loads and rudder hinge moment measurements large and approximately linear variations with incidence. were obtained from a 1/8 scale model of the M2-F3 lifting body Comparisons are made with previous measurements on a delta wing vehicle tested in the 11 foot transonic wind tunnel. The Zests were of higher aspect ratio also with sharp edges. In general, the conducted at Mach 0.50 to 7.30. The effects of variations in numerical values of the derivatives and the variation in the derivatives rudder deflection. upper flap deflection, lower flap deflection, and due to changes in the mean incidence, frequency of oscillation, and angles of attack and sideslip were studied. The left outboard fin Reynolds number are smaller for the more slender wing. loads increased with increase in angle of attack. Mach number. Author (ESRO) rudder deflection. lower flap deflection, and negative sideslip and decreased with increasing upper flap deflection. The rudder hinge moment increased with increase in rudder dflection and. generally. with Mach number. Author N71-24572# National Physical Lab., Teddington (England). Aerodynamics Div. PART 3: MEASUREMENTS OF THE OSCILLATORY PITCHING-MOMENT DERIVATIVES ON A SHARP-EDGED N71-24582*# Nations1 Aeronautics and Space Administration. DELTA WING AT ANGLES OF INCIDENCE FOR WHiCH Langley Research Center, Langley Station, Va. VORTEX BREAKDOWN OCCURS NOISE MEASUREMENTS FOR A THREE ENGINE L. Woodgate In its Meas. of the Oscillatory Pitching-Moment TURBOFAN TRANSPORT AIRPLANE DURING CLIMBOUT Derivatives on a Series of Three Delta Wings in Incompressible AND LANDING APPROACH OPERATIONS Flow 1971 p 39-57 refs, W. Latham Copeland and Lorenzo R. Clark Washington May Copyright. Avail: NTIS; HMSO: $22; BIS: $7.20 1971 54 p refs Pitching-moment derivatives have been measured on a (NASA-TN-D-6137; L-5994) .4vail: NTlS CSCL 01B sharp-edged delta wing of aspect ratio 1.484 for a range of Noise measurements have been made for a three engine incidence from alpha = 20 to 35 deg. For alpha = 30 and 35 deg. turbofan transport airplane during climbout and landing approach vortex breakdown occurred above the wing surface. Some operations in which the airplane operating procedures were carefully numerically-low values of both the stiffness and damping derivatives controlled. These controlled procedures included an orderly were obtained for alpha = 30 deg at low frequency parameters scheduling of operating variables such as engine power, speed, and these are attributed to vortex breakdown. Corresponding altitude, and flap settings. The results of these studies are presented measurements at higher frequency parameters were practically for seven climbout operations involving various climb speeds, flap unaffected. Flow visualization showed that the pitching oscillation settings, and engine power settings and for three landing approach led to an oscillation of the streamwise position of the vortex operations involving various glide-slope angles. In general, the breakdown but, for the small amplitude of oscillation used, had no results from the climbout studies indtcated that the lower noise effect on the mean peition of the breakdown. Author (ESRO) levels (6 GI3 to 14 dB) were associated with profiles employing lower engine powers during second-segment climb. It was also found that, for a given climb profile and climb rate, slightly higher noise levels are associated with operations employing fixed flaps N71-24573# National Physical Lab., Teddington (England). than with a specified flap retraction schedule. The results from Aerodynamics Div. landing approach studies indicated that generally lower noise levels PART 4: MEASUREMENTS OF LIFT, DRAG, AND PITCHING were associated with the steeper glide slopes. For these steeper MOMENT ON A SERIES OF THREE DELTA WINGS glide slopes. noise reductiois attained (4 dB to 9 dB) resulted from L. Woodgate and A. S. Halliday In its Meas. of the Oscillatory both the increased altitude and the lower engine powers. Author Pitching-Moment Derivatives on a Series of Three Delta Wings in Incompressible Flow p 58-75 refs Copyright. Avail: NTIS; HMSO: E2; BIS: $7.20 The measurements were made on three 6 percent thick N71-24586*# Boeing Co.. Seattle, Wash. delta wings; wing (1) had an aspect ratio of 1.484 and all its LOW WING LOADING STOL TRANSPORT RIDE edges were sharp, wing (2) also had an aspect ratio of 1.484 and SMOOTHING FEASIBILITY STUDY Final Report the leading edges were rounded, and wing (3) had an aspect ratio of 8 Feb. 1971 77 p refs 0.654 with all edges sharp. The values of C sub I (lift coefficient). (Contract NAS1-10410) C sub m (pitching moment coefficient), and the derivative\delta C (NASA-CR-1 11819; D3-8514-2) Avail: NTlS CSCLOlC sub m/delta alpha obtained are compared with values predicted Results of an analytical study to determine the feasibility by a theory of Garner and Lehrian which takes into account the of providing satisfactory ride qualities using modern controls effects of leading-edge flow separation. The values obtained for technology on a high performance, low wing loading STOL aircraft are wing (1) were in good agreement with similar measurements from given. The aircraft configuration was designed to be competitive other sources, C sub I being slightly larger than theory and C sub with present high speed jet aircraft economics and block times and m in reasonable agreement with theory. The round leading edge to meet proposed noise requirements. Author of wing (2) had the predictable effect of slightly reducing the value of C sub I and numerically increasing the value of C sub m for the mid-root-chord axis, as compared with the sharp-edged wing. Wing (3) produced values much lower than both theory and reported values for flat-plate deltas of similar aspect ratio. Author (ESRO) N71-24603# Army Test and Evaluation Command, Aberdeen Proving Ground, Md. FLIGHT LINE ANALYZERS N71-24581*# National Aeronautics and Space Administration. 7 Jan. 1971 20 p refs Flight Research Center, Edwards. Calif. (AD-7 19675; MTP-6-3-0901 Avail: NTlS CSCL 1/3 VERTICAL-FIN LOADS AND RUDDER HINGE-MOMENT Maintenance of complex aircraft systems requires the ability MEASUREMENTS ON A 1/8 SCALE MODEL OF THE M2F3 to determine the completion of systems on the flight line. The LIFTING BODY VEHICLE AT MACH NUMBERS FROM 0.50 document defines procedures for field testing analyzers utilized in TO 1.30 testing systems and fault isolating components. Author (GRA)
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N71-24651*# National Aeronautics and Space Administration. (NASA. Marshall Space Flight Center. Huntsville. Ala.) p 423-450 Langley Research Center, Langley Station. Va. ref NASA SPACE SHUTTLE TECHNOLOGY CONFERENCE. VOLUME 3: DYNAMICS AND AEROELASTICITY Washington Apr. 1971 448 p refs Conf. held at Langley Station. Va.. 2 - 4 Mar. 1971 N71-24659*# National Aeronautics and Space Administration. (NASA-TM-X-2274: L-7739) Avail: NTlS HC $6.00/MF $0.95 Ames Research Center, Moffett Field, Calif. CSCL 20K THICK HIGH ASPECT RATIO WING, PART 2 Larry L. Erickson. Bruno J. Gambucci and Phillip R. Wilcox In its CONTENTS: NASA Space Shuttle Technol. Conf., Vol. 3 Apr. 1971 1. RECENT STUDIES OF SPACE SHUTTLE MULTIBODY p 201-229 refs DYNAMICS S. A. Leadbetter and L. A. Kiefling p 1-25 ref Avail: NTlS HC$G.OO/MF$0.95 CSCL 20K Transonic flutter and buffet results are presented for two 2. 5PACE SHUTTLE TPS PANEL VIBRATION STUDIES elastic models of a proposed space-shuttle straight wing. The H. D Carden, B. J. Durling. and W. C. Walton, Jr. p 27-48 models were tested at Mach numbers from 0.6 to 1.1 at varlous refs dynamic pressures and at angles of attack up to 18 deg. Zero 3. APPROXIMATE ANALYSIS AND DYNAMIC TESTS degree angle of attack flutter occurred in a narrow Mach number FOR A THERMAL PROTECTION SYSTEM PANEL I. U. Ojalvo and range centered at about Mach 0.85. Stall flutter was not observed N. Arcas (Grumman Aerospace Corp.. Bethpage, N.Y.) p 49-93 although several instances of low torsional damping were noted. refs At conditions of maximum buffet intensity, model peak dynamic 4. SPACE SHUTTLE LIQUID DYNAMICS F. M. Bugg bending moments ranged up to 80% of the corresponding static and N. S. Land p 95- 120 bending moments. Author 5. SOME LANDING GEAR CONSIDERATIONS FOR SPACE SHUTTLE VEHICLES 8. R. Hanks and T. J. W. Leland p 121-154 refs N71-24660*# National Aeronautics and Space Administration. 6. RECENT STUDIES OF EFFECTS OF GROUND WINDS ON SPACE SHUTTLE VEHICLES R. W. Hess. W. H. Reed, 111, and Ames Research Center, Moffett Field, Calif. J. T. Foughner. Jr. p 155- 173 refs APPLICATION OF RECENT PANEL FLUTTER RESEARCH 7. EFFECTS OF SPACE SHUTTLE CONFIGURATION TO THE SPACE SHUTTLE. PART 1: BOUNDARY LAYER ON WING BUFFET AND FLUTTER PART 1: LAUNCH VEHICLE AND HYPERSONIC EFFECTS Peter A. Gaspers, Jr. In its NASA Soace Shuttle Technol. Conf. WITH TIP FIN R. C. Goetz p 181-199 refz Vol.3 Apr. 1971 p 231-245 refs 8. THICK HIGH ASPECT RATIO WING, PART II L. Avail: NTlS HC$6.00/MF$0.95 CSCL2OK L. Erickson, B. J. Gambucci. and P. R. Wilcox (NASA. Ames Published experimental and theoretical results concerning panel Research Center, Moffett Field, Calif.) p 201 -229 refs flutter are reviewed and some very recent and very significant theoretical results for large boundary layer thickness are presented. 9. APPLICATION OF RECENT PANEL FLUTTER RESEARCH In addition, some theoretical results for panel flutter at hypersonic TO THE SPACE SHUTTLE. PART 1: BOUNDARY LAYER AND speeds which show nonlinear destabilizing effects are reviewed. HYPERSONIC EFFECTS P. A. Gaspers, Jr. (NASA. Ames Resea.-h Finally the significance of these results and their application to the space shuttle are discussed. Author Center, Moffett Field, Calif.) p 231 -245 refs
10. APPLICATION OF RECENT PANEL FLUTTER RESEARCH TO THE SPACE SHUTTLE. PART II: INFLUENCE OF EDGE N71-24661*# National Aeronautics and Space Administration. CLIPS AND FLOW ANGULARITY H. L. Bohon and C. P. Shore Langley Research Center, Langley Station, Va. p 247-264 refs APPLICATION OF RECENT PANEL FLUTTER RESEARCH 11. BUFFET RESPONSE Ut SPACE SHUTTLE LAUNCH TO THE SPACE SHUTTLE. PART 2: INFLUENCE OF CONFIGURATIONS AS DETERMINED BY TESTS OF AN EDGE CLIPS AND FLOW ANGULARITY AEROELASTIC MODEL L. Muhlstein. Jr. (NASA. Ames Research Herman L. Bohon and Charles P. Shore In its NASA Space Center. Moffett Field, Calif.) p 265-291 Shuttle Technol. Conf., Vol 3 4pr. 1971 p 247-264 refs
12. PRELIMINARY MEASUREMENTS AND FLOW Avail: NTlS HC $6.0U/ iwt- $0.95 CSCL 20K VISUALIZATION STUDIES OF PRESSURE FLUCTUATIONS ON The parameters that are known contributors to aeroelastic SPACE SHUTTLE CONFIGURATIONS C. F. Coe. J. B. Dods, Jr.. problems in light of current TPS designs are examined. In particular, R. C. Robinson, and W. H. Mayes p 293-314 ref the nature of boundary conditions and flow angularity as they affect panel flutter are discussed. The data are not restricted to 13. THE Et-PECTS OF PARAMETER VARIATION ON INFLIGHT metallic panels but, in, fact, may also apply to panels with external WIND LOADING A. C. Mackey (NASA. Manned Spacecraft insulation. Emphasis, however, is placed on the orthotropy of the Center, Houston, Tex.) p 3 15- 332 surface structure and the deflectional flexibility of the clips which 14. TECHNOLOGY: PRELIMINARY INVESTIGATION OF connect it to the primary structure. Author LOAD AND MODAL SUPPRESSION FOR SPACE SHUTTLE B. J. Kuchta (Gen. Dyn./Convair. San Diego. Calif.) p 333-357
15. SHUTTLE POGO REVIEW J. E. Harbison (NASA. N71-24662*# National Aeronautics and Space Administration. Marshall Space Flight Center, Huntsville, Ala.) p 359-399 Ames Research Center, Moffett Field. Calif. BUFFET RESPONSE OF SPACE SHUTTLE LAUNCH 16. SPACE SHUTTLE ACOUSTIdS S. H. Guest (NASA. CONFIGURATIONS AS DETERMINED BY TESTS OF AN Marshall Space Flight Center, Huntsville, Ala.) p 401 -422 AE ROE LAST1C MODEL Lado Muhlstein. Jr. In its NASA Space Shuttle Technol. Conf., Vol 17. PRELIMINARY VIBRATION DESIGN AND TEST CRITERIA 3 Apr. 1971 p 265-291 rnNSIDERATIONS FOR THE SPACE SHUTTLE H. J. Bandgren Avail: NTlS HC$6.00/MF$0.95 CSCL20K Preliminary results of a series of tests designed to investigate
46 1 N71-24663
the buffet response of a typical straight wing and a delta wing The design and development of a graphite heated, COI~,...- space shuttle vehicle (SSV) launch configuration recently completed running, Mach 20 wind tunnel, which operates with Reynolds at the Ames Research Center are presented. The purpose of these numbers between 6 x 10,000 and 5 x 1,000,000 per meter, are tests was to determine what are some of the potential buffet described. Preliminary calibrations are presented for a contoured problems of a typical SSV launch configuration. 4uthor and a conical nozzle and for the performance of the centerbody diffuser.& _electron beam probe is used to measure test section conditions. Author (ESRO) N71-24663*# National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. PRELIMINARY MEASUREMENTS AND FLOW N71-24689*# National Aeronautics and Space Administration. VISUALIZATION STUDIES OF PRESSURE FLUCTUATIONS Lewis Research Center, Cleveland. Ohio. ON SPACE SHUTTLE CONFIGURATIONS DESIGN POINT CHARACTERISTICS OF A 15-TO-80 kWe Charles F. Coe. Jules E. Dods, Jr.. Robert C. Robinson, and William NUCLEAR- REACT0 R B RAYTON- CYCLE POWER SYSTEM H. Mayes In its NASA Space Shuttle Technol. Conf.. Vol. 3 Apr. Paul T. Kerwin [1971] 9 p refs Proposed for presentation at the 1971 p 293-314 ref 1971 Intersociety Energy Conversion Engineering Conf.. Boston, Avail: NTlS HC$6.00/MF&u.95 CSCL2OK 3-6Aug. 1971 Results of research in flow characteristics and pressure (NASA-TM-X-67811) Avail: NTlS CSCL 18L fluctuations on space shuttle launch and reentry configurations are A study of 15-80 kWe nuclear reactor powered Brayton reported. The investigations to date have consisted of pressure cycle power system is presented. The system has a design turbine fluctuation measurements at transonic speeds on 0.01- and inlet temperature of 1150 F based on the use of a zirconium- hydride 0.025-scale models of straight- and delta-wing launch configurations reactor but is also required to be capable of operation at and fluorescent oil flow tests of 0.008-scale models of straight- turbine inlet temperatures up to 1600 F with an advanced reactor. and delta-wing launch configurations over a Mach number range Considerations involved in the selection of cycle parameters, of 0.8 to 2.0. The Bolt, 8eranek and Newman tests have been working fluid, pressure level, and turbomachinery rotational speed directed to the definition of unsteady pressures for reentry conditions. are discussed, Siie and weight estimates. predicted design- They consisted of flow visualization studies and measurements of point performance. and required radiator area are presented. pcessure fluctuations on both 0.004-scale and 0.0077-scale models Author of a low-cross-range orbiter configuration at alpha = 60 deg for Mach numbers of 2.5 and 4.0. Author N71-24690*# National Aeronautics and Space Administration Lewis Research Center, Cleveland. Ohio. N71-24664*# National Aeronautics and Space Administration. PREDICTED PERFORMANCE OF A 15-80 kWe REACTOR Manned Spacecraft Center, Houston, Tex: BRAYTON POWER SYSTEM OVER A RANGE OF OPERATING THE EFFECTS OF PARAMETER VARIATION ON INFLIGHT CONDITIONS WIND LOADING D. C. Guentert and R. L. Johnsen [I9711 10 p refs To be Alden C. Mackey In ,IS NASA Space Shuttle Techn.,. Conf., Vol. presented at 1971 Intersoc. Energy Conversion Eng. Conf., Boston. 3 Apr.1971 p 315-332 3 - 6 Aug. 197 1 ; sponsored by SA€ Avail: NTlS HC$6.00/MF$0.95 CSCL20/4 (NASA-TM-X-67833) Avail: NTlS CSCL 18L Performance, controllability. and structural loads were A computer simulation of a 15-80 kWe nuclear reactor Brayton investigated to maximize the payload in space shuttle operation. The cycle power system designed for a turbme inlet temperature of parameters: wing incidence angle, control system gains. commanded 1150 F was used to study the steady-state performance of the attitude history, and winds are considered to affect boost loads and system at turbine inlet temperatures between 1050 and 1600 F. performance. Their effects are presented in graphs. It is concluded The low end of the temperature range IS of interest in applications that the means for reducing structural loads are available. and using a zirconium hydride reactor heat source, while the 1600 F structural loading must be considered in payload maximization temperature assumes the use of an advanced reactor. analyses. F.O.S. Cycle-parameter effects and predicted system efficiency and re- quired radiator area are presented over a range of compressor inlet temperatures and turbine inlet temperatures. The perform- ance over a range of power levels is also presented. Author N71-24669# Army Aeromedical Research Lab.. Fort Rucker. Ala. THE USE OF HIGH INTENSITY XENON LIGHTING TO ENHANCE US ARMY AIRCRAFT DAY/NIGHT CONSPICUITY N71-24691*# National Aeronautics and Space Administration. John K. Crosley, William E. McLean, Ronald G. Tabak, and Robert Lewis Research Center, Cleveland, Ohio. W. Bailey Jan. 1971 32 p. refs MOTOR STARTING TECHNIQUES FOR THE 2-TO-15 kW (AD-718639; USAARL-71-13) Avail: NTlS CSCL.O1/2 BRAYTON SPACE POWER SYSTEM In-flight studies were performed to compare the effectiveness L. J. Gilbert. J. S. Curreri. and D. A. Cantoni [1971] 12 p of aircraft-mounted, high-intensity Xenon flashtube lights for refs Proposed for presentation at the 1971 lntersociety Energy increasing the conspicuity of small trainer helicopters during both Conversion Engineering Conf.. Boston. 3-6 Aug. 1971 daytime and nighttime flights. Twenty-eight subjects rated both (NASA-TM-X-67819) Avail: NTlS CSCL 18L lighted and non-lighted aircraft visibility as viewed from the ground The 2-15 kilowatt Erayton space power system has been and from air to air in differing flight modes. Data are presented effectively started by motoring the rotating unit. This Brayton to indicate the increase in aircraft conspicuity available through the power system generates 1201208 volts, 1200 hertz electrical power qoplication of this type of lighting. Author (GRA) at a rated speed of 36,000 rpm. The system is designed for a turbine inlet temperature of 1600 F (1 145 K) and can be operated N71-24675# Imperial Coll. of Science and Technology, London with a variety of heat sources such as a nuclear reactor or (England). Dept. of Aeronautics. radioisotope. By applying 20 volts line-to-neutral. 400 hertz electrical THE IMPERIAL COLLEGE GRAPHITE HEATED power to the alternator terminals at standstill, the rotating unit can HYPERSONIC WIND TUNNEL be motored to a speed of 12.000 rpm in about 20 seconds. Upon J. K. Harvey. R. W. Jeffery. and D. C. Uppington Jan. 1971 removal of the input electrical power, the system self-accelerates 46 p refs Sponsored by Min. of Aviation Supply to its rated speed, provided that the turbine inlet temperature is (IC-AERO-71-01] Avail: NTlS 875 F (741 K) or higher. Author
462 N71-24709
N71-24692* National Aeronautics and Space Administration. volume. Experimental results from Mach numbers of 6 to 20 are Flight Research Center, Edwards, Calif. presented for a series of trapezoidal bodies; the cross section of TRAVERSING PROBE Patent the body giving best lift drag ratio differs from that indicated in Edwin J. Saltzman. Meryl D. De Geer. Stanley C. Plamowski. and earlier work. A simple sin(2) deficiency method is presented for Robert Grant Green. inventors (to NASA) Issued 20 Sep. 1966 predicting pressures on blunt shapes; the method appears to yield (Filed 25 Jun. 1964) 9 p CI. 73-389 results comparable to more .elaborate methods requiring machine (NASA-Case-XFR-02007; US-Patent-3,273,399; computation. Author US-Patent-AppCSN-378080) Avail: US Patent Office CSCL 20D An instrument which makes it possible to obtain an accurate boundary layer profile using only a limited number of probes, usually one or two, is described. The instrumentation required for recording and measuring is (1) an instrument for measuring and N71-24706*# National Aeronautics and Space Administration. recording the pressure conditions encountered by each probe. and Langley Research Center, Langley Station, Va. (2) an instrument for determining and recording the position of the FLUTTER AND UNSTEADY LIFTTHEORY In its Performance and Dvn. of Aerospace probe with respect to the vehicle surface. Inasmuch as the probes are E. Carson Yates. Jr. mounted in a fixed position to a single mast only one instrument is Vehicles 1971 p 289-374 refs required for probe position even though two probes are employed. Avail: NTlS HC$9.00/MF$0.95 CSCL2Ob Two embodiments of a traversing mechanism for extending and A brief introduction to the aeroelastic problems of aircraft retracting the probe are disclosed. is given. Emphasis is on the flutter of lifting surfaces, and the most Official Gazette of the U.S.Patent Office. commonly used technique for the theoretical determination of flutter stability boundaries is shown. Classical theoretical methods are presented for evaluating the required oscillatory aerodynamic forces in subsonic. supersonic, and hypersonic speed ranges. Some N71-24702*# National Aeronautics and Space Administration. comparisons of theoretical and experimental results are included. Langley Research Center, Langley Station, Va. Rigorous mathematical developments are not emphasized. STABILITY AND CONTROL CHARACTERISTICS OF STOL Author AND V/STOLAIRPLANES Joseph R. Chambers In its Performance and Dyn. of Aerospace Vehicles 1971 p 1-69 refs N71-24707*# National Aeronautics and Space Administration, Avail: NTlS HC$9.OO/MF$0.95 CSCLOlA Langley Research Center, Langley Station, Va. Some of the stability and control characteristics common EFFECTS OF AEROELASTICITY ON STATIC to most V/STOL airplanes are discussed. In particular, specific AERODYNAMIC DERIVATIVES stability and control problems of deflected slip stream, tilt wing. John E. Lamar In its Performance and Dyn. of Aerospace Vehicles ducted propeller, and jet powered vehicles are covered. The 1971 p 375-438 refs contents include a variety of experimental and analytical techniques Avail: NTlS HC$S.OO/MF$O.& CSCLPOD presently used to analyze the stability and control characteristics of The effects of aeroelasticity on some static longitudinal. V/STOL airplanes. Author derivatives are considered. Different solution techniques are presented and from these techniques; one, the force-slope method (called herein). is selected by which the effects of static aeroelasticity may be computed. In order to use the force slope N71-24703*# National Aeronautics and Space Administration. method, the aerodynamic (only subsonic speeds are considered) and Langley Research Center, Langley Station, Va. structural influence coefficient matrices must first be determined. METHODS OF OBTAINING STABILITY DERIVATIVES These methods are developed in some detail, after which solutions M. J. Queijo In its Performance and Dyn. of aerospace Vehicles for a typical configuration are given. Author 1971 p 71-101 refs Avail: NTlS HC$S.OO/MF$0.95 CSCL2OD Various methods of obtaining aerodynamic derivatives are N71-24708*# National Aeronautics and Space Administration. reviewed. These methods include wind-tunnel tests, aerodynamic Langley Research Center. Langley Station, Va. theory, and extraction from flight tests. with the emphasis being RESPONSE OF FLEXIBLE AIRPLANES TO ATMOSPHERIC on flight tests. Two techniques for extracting derivatives from flight TURBULENCE are covered in sufficient detail to indicate the procedures involved. Kermit G. Pratt In its Performance and Dyn. of Aerospace These methods are a strict least squares approach and an iteration Vehicles 1971 p 439-503 refs technique. References are listed for additional background and Avail: NTlS HC$9.00/MF$0.95 CSCLOIA details of various techniques. Author Current random process theory methods for the estimation of the theoretical average frequency of exceeding peak responses of various levels are described, and calculated results are compared with results from flight measurements. Contents include: (1) the N71-24704*# National Aeronautics and Space Administration. statictical characteristics of the airplane responses and of the Langley Research Center, Langley Station, Va. turbulence velocities, (2) the relationship of these characteristics in DESIGN OF BODIES FOR LOW DRAG AND HIGH terms of power spectral density (PSD) functions and frequency PERFORMANCE IN PRACTICAL HYPERSONIC FLIGHT responses to a sinusoidal gust field of various wavelengths, (3) the E. S. Love In its Performance and Dyn. of Aerospace Vehicles relation of PSD functions to random time functions and to statistical 1971 p 103-174 refs parameters, (4) methods of calculating frequency responses and Avail: NTlS HC$9.00/MF$0.95 CSCL2OO aerodynamic forces due to gusts. and (5) the synthesis of the Some topics related to body shaping for minimum drag responses experienced during routine flight operations. Author and improved performance at hypersonic speed are presented. Implications of the most frequently assumed pressure laws are reviewed from the view of practical flight regimes, and solutions expressed in exponential residuals are presented for inviscid minimum N71~24709*#National Aeronautics and Space Administration. drag power-law bodies (simple and complex) for a wide range of Langley Research Center. Langley Station, Va. fineness ratio. Analytical results and comparisons with experiment GUST ALLEVIATION are given for constraints of length and diameter and legnth and William H. Phillips In its Performance and Dyn. of Aerospace
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Vehicles 1971 p 505-553 refs GEOSTATIONARY SATELLITES AND AIRCRAFT Summary Avail: NTIS HC$9.00/MF$0.95 CSCL2OD Report A discussion is presented of the response of an airplane C. E. Wernlein (Westinghouse Elec. Corp., Baltimore. Md.) Nov. to turbulence, including techniques for the alleviation of lateral and 1970 50 p refs longitudinal motions. A simplified theoretical treatment of the (NASA-TM-X-65508; X-490-71-72) Avail: NTlS CSCL 171 longitudinal response to vertical gusts, which allows calculation of the The propagation and system factors influencing the validity of effects of various types of gust alleviation systems, is presented. an L band communication system between geostationary satellites Flight experiments on various gust alleviation systems are reviewed. and aircraft terminals, are discussed. Also discussed are the effects A brief discussion is given of the application of these systems to of ionospheric and tropospheric absorption, scintillation. range bias. different types of airplanes. Finally. methods of refinement of the Faraday rotation, earth reflected multipath, and system noise. simplified theory to include effects of horizontal gusts, unsteady lift E.H.W. effects, and isotropic turbulence are described. Author
N71-24914*# National Aeronautics and Space Administration. Goddard Space Flight Center, Greenbelt, Md. N71-24849# Japan Atomic Energy Research Inst.. Tokyo. ABSORPTION EFFECT OM VHF PROPAGATION BETWEEN NONDESTRUCTIVE TESTING OF AIRCRAFT STRUCTURES SYNCHRONOUS SATELLITE AND AIRCRAFT Summary BY RADIOISOTOPES Report Oct. 1970 153 p refs In JAPANESE; ENGLISH summary Edward J. Mueller (Westinghouse Elec. Corp., Baltimore. Md.) Dec. (JAERI-Memo-4163) Avail: AEC Depository Libraries 1970 50 p refs The preparation and radiological characteristics of Tm- 170 (NASA-TM-X-65507;X-490-71-44)Avail: NTIS CSCL 178 and lr-192 gamma sources, and the nondestructive testing of Ionospheric and tropospheric absorption, in terms of structural parts for aircraft using gamma sources, are discussed. geographical contour, are discussed for the very high frequencies in Author (NSA) an aeronautical satellite system. The North Atlantic region was chosen as the test area. The system comprises two geostationary satellites. Conclusions indicate no allowances need be made for N71-24869*# Massachusetts Inst. of Tech., Cambridge. tropospheric absorption. but that auroral and ionospheric absorption AN AIRSPACE UTILIZATION MODEL FOR V/STOL should be considered in North Atlantic des,ign. Results also show TERMINAL OPERATIONS that aeronautical routing. operational procedures. and Dorian Albert DeMaio (M.S. Thesis) Jan. 1971 95 p refs telecommunications systems design must be considered. E.H.W. (Contract NASl2-2081; Grant NGR-22-009-010: Contract DOT-TSC-5) (NASA-CR-118515; TE-45) Avail: NTIS CSCLOlB N71-24920# H.r Regisrration Board. London (tngland). A computer graphics display program is developed for use CIVIL AIRCRAFT AIRWORTHINESS DATA RECORDING tn terrlmal area'audies and V/STOL approach and departure path PROGRAM: EN ROUTE USE OF FLAP synthesis. The computer processes inputs describing the terminal Apr. 1970 12 p ref area and accompanying constraints and displays on 2 . Tthode ray (ARB-TN-99: CAADRP-TR-18) Avail: NTlS tube the airspace utilization model, a three dimensional image A survey of current practices relating to en-route use of representation of the constraints at a given altitude. Extensive flap indicates that flaps are used for descent or holding whether machine operator interaction is provided to select various constraint or not clearance for this has been obtained. On the two aircraft criteria. to plan approaches and departures and to check the results considered, the maximum indicated air speed for flap appears to through viewing and teletype output. The program is general and be used as target spsed and exceedances, though small, are may be applied to a number of terminal areas. The programs' frequent. Author applicability and usefulness is demonstrated in the analyses of Several proposed VTOL port sites in the Northeast Corridor. Author
N71-24882# National Aviation Facilities Experimental Center. N71-24925# National Transportation Safety Board. Washington, D.C. Atlantic City. N.J. TECHNICAL EVALUATION OF DUAL INPUT REPORT OF THE NATIONAL TRANSPORTATION SAFETY TRANSPONDER Final Report,Jul. 1969 -May 1970 BOARD Annual Report to Congress, 1970 17 Mar. 1971 61 p refs Jules E. Blaze; Apr. 1971 78 p refs (FAA-NA-71-39: FAA-RD-71-18) Avail: NTlS (AR-4) Avail: Issuing Activity The Dual Input Transponder (DIT) was evaluated to determine The activities of the Transportation Safety Board for 1970 if it. in conjunction with upper and lower aircraft antennas. could are reported. Among the transportation safety's list of 10 worst resolve existing Air Traffic Control Radar Beacon System (ATCRBS) enemios are: alcohol. ineffective 'packaging' of motorists and pilots. antenna coverage problems by minimizing aircraft antenna shielding youth and highway fatalities, and induced pilot error. Safety in phenomena. Flight tests of the DIT and other comparative aviation and surface transportation is discussed. A summary of transponder-antenna configurations were conducted and included investigations and recommendations is included. F.O.S. several types of manuevers intended to place the test aircraft in numerous shielding attitudes. Results of the test program indicated that the DIT effectively minimized the loss of transponder replies N71-24948* National Aeronautics and Space Administration. caused by shielding of the antennas and provided essentially Electronics Research Center, Cambridge, Mass. uninterrupted antenna coverage. A limited number of tests with two SATELLITE AIDED VEHICLE AVOIDANCE SYSTEM Patent independently operated transponders and two antennas indicated Ernest R. Steele. inventor (to NASA) Issued 22 Dec. 1970 (Filed that this configuration resulted in less apparent shielding effects 28 Mar. 1969) 19 p CI 343-1 12: Int. CI. G01s5/02 than the DIT system. Author (NASA-Case-ERC-10090: US-Patent-3,550.1 29; US-Patent-AppCSN-811542) Avail, US Patent Office CSCL 17G A method and an apparatus for warning aircraft pilots of the N71-24913*# National Aeronautics and Space Administration. proximity of another aircraft are detailed. The apparatus comprises Goddard Space Flight Center, Greenbelt, Md. a system including a satellite for transmitting a synchronizing signal A 1540 TO 1660 MHz PROPAGATION BETWEEN end means onboard the aircraft for receiving said synchronizing
464 N71-25050 signal. Means are also included onboard said aircraft for generating N71-25032# Air Force Systems Command, Wright-ratterson a response signal in response to said synchronizing signal and for AFB. Ohio. Foreign Technology Div. opening a gate upon the receipt of said synchronizing signal for STABILITY AND CONTROLLABILITY OF SUPERSONIC receiving said response signal. The gate is maintained open for a AIRCRAFT, 1970 predetermined period of time that establishes a threat detection V. Lutskii et al 4 Dec. 1970 14 p Transl. into ENGLISH from zone so that a response signal from another aircraft passes Aviatsiya i Kosmonavtilta (Moscow), no. 1, 1970 p 15 - 18 through the gate only if the response signal is received during the (AD-719804; FTD-HC-23-599-70) Avail: NTlS CSCL 113 predetermined period of time. The received response signal is To a great extent, the maneuverability of a supersonic fighter applied to an indicator to indicate the proximity of the other aircraft is determined by the value of the maximal available overloads or is used to compute the threat of collision and derive a display which vary in relation to the flight speed and height. In its of a suitable avoidance maneuver. turn, the maximal available overload is affected by the maximally Official Gazette of the U.S. Patent Office permissible value of lift coefficient and the reserve C(subscript y)--ranging from the balancing value in straight flight to the maximally permissible value. Satisfactoly parameters of stability and N71-24964# Hawaii Univ.. Honolulu. Information Sciences controllability are retained in the delta-wing fighters under condition Program. of aerodynamic buffeting. Author (GRA) THE THEORY OF DIGITAL PROCESSING OF STOCHASTIC SIGNALS FOR USE IN AVIONIC SYSTEMS ON-BOARD AIR FORCE AIRCRAFT Final Scientific Report, 1 Jan. 1967’-31 Dec. 1970 N71-25048# Air Force Systems Command, Wright-Patterson N. Thomas Gaarder Mar. 197 1 17 p refs AFB, Ohio. Foreign Technology Div. (Grant AF-AFOSR-1251-67) FIRST BORN OF SOVIET AVIATION SCIENCE (AD-719822: CER-PRE-70101; AFOSR-TR-71-0494) Avail: NTlS A. I. Makarevskii et al 15 Jan. 1970 29 p Transl. into ENGLISH CSCL 914 from Priroda (USSR), no. 5. 1970 p 2- 11 The report contains a description of the University of Hawaii (AD-719802; FTD-MT-24-292-70) Avail: NTlS CSCL 1/2 research program in the theory of digital processing of stochastic The article briefly traces the role of the Central signals for use in avionic systems oh-board Air Force aircraft. The Aerohydrodynamic Institute im. Prof. N. E. Zhukovskiy (TsAGI) in the majority of new signal Processors in avionic communication and development of Soviet military and civilian aviation. It discusses control systems are being realized digitally. They are realized digitally some of the technical problems encountered in the development of because the advent of the present integrated circuit technology has subsonic, transonic, supersonic, and hypersonic flights and steps led to inexpensive. reliable. flexible, and light weight systems. The undertaken to solve them. Some of the TsAGl wind tunnels and discrete nature of these digital processors coupled with the their role in aircraft development are described. Author (GRA) stochastic nature of their input signals imposes constraints upon such systems that should be considered in the design of such systems. Author (GRA) N71-25049# Air Force Systems Command, Wright-Patterson AFB. Ohio. Foreign Technology Div. STABILITY AND CONTROLLABILITY OF SUPERSONIC N71-24996 Kansas Univ.. Lawrence. AIRCRAFT. 1969 EMPENNAGE LOADS ON T-TAIL TRANSPORTS -Q V. Lutskii et al 4 Dec. 1970 10 p Transl. into ENGLISH from CONTl NUOUS ATMOSP HE RIC TURBU LEMCE Aviatsiya I Kosmonavtika (USSR). no. 1 1,1969 p 1 1 - 18 Henry Morgan Dodd, Jr. (Ph.D. Thesis) 1969 104 p (AD-719803; FTD-HC-23-597-70) Avail: NTlS CSCL 1/3 Avail: Univ. Microfilms Order No. 70-1 1014 During the piloting of supersonic aircraft with swept wings. Empennage loads on T-tail transporis were investigated it is important to take into account a reduction in the overload for the case of response to continuous atmospheric turbulence. A stability margin in the transonic range of speeds at relatively small real-time analog-digital computer simulated the airplane dynamics angles of attack. This is connected with the unfavorable and determined the importance of nonlinear aerodynamic loads development of flow separation on the wing and the horizontal caused by simultaneous veRical and lateral gusts. These nonlinear empennage under conditions of the formation and development of aerodynamic effects were determined from wind-tunnel tests in a supersonic zones of flow and shock waves; such o tiundition transonic dynamics tunnel. The simulated model was assumed to sometimes leads to a spontaneous abrupt rise in the overloading at be a rigid airplane with five degrees of freedom (2 longitudinal. 3 lateral). and results were obtained for both yaw damper on and these speeds. Author (GRA) damper off flight conditions. Bending moments on the stabilizer, fin tip. and fin root were chosen as typical loads, with emphasis on how loads m.ight be altered by the nonlinear effects. Dissert. Abstr. M71-25050# Royal Aircraft Establishment. Bedford (England). Aerodynamics Dept. FLIGHT TESTS TO INVESTIGATE THE PROBLEMS QF STEEP APPROACHES BY STOL AIRCRAFT N74-25024*# Techtran Corp., Glen Burnie. Md. C. 0. O’Leary and N. V. Slatter London Aeron. Res. Council AVIATION AND ASTRONAUTICS IN THE USSR 1970 43 p refs Supersedes RAE-TR-69277; ARC-31849 A. A. Izmaylov, ed. Washington NASA May 1971 652 P (ARC-CP-1138; RAE-TR-69277; ARC-31849) Copyright. Avail: refs Transl. into ENGLISH of the book ‘Aviatsiya i Kosmonavtika NTIS; HMSO: 60p; 61s: $2.40 SSSR Moscow, Mil. Press, 1968 p 1 - 599 Steep approach tests with a Varsity and an Andover aircraft (Contract NASw-1695) are described. Using the Varsity aircraft, 243 visual approaches (NASA-TT-F-13142) Avail: NTlS HC $9.00/MF $0.95 CSCL were flown in a statistical experiment which included variations of 050 approach angle, speed. height of entry to the approach, glide path The history of the development of aviation in the U.S.S.R. guidance and pilots. A statistical analysis of the effects of the is reviewed. Starting with aviation in prerevolutionary Russia, the variables on various approach performance parameters was carried stages during the periods of the civil war. building socialism, World out and the significant results are illustrated and discussed. Tests War 2. and postwar period are discussed with the birth and with the Andover aircraft were on a smaller scale and were development of astronautics. Lists of aviation heroes of the Soviet primarily concerned with the final phase of the anoroach and Union are also included. F.O.S.
465 N71-25053
landing. The most important results of the tests are that steep N71-25073# Advisory Group for Aerospace Research and approaches can be accurately and consistently made using a Development. Paris (France). simple form of glide path guidance and landing distances can be REPORT OF THE HIGH REYNOLDS NUMBER WIND decreased without any apparent increase in variability of performance. TUNNELSTUDY GROUP OF THE FLUID DYNAMICS PANEL Author (ESRO) AQr. 1971 24 p refs ~A~ARD-AR-35-71)Avail: NTlS The working group considered transonic wind tunnel performance and operating characteristics required to support N71-25053# Lockheed Missiles and Space Co.. Sunnyvale. Calif. evolution of military and civil, aeronautical and aerospace systems SCANNING SYSTEMS FOR THERMALVIEWERS during the coming decade. These considerations, along with a E. la. Karizhenskii et al [1971] 6 p Transl. into ENGLISH from review of experience on model testing at transonic speeds. led to Optiko-Mekh. Prom. (Leningrad), no. 9, 1970 p 39-42 the conclusion that the NATO nations should acquire, as soon as (AD-719854) Avail: NTlS CSCL 1715 possible, two types of new wind tunnels. One tunnel should Some questions associated with the development of scanning duplicate transonic flight Reynolds numbers and have a run time on systems for thermal viewers are examined. Recommendations are the order of one second. The second should have a 16 ft test made for the selection of such systems. Author (GRA) section and should provide Reynolds numbers that are 3 or 4 times the maximum presently available, with a run time on the order of 10 seconds. It was also concluded that AGARD should support current research and development in design, operation and test N71-25060# Aerospace Medical Research Labs., Wright-Patterson techniques in transonic tunnels of the continuous. conventional AFB, Ohio. blowdown and Ludwieg tube type, and that AGARD should MEASUREMENT AND ANALYSIS OF C-5A INTERIOR encourage expansion of these activities in the future. Author ACOUSTlC ENVIRONMENTS D U RI N G FLIGHT OPERATIONS Final Report,Jul. -Aug. 1970 Justus F. Rose, Jr. Oct. 1970 11 p refs (AD-719746; AMRL-TR-70-110) Avail: NTlS CSCL20/1 M71-25080# Advisory Group for Aerospace Research and Interior sound pressure levels produced by the C-5A aircraft Development, Paris (France). were measured at sixty-six locations where crew/passenger EXTREME VALUE ANALYSIS AND ITS APPLICATION TO personnelgwould typically be located during operational missions. e. g. VERTICAL ACCELERATIONS MEASURED ON Conditions ranged from aircraft preflight through maximum endurance TRANSPORT AIRPLANES OFTYPE C-130 cruise at an altitude of 31,000 feet. These data were used to Otto Buxbaum (Lab. fuer Betriebsfestigkeit) Mar. 1971 31 p compute A-weighted and C-weighted overall sound levels, permissible refs. Presented at 31st Meeting of the Panel on Environ. Statist. exposure times with and without ear protection and preferred Data of AGARD, Tonsberg, Norway, 1-6 Nov. 1970 speech interference tevels. The measured data were grouped by (AGARD-R-579-71) Avail: NTlS location/condition and each major compartment in the aircraft The interpretation of cumulative frequency distributions of evaluated for human exposure to the environment. The major problem measured flight loads can be increased significantly by an additional area is in the cargo compartment where the high noise levels are extreme value analysis. This method not only leads to a higher such that for any appreciable exposure time, ear protection must reliability in fatigue design but may be used also for a prediction be worn to prevent risk of permanent hearing impa...nent. The of extreme loading conditions and for a description of the effect public address system in the cargo compartment is inadequate as of airplane and flight parameters on loads, as is demonstrated for presently configured and coupled with the high noise levels cannot c.g. vertical accelerations and gust velocities measured on airplanes be effectively used to brief passengers during missions. of type C-130. Author Author (GRA)
N71-25065# Royal Aircrafi Establishment. Bedford (England). Aerodynamics Dept. N71-2504)2# Air Force Systems Command, Wright-Patterson A PILOTED SIMULATOR STUDY OF A JET VTOL AFB, Ohio. Air Force Flight Dynamics Lab. AIRCRAFT IN PARTIALLYJET-BORNE FLIGHT PROCEEDINGS OF THE AIR FORCE CONFERENCE ON K. P. King and A. McPherson London Aeron. Res. Council 197 1 FATIGUE AND FRACTURE OF AIRCRAFT STRUCTURES 67 p refs Supersedes RAE-TR-68301; ARC-31 163 AND MATERIALS :ARGR/M-3647; RAE-TR-68301; ARC-31 163) Copyright. Avail: Sep. 1970 898 p refs Conf. held at Miami, 15- 18 Dec. 1969 NTIS; HMSO: E 1.75; BIS- $6.30 (AD-719756: AFFDL-TR-70-144) Avail: NTlS HC $9.00/MF A Simulation of a small jet VTOL aircraft has been used $0.95 CSCL 1/3 to examine the principles of controlling such aircraft in the partly The document is comprised of papers presented at the Air jet-borne regime. An investigation of three alternative techniques Force Conference on Fatigue of Aircraft Structures and Materials, for controi at constant speed was made, from which the pilots sponsored by the Air Force Flight Dynamics Laboratory (AFFDL) were able to select a single control technique that was effective and the Air Force Materials Laboratory (AFML), Air Force from the lowest speed simulated (40 kt) to the highest (150 kt). Systems Command. The purpose of the Conference was to discuss The preferred technique was to use thrust to control.,f)ight path technological advancements in fatigue and fracture theory. The and thrust vector angle to control airspeed while using attitude Conference was comprised of ten technical sessions (including two (controlled by the elevator) to make fine adjustments to both flight panel discussions) entitled The Role of Materials in Structures: path and airspeed. A preliminary study of techniques for performing Fundamentals 1 + II; Criteria; Fracture I + II: Phenomena I + 11: the transition between wing-borne and jet-borne flight was then Analysis: Design and Service Experience. A total of fifty-six technical made. Although computation limitations precluded transitions to papers were presented. Author (GRA) speeds below 40 kt, some valuable information was gained. In particular, a number of transitions were performed successfully, and without great difficulty, while following an ILS beam. As a result of these tests. it is believed that jet VTOL aircraft with adequate N71-25133# Army Foreign Science and Technology Center, stability may have a greater potential than had been anticipated for Charlottesville. Va. operating in poor weather, without the complicated flight-director SOVIET HELICOPTERS [SOVETSKIE VERTOLETY] systems and automatic controls that have generally been thought 18 Feb. 1971 11 p Transl. into ENGLISH from the Russian to be necessary. Author (ESRO) (AD-719585: FSTC-HT-23-1063-70) Avail: NTlS CSCL 1 /3
466 N71-25396
Brief descriptions are presented for the V-10(Mi-10). Ka-25K. required to burn fuels of different compounds in rurbbjet or injection KA-26 and KA-22 helicopters. Author (GRA) burners. Equations were developed to calculate the air requirements in turbojet and injection systems when changing feed gases of known density and compositions. Author (GRA) N71-25196# Committee on Science and Astronautics (U.S. House). NASA AUTHORIZATION, 1972, PART4 N71-25362*# Massachusetts Inst. of Tech.. Cambridge. Washington GPO 1971 325 p refs Hearings on H.R. 3981 Aeroelastic and Structures Research Lab (Superseded by H.R. 7109) before Comm. on Sci. and Astronaut., PERTURBATION AND HARMONIC BALANCE METHODS 92d Congr., 1st Sess.. No. 2.18 and 23 Mar. 197 1 FOR NONLINEAR PANEL FLUTTER Technical Report, 11 Avail: Subcomm. on Advan. Res. and Technol. Dec. 1969-15 Mar. 1971 Statements and testimony are presented on NASA research Luigi Morino, Ching-Chiang Kuo. and John Dugundji Mar. 1971 and program management facilities, tracking and data acquisition, 107 p refs space research technology, and nuclear power and propulsion. Also (Grant NGR-22-009-387) documented are hearing materials on technology utilization and (NASA-CR-111907: ASRL-'TR-164-1) Avail: NTlS CSCL20K aeronautics research and technology. Sixteen prepared statements Nonlinear panel flutter is examined by using the multiple on these NASA programs are included. E.C. time scaling method and the harmonic balance method. The two methods are applied to the analysis of (1) simply supported two dimensional plates; and (2) clamped-clamped three dimensional N71-25209# Air Force Systems Command, Wright-Patterson plates. The effect of mass ratio and inplane loadings are analyzed AFB. Ohio. Foreign Technology Div. in both bases. The influence of the aspect ratio is considered also THE ASSEMBLY OF GAS TURBINE AIRCRAFT ENGINES for the three dimensional plste. The two methods yield very similar (SELECTED CHAPTERS) results. A comparison with existing methods shows that the results V. I. Sokolov et al 10 Dec. 1970 102 p refs Transl. into are in very good agreement with those obtained by straightforward ENGLISH from the publ. 'Sborka Aviatsionnykh Gazoturbinnykh direct numerical integration method. Author Dvigateley' 1969 p 257-343 (AD-719823; FTD-HC-23-635-70) Avail: NTlS CSCL 21/5 While the units and subassemblies can be assembled both N71-25384*# National Aeronautics and Space Administration. in an assembly shop and in the assembly sections of the combined Lewis Research Center, Cleveland, Ohh. and machine-assembly shops, the overall assembly of an engine POTENTIAL OF METHANE FUELED SUPERSONIC is done only in an assembly shop. The overall assembly of TRANSPORTS OVER A RANGE OF CRUISE SPEEDS UP TO engines, just as the assembly of units. consists of the preliminary MAC.H 4 intermediate and final assembly operations. In the process of John 8. Whitlow. Jr. and Gerald A. Krae Washington May 1971 conducting these operations, a check is made of the mutual 39 p refs arrangement of the parts and units; the axial. radial and diametral (NASA-TM-X-228) Avail: NTlS CSCLO1 B clearances and fits are established. These must comply with the A major factor restricting currently proposed SSTs to a technical specifications for the overall assembly of engines. The maximum cruise speed of Mach 2.7 is the limited heat sink report discusses the overall assembly of three types 6f gas-turbine capacity of kerosene-type fuels. Higher speeds may be possible with engines (GTE), differing significantly in design of basic units; cryogenic liquid methane, which has up to seven times the heat therefore the preliminary intermediate and final assembly processes sink and can be economically obtained from natural gas. In the differ in respect to the methods used in these processes. analysis presented, methane.was considered as the fuel for airplanes Author (GRA) designed to cruise at speeds up to Mach 4. When a comparison was made at Mach 2.7 with a conventionally fueled SST. the use of methane improved both range and direct operating cost (DOC) by about 11 percent. Little range improvement was obtained by N71-25260*# National Aeronautics and Space Administration. cruising faster than Mach 2.7, although certain assumptions made Goddard Space Flight Center. Greenbelt. Md. in this study should produce somewhat optimistic results at the OPTICAL PROPERTIES OF CLOUDS higher speeds. Range peaked near Mach 3 and decreased from 6 In its Warren A. Hovis Significant Accomplishments in Sci. and to 13 percent as cruise speed was increased to Mach 4. The block Technol. at Goddard Space Flight Center 1970 p 19-22 time reductions obtained with higher cruise speeds are beneficial to DOC. Most of the possible DOC improvement was obtained by Avail: NTlS HC$G.OO/MF$0.95 CSCLO48 a speed increase to Mach 3.2, where a 20-minute time saving Remote measurements of optical cloud properties by aircraft produced 7 percent improvement in DOC. Author mounted spectrometers are described. Cloud reflectance measurements in the solar infrared region show that a two channel radiometer with bands centered at 1.7 microns and 2.1 microns can discriminate cloud type and determine to some degree the size N71-25396# National Aerospace Lab.. Tokyo (Japan). of cloud particles. A third channel centered at 1.6 microns is able A MODEL TEST ON THE HOVERING PERFORMANCE OF to distinguish between jet contrails and natural clouds. G.G. JET FLAPPED ROTOR Masaki Komoda. Tohichi Oka. Kingo Takasawa. and - Nobuhiro Toda 1970 18 p refs In JAPANESE; ENGLISH summary , (NAL-TR-211) Avail. NTlS N71-26369# Air Force Systems Command. Wright-Patterson A model test was conducted to investigate the hovering AFE, Ohio. Foreign Technology Dir. performance of jet-flapped rotors with special attention to the THE WORK OF TURBINE AND INJECTION BURNERS ON comparison with that predicted theoretically. The jet-augumented A GAS VARIABLE COMPOSITION thrusts and torques were measured for given sets of rotor rpm and E. P. AdinJkov et 81 1 Dec. 1970 15 p refs Transl. into ENGLISH mass flow rate. Except for the fact that considerably smaller rates from Gaz. Prom. (Moscbw). v. 14, no. 11. 1969 p 36- 39 of mass-flow were measured than predicted. which is attributable (AD-7 19834: FTD-MT-24-273-70) Avail: NTlS CSCL 21/6 to pressure loss within the nozzle area. the general dependence of Combustion and aerodynamic installations are described measured thrust and torque coefficients upon mass flow and rotor which are used to determine ampint of air (gas to air tstios) rpm exhibits acceptable agreement with theoretical predictions
46 7 N71-25397
based on the annular momentum theory in conjunction with CASING TREATMENT INVESTIGATIONS. EVALUATION two-dimensional jet-flapped airfoil theory Author OF RANGE AND DISTORTION TOLERANCE FOR HIGH MACH NUMBER TRANSONIC FAN STAGES. VOLUME 1 W. A. Tesch May 1971 203 p ref (Contract NAS3-11157) (NASA-CR-82862; GE-R71-AEG-149-Vol-l) Avail: NTlS CSCL N71-25397*# Northrop Corp.. Hawthorne, Calif. 20D RECIRCULATION CHARACTERISTICS OF A SMALL-SCALE Two high-tip-speed compressor stages were tested with VTOL LIFTENGINE POD various rotor tip casing treatment configurations under conditions Gordon R. Hall May 1971 112 p refs of undistorted inlet flow, tip-radial distortion and circumferential (Contract NAS3-10498) distortion. The first stage consisted of a 1400 ft/sec tip speed (NASA-(3-1774) Avail: NTlS CSCLOlB medium-aspect-ratio rotor plus a stator vane row: the second stage Exhaust gas ingestion and recirculating flow field characteristics had a 1500 ft/sec tip speed medium-aspect-ratio rotor and a of B small-scale VTOL lift engine pod coniaining two simulated stator vane row. This second stage was tested both with and engines are reported. Results are presented for -tests designed to without zero-turning inlet guide vanes. Overall performance and stall investigate transient development of the recirculating flow field, margin were determined for each stage configuration and inlet steady state ingestion and recirculating flow field characteristics, and condition at 70, 90, 100% of design speed. Extensive surveys of flow dynamic simulation of takeoff and landing. The steady state test conditions were made for the case of circumferential distortion. In results include effect of nozzle height and spacing, effect of inlet and addition. blade element data were obtained when testing with exhaust flow conditions. and effect of wind speed and direction. undistoried and radial distortion inlet conditions. The techniques and Author procedure used to acquire the data are described and an analysis and discussion of the test results is included. Author
N71-25411*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. PRELIMINARY IMPACT SPEED AND ANGLE CRITERIA FOR N71-25461*# General Electric Co , Cincinnati. Ohio DESIGN OF A NUCLEAR AIRPLANE FlSSlON PRODUCT TASK 4 STAGE DATA AND PERFORMANCE REPORT FOR CO NTA I NME NT VESSEL CAS1 NG TREATMENT I NVESTlGATl ONS EVALUATION Patrick M. Finnegan, Richard L. Puthoff. and James W. Turnbow OF RANGE AND DISTORTION FOR HIGH MACH NUMBER (Dyn. Sci. Corp.. Phoenix, Ariz.) Washington May 1971 37 p TRANSONIC FAN STAGES, VOLUME 2 (NASA-TM-X-2245: E-6025) Avail: NTlS CSCL 21 F W A Tesch May 1971 333 p ref Reports and photographs of 96 major accidents occurring (Contract NAS3-11157) before 1965 and involving multiengine jet aircraft were studied. (NASA-CR-82867 GE-R71-AEG-l49-Vol-2) Avail NTlS CSCL Impact speed and angle are presented for landing and takeoff 20D accidents, cruise accidents without in-flight structural failure, and Tabulations are presented of blade element and circumferential in-flight structural failure accidents. The landing and takeoff accidents distortion flow survey data For description of test see N7 1-25460 had an average impact velocity of 200 ft/sec from a;,, direction Author and a maximum impact velocity of 300 ft/sec with a 10 deg solid angle about the roll axis. The cruise accident without structural failure had an average impact velocity of 400 ft/sec and a maximum possibly as high as 1000 ft/sec (305 m/sec). both within a 10 N71-25524*# National Aeronautics and Space Administration. deg solid angle about the roll axis. The in-flight structural failure Lewis Research Center, Cleveland, Ohio. accident had an average impact velocity of 400 ft/sec (122 AIRBREATHING NUCLEAR PROPULSION, A NEW LOOK m/sec) from any direction and a maximum possibly as high as 1000 Frank E. Rom [1971] 23 p refs Presented at 6th Symp. on ft/sec (305 m/sec) within a 10 deg solid angle about the roll axis. Advanced Propulsion Concepts, Niagara. N.Y., 4- 5 May 1971: The in-flight structural failure accident determines the most severe sponsored by AFOSR impact speed for all impact angles. Author (NASA-TM-X-67837) Avail: NTIS CSCL 21 F Aircraft that could fly anywhere on the surface of the earth or remain aloft for weeks at a time without refueling is discussed. N71-25454*# General Electric Co., Cincinnati, Ohio. Aircraft Such an aircraft or air cushion vehicle would be nuclear propelled Engine Group. with complete radiation shielding for crew and passenger safety, IMPROVED ALUMlNlDE COATINGS FOR NICKEL BASE and have safety provisions designed to prevent the release ‘of ALLOYS Final Report radioactive material in the event of serious aircraft accidents. Other M. A. Levinstein and J. R. Stanley 1 2 Mar. 197 1 175 p refs safety features include reactors for long operation without refueling, (Contract NAS3-11 160) long life high temperature oxidation resistant heat exchangers. and (NASA-CR-72863) Avail: NTIS CSCL 1 1F light weight long life valves and pumps. The economics and Improved aluminide coatings for the NASA 6A nickel-base practicality of such vehicles are also discussed. E.H.W. superalloy. developed for high-temperature jet engine components, were investigated. Coatings involved modifications of a base system representative of three approaches to improve coating stability: 1) oxide particle embedment. 2) chromium enrichment, and 3) N71-25537*# National Aeronautics and Space Administration. aluminum enrichment. Both single-step and duplex coating processes Flight Research Center, Edwards, Calif. were used. Coatings were tested at 2000 F (1366 K) in dynamic IN-FLIGHT EVALUATION OF THE LATERAL HANDLING OF oxidation using both high- and low-velocity cycle burner rigs and A FOUR-ENGINE JET TRANSPORT DURING APPROACH ballistic impact. Coating systems identified exceeded 666 hours life AND LANDING at Mach 0.5 and 2000 hours at low velocity. Tensile and Euclid C. Holleman and Glenn 8. Gilyard Washington May 1971 stress-rupture properties of NASA 6A were not affected by the 31 p refs (NASA-TN-D-6339: H-642) Avail: NTlS CSCL 01 coatings. Author B The lateral handling of a typical jet transport was evaluated during up-and-away and approach flight in the landing configuration. N71-25460*# General Electric Co , Cincinnati. Ohio Sidestep maneuvers to a landing were performed with several TASK 4 STAGE DATA AND PERFORMANCE REPORT FOR levels of lateral control power in smooth-air conditions. A roll control
468 N71-25772
power capability of about 15 degrees per second was required for on stability and control of aircraft and engine performance is satisfactory lateral control, 200-foot lateral offsets to the runway discussed. Approximation methods of calculating the dimensions of could be safely corrected with very low levels of lateral control icing zones are presented. Present:day mechanical, physico-chemical, power. approximately 2 to 5 degrees per second, using altered and thermal anti-icers are briefly examined and criteria for evaluating piloting techniques. The pilot evaluation results were in general them when designing AIS are proposed. Principal attention is paid agreement with results from other studies. Author ,U eiecrro-thermal and preheat-air systems. for which detailed methods of heat calculations are spelled out. Methods and techniques of testing AIS under fulr-scale and artificial icing conditions are described and tests with icing simulators are analyzed. N71-25604# Naval Civil Engineering Lab.. Port Hueneme. Calif. Author (GRA) AIRFIELD PAVEMENT CONDITION SURVEY, USNS ADAK. ALASKA David J. Lambiotte and Robert 8. Brownie Jan. 1971 63 p N71-25714# Lockheed Missiles and Space Co., Palo Alto, Calif. refs ON TRANSONIC FLOW PERTURBATIONS CAUSED BY (AD-719889: NCEL-TN-1138) Avail: NTIS CSCL 1/5 VORTICITY The results of a condition survey of the airfield pavements G. B. llinskaya et al 119711 4 p refs Transl. into ENGLISH at the U. S. Naval Station. Adak. Alaska are presented. The survey from Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza (USSR),no. 1. established statistically-based condition numbers (weighted defect 1971 p 168-170 densities) which were direct indicators of the condition of the Avail: NTIS: National Translations Center, John Crerar Library. individual asphaltic concrete and portland cement concrete pavement Chicago, 111. 6061 6 facilities. Additional evaluation efforts included photographic Plane vortical gas flows in the neighborhood of a point coverage of defect types. preparation of the construction history of of orthogonality of the sonic line to the velocity vector are studied. the station, compilation of data on current aircraft traffic and aircraft Such points originate in the transonic flow over a wing profile in types using the station, performance of runway skid resistance tests, the external boundary layer region, where there is a transverse and a study of the requirements for future pavement evaluation velocity gradient. Flows in which the acceleration is negative ahead efforts. Author (GRA) of the sonic point are investigated. They can originate in the flow around a wing profile with a peak pressure distribution, when intense compression waves starting from the sonic line retard the N71-25621# &enter for Naval Analyses, Arlington, Va. Inst. flow in the local supersonic zone. The gas motion is described by of Naval Studies. the continuity. vortex, and Bernoulli equations. Author GENERAL AVIATION, NAVAL AVIATION AND CONGESTION WITH AN EXAMPLE FROM SOUTHERN CALIFORNIA Stuart G. Schmid Jan. 1971 32 p refs Irs INS Res. Contrib. N71-25746# Joint Publications Research Service, Washington, No. 154 D.C. (Contract NO001 4-68-A-0091 ) STUDY OF CLEAR SKY TURBULENCE IN THE (AD-719906) Avail: NTlS CSCL 112 STRATOSPHERE Federal Aviation Authority projections of general aviation N. K. Vinnichenko et ai 14 May 1971 12 p refs Transl. into activity for 1980 show a 75 percent increase over 1969 levels. ENGLISH from Tr. Tsentr. Aerolog. Observ. (Moscow). no. 100. Such growth will cause a substantial increase in general aviation 1970 p 86-98 traffic in airspace over metropolitan areas, creating difficulties for (JPRS-53133) Avail: NTIS present users of airspace including ths Navy. This paper describes Theoretical and experimental studies of clear air turbulence are a simple computational model used to translate projected general reviewed. The topics include the following areas of investigations: aviation growth into implied densities and aircraft interaction large and small scale pulsations, statistical hydromechanical study frequencies. The model is applied to Southern California and a case of synoptic scale movements, characteristic features distinguishing study is made of Miramar NAS at San Diego. The study shows turbulent motion from wave motion, turbulence affecting supersonic that Navy operations there will be seriously hampered by general passenger and transport aircraft, energy transfer rate in the presence aviation traffic within the decade unless stricter air traffic controls of turbulence, distribution of turbulent zones, correlation and spectral are imposed. Such controls are probably justifiable considering the characteristics of lower stratospheric turbulence, and problems costs of moving Navy operations out of Miramar in comparison to associated with creating a physical model of turbulence in the free the costs to general aviation of staying clear of prescribed Navy atmosphere. N.E.N. airspace. Author (GRA)
N71-25622# Army Foreign Science and Technology Center. Washington, D.C. N79-257727# Aerojet Liquid Rocket Co.. Sacramento, Calli. AIRCRAFT ANTI-ICING SYSTEM : PRINCIPLES OF DESIGN INVESTIGATION OF THE SUITABILITY OF GELLED AND TEST METHODS METHANE FOR USE IN A JET ENGINE Final Report. 159un. V. S. Savin et al 26 Jan. 1971 380 p refs Transl. into 1970-15Feb. 1971 ENGLISH of the book "Protivoobledenitelnye Sistemy Letalelnykh E. M.Vander Wall Mar. 1971 97 p refs Apparotov: Osnovy Proektir. i Metody Ispytanii" Moscow. (Contract NAS3-14305) Mashinostr., 1967 p 1 -- 320 (NAqA-CR-72876) Avail: NTlS CSCL 21D (AD-719922: FSTC-HT-23-411-69) Avail: NTlS HC $6.00/MF the results are presented of an investigation that involved: $0.95 CSCL 113 (1) evaluation of suitable particulate gelants for liquid methane, (2) Theoretical fundamentals and practical methods of calculating characterization of the resulting gels with respect to inhibition of and testing anti-icing systems (AIS) of aircraft and helicopters are nitrogen absorption, sloshing behavior. venting behavior, and effects described. Based on generalizations of results of experimental of boil-off, and (3) heat exchanger tests to determine potential research. the meteorological conditions under which icing of aircraft problem areas in utilizing the gels in jet engines. Both water and and power plant is possible are pointed out. and the conditions methanol were found to be suitable gelants for liquid methane. that must be taken as calculation basis in designing AIS are set Liquid methane gelled with water was successfuly evaluated in the forth. The unfavorable effect of various forms and types of icing heat exchanger tests. Author
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N71-25783*# National Aeronautics and Space Administration. (AD-719913; FSTC-HT-23-539-71; RA-017-68) Avail: NTlS Lewis Research Center, Cleveland, Ohio. CSCL 2115 NUCLEAR POWERED AlR CUSHION VEHICLE§ FOR The book reviews the principles of the theory of gas turbine TRANSOCEANIC COMMERCE engines. The main attention is devoted to the physical significance Frank E. Rom and Charles C. Masser Washington May 1971 of the phenomena and behavior patterns reviewed, and especially 52 p refs to those questions of theory directly associated with engine (NASA-TM-X-2293; E-61.52) Avail: NTlS CSCL 21F operation in the aircraft, and with bench testing. Author (GRA) Large air-cushion vehicles (ACV's) greater than 3620 metric tons (4000 tons) gross weight. have the potential for hauling transoceanic cargo at rates in the range of $0.006 to $0.012 per metric ton-kilometer ($0.010 to $0.020/ton-n mi) at speeds of N71-25822*# Translation Consultants, Ltd.. Arlington, Va. 185 kilometers per hour (100 knots). It theoretically would take a fleet SHORT TERM CREEP OF METALS AND ALLOYS UNDER of over 1000 10,000-metric-ton-gross-weight ACV's to handle 10 CONDITIONS OF AERODYNAMIC HEATING percent of the world transoceanic trade projected for 1985. ACV's [KRATKOVREMENNAYA BOLZUCHEST METALLOV I using compact lightweight nuclear reactors show clearly superior SPLAVOV V USLOVIYAKH AERODINAMICHESKOGO performance for ranges of 37 10 kilometers (2000 n mi) or greater. MAGREVA] For a range of 7420 kilometers (4000 n mi) the total operating I. N. 8ogachev et al Washington NASA May 1971 10 p cost for chemical ACV's is three times that for nuclear ACV's. The refs Transl. into ENGLISH from Izv. Vyssh. Ucheb. Zaved., Chern. nuclear ACV performance is less sensitive than the chemical AGV Met.(USSR),no.4,1970 p 142-147 to the operating and cost assumptions used. Relatively large (Contract NASw-2038) variations in any of the important assumptions had a relatively small (NASA-TT-F-13633; Avail: NTlS CSCL 11F effect on nuclear ACV performance. Author A method of testing metals and alloys for ghort-term creep under conditions of 'aerodynamic heating (in dynamic contact with high velocity air flows in the test apparatus) is described. Tests on Ni. Co. Armco Fe. Ti alloys, and various types of C and alloy steel N71-25784*# Hamilton Standard Div , United Aircraft Corp at 500- 1000 C show that the nature of the creep process under Windsor Locks, Conn aerodynamic conditions differ sharply from that characterizing static RESULTS OF INITIAL PROP-FAN MODEL ACOUSTIC creep. The change is attributed to thermal, erosive, and corrosive TESTING. VOLUME 2: APPENDICES B THRU F effects, and in some cases to the alternating stresses arising from F B Metzger and T G Ganger 4 Dec 1970 305 p high-speed air flows. Author (NASA Order L-60739) (NASA-CR-111 842-2, HSER-5787-Vol-2) Avail NTlS HC $6 OO/MF$O 95 CSCL 20A Stationary microphone test data from the prop-fan model test are presented along with an evaluation of the accuracy of the N71-25846# General Precision, Inc., Binghamton, N.Y. Link data Appendices contain the one-third octave band data for the Group. far-field tests conducted with the static shroud ir-+alled the A COMPARISON OF PILOT PERFORMANCE USING A narrow band data for the far-field tests conducted with the static CENTER STICK vs SIDE ARM CONTROL CONFIGURATION shroud installed, the one third octave band data for the near-field Technical Report, May-Oct. 1968 tests conducted with the static shroud installed, and the one Richard Geiselhart. Paul Kemmerling. James E. Cronburg. and third octave band data for the far-field tests conducted with the David E. Thorburn Wright-Patterson AFB, Ohio AFSC Nov. 1970 compromise shroud installed Author 54 p refs (Contract F33615-68-C-1097) (AD-720846; ASD-TR-70-39) Avail: NTlS CSCL 113 Six Air Force pilots having current flying status flew a N71-25785*# Hamilton Standard Div., United Aircraft Corp.. series of forty-minute missions to compare pilot performance with Windsor Locks, Conn. the conventional center stick, dual side stick. and single side stick RESULTS OF INITIAL PROP-FAN MODEL ACOUSTIC configurations. An F-1 11 flight simulator with three TESTING. VOLUME 1: DISCUSSION degrees-of-motion was employed as the test-bed for the experiment. F. B. Metzger and T. G. Ganger 4 Dec. 1970 58 p refs The missions. which included climbout. a terrain following portion, (NASA Order L-60739) two banking turns, and five Instrument Landing System (ILS) ap- (NASA-CR-111842-1: HSER-5787-Vol-1) Avail: NTlS CSCL23A proaches, were designed to test the feasibility of side stick con- Results are summarized of a test program conducted to trollers under low-altitude, high-speed conditions. Course steering explore the low noise potential of the prop-fan, a high bypass ratio, deviation, airspeed deviation, pitch deviation, and I LS evaluation low pressure ratio, variable pitch propulsor. Far field noise dita and scores were obtained using the computer to compare pilot directional character of a 21-inch diameter prop-fan model were performance using the three stick configurations. From the evaluation determined for two shroud configurations, a bellmouth test shroud of the performance data and opinion questionnaires filled out by and a takeoff/cruise shroud. In addition, near field data were the pilots. it was concluded that side stick controllers are feasible obtained for the bellmouth test shroud. Review of the data reinforce for use in a relatively high-speed aircraft flying a low-altitude, earlier conclusions that a large STOL aircraft powered by prop-fans high-speed mission, and that dual side sticks are preferable to single has the potential to meet the objective of 95 PNdB at 500 feet side sticks. Recommendations were made for furthef studies in with modest acoustic treatment. Author several areas. Author (GRA)
N71-25872*# National Aeronautics and Space Administration. N71-25808# Army. Foreign Science and Technology Center, Lewis Research Center, Cleveland, Ohio. Charlottesville, Va. MACH 2.5 PERFORMANCE OF A BICONE INLET WITH PRINCIPLES OF THE THEORY OF AVIATION GAS TURBINE INTERNAL FOCUSED COMPRESSION AND 40 PERCENT ENGINES [OSNOVY TEORll AVIATSIONNYKH INTERNAL CONTRACTION GAZOTURBINNYKH DVIGATELEI] Joseph F. Wasserbauer and David A. Choby Washington May I. I. Kulagin 15 Dec. 1970 307 p Transl. into ENGLISH from 1971 58 p refs the Russian report (NASA-TM-X-2294: E-6079) Avail: NTlS CSCL 20D
470 N71-26053
The inlet was designed to have the minimum internal organization of technical servicing are elucidated. Data regarding contraction consistent with high total-pressure recovery and low methods and means of control and mechanization of processes of cowl drag. Without a bypass system the inlet provided a critical technical servicing are set forth. In the book questions of flight pressure recovery of 0.880 and a steady-state distortion of 0.185 operations of aircraft are stated: the organization and provision of when the supercritical bleed flow was 0.032. With a bypass flights, maintenance of aircraft at various stages, under specific system in operation the critical pressure recovery increased to 0.903 conditions and cases of flight, methods of determination of load. and and the steady-state distortion dropped to 0.10. Maximum angle centering. and of fuel consumption. and method6 of analyzing flying of attack before an inlet unstart ranged as high as 9.4 deg. accidents. Author (GRA) Author
N71-25998*# Translation Consultants, Ltd.. Arlington, Va. N71-25876# Aluminum Co. of America. New Kensington. Pa. VARIABLE AERODYNAMIC FORCES IN A TURBINE STAGE Alcoa Research Labs. INDUCED BY A VANE CASCADE IN THE WAKE OF A INVESTIGATION TO DEVELOP A HIGH STRENGTH PRECEDING CASCADE [PEREMENNYYE STRESS-COR ROSl ON RESISTANT NAVAL AIRCRAFT AERODINAMICHESKIYE SlLY V TURBINNOY RESHETKE, ALUMINUM ALLOY Final Report, 16 Dec. 1969-16 Sep. VOZ B U ZH D AYE MYYE P OS LE D UY U S C H C HIM 1970 LOPATOCHNYM APPARATOM] J. T. Staley 20 Nov. 1970 114 p refs A. S. Laskin et al Washington NASA May 1971 6 p refs (Contracts NO0019-70-GO1 18; N00019-69-C-0292) Transl. into ENGLISH from Energomashinostr. (Moscow). v. 16. Jul. (AD-720398) Avail: NTlS CSCL 11/6 1970 p 45-46 The report presents the results of an evaluation of three (Contract NASw-2038) tempers of commercially fabricated alloy MA15 plate in 1 in. to (NASA-TT-F-13631) Avail: NTlS CSCL2OD 6 in. thickness. Compared at equal strengths, MA15 developed Experimental and theoretical study of the aerodynamic forces higher resistance, to stress-corrosion cracking. greater resistance to produced in a.turbine stage by each subsequent vane cascade d exfoliation corrosion, higher toughness. and better fatigue a cascade series. Experimental oscillograms are given to show the performance than established commercial aluminum alloys. Compared pressure pulsations and pulsation amplitude variations on the at equal resistance to stress-corrosion cracking, MA15 developed concave and convex surfaces of a cascade sequence. The complex substantially higher strength than established commercial aluminum nature of variations in the aerodynamic forces resulting from the alloys. Field testing of this material is recommended. interaction betwe'en the successive vane cascades is discussed. Author (GRA) Author
N71-26032# National Transportation Safety Board. Washington. N71-25920*# National Aeronautics and Space Administration. D.C. Goddard Space Flight Center, Greenbelt, Md. AIRCRAFT ACCIDENT REPORT: COMPANIA ECUA- RADIO FREQUENCY UTILIZATION IN THE BANDS OF TORIANA DE AVlAClON DOUGLAS C-54D. REPUBLIC PRINCIPAL INTEREST FOR AERONAUTICAL SATELLlTEa OF ECUADOR, HC-AON: MIAMI INTERNATIONAL John J. Bisaga, Earl J. Holliman, and Allan Schneider Dec. 1970 AIRPORT, MIAMI, FLORIDA, 14 APRIL 1970 128 p refs Dec. 1970 27 p ref (NASA-TM-X-65527; X-490-70-447) Avail: NTlS CSCL 178 (NTS8-AAR-71-2) Avail: NTlS Radio frequencies examined are those allocated and assigned A Douglas C-54D. of Ecuadorian registration. crashed at in the frequency bands 118.0 to 136.0 MHz (VHF) and 1535 to Miami International Airport, Miami, Florida, at approximately 0724 1660 MHz (UHF or L band). The frequency areas were considered est.. April 14, 1970. The aircraft was being operated as an as possible candidates for aeronautical communications using international cargo flight by Compania Ecuatoriana de Aviacion. The satellite techniques because of their current allocation to the accident occurred during the initial climb, following an instrument aeronautical service. The present utilization, future trends which would takeoff at Miami International Airport. The flight was en route from affect frequency availability with projected growth. and pertinent Miami to Panama City, Panama, the first leg of a flight which was factors influencing frequency assignment for the time frame to to terminate at Quito, Ecuador. The two pilots, the only occupants 1980 were studied. Since the ability to meet increased utilization of the aircraft. were killed, and the aircraft was demolished by also depends upon channelization and performance characteristics. impact and postimpact ground fire. Author the parametric relation of these factors for a range of values were included. Author
N71-26052*# National Aeronautics and Space Administration. N71-25955# Air Force Systems Command, Wright-Patterson Washington. D.C. ' AFB. Ohio. Foreign Technology Div. CURRENTSHUTTLE STATUS TECHNICAL MAINTENANCE OF AIRCRAFT C. J. Donlan In its NASA Space Shuttle Technol. Conf.. Vol. 1 [TEKHNI CHESKAY A EKSP LU ATATSIY A LETATELNY KH Apr. 1971 p 1'-15 APPARATOV] Avail: NTlS HC$9.OO/MF$0.95 CSCL05A A. I. Pugachev et al 15 Jan. 1971 633 p refs Transl. into Space shuttle cost trends per pound of payload are defined ENGLISH from the Russian for current transportation systems ranging in size from the Scout (AD-720366; FTD-MT-24-110-70) Avail: NTlS HC $9.00/MF to the Saturn V. Technical performance requirements, engine size. $0.95 CSCL 1,I3 and vehicle configurations are assessed, mobilization of people and Basic questions on the theory, practice and organization resources and a broad technology program are outlined. and a of technical maintenance of aircraft of civil aviation are stated. current space shuttle planning schedule involving a delta-type Application of methods of flow planning, the theory of mass servicing orbiter with single vertical tail and associated canard-type booster and the theory of reliability in solving problems of technical configurations is presented. G.G. servicing are considered. Basic rules are started for the maintenance of aircraft and special features of their servicing under various climatic conditions. Questions regarding provision of operational N71-26053*# National Aeronautics and Space Administration. technical facilities for aircraft and foreign experience in the Ames Research Center, Moffett Field, Calif.
47 1 N71-26054
FLOW FIELDS AND AERODYNAMIC HEATING OF SPACE EFFECTS. PART 1: FLOW FIELD VISUALIZATION, SHUTTLE ORBITERS THERMOCOUPLE MEASUREMENTS, AND ANALYSIS J. G. Marvin. W. K. Lockman, G. G. Mateer. H. L. Seegmiller. C. H. Lee Seegmiller In its NASA Space Shuttle Technol. Conf., Vol. C. Pappas et al In its NASA Space Shuttle Technol. Conf., Vol. 1 Apr. 1971 p 185-215 ref Apr. 1971 p 21 -73 refs Avail: NTIS HC$S.OO/MF $0.95 .CSCL 20M Avail: NTlS HC$S.OO/MF$0.95 CSCL 200 Flow field visualization techniques, thermocouple Flow fields and heating environments that the space shuttle measurements, and analyses of shock interference phenomena about orbiter will encounter are investigated in hypersonic wind tunnel a model of the straight wing orbiter established: (1 wing fuselage simulations in order to obtain data for evaluating performance shock interference heating effects for low sweep wing at angles prediction techniques and for extrapolating ground based facility of attack from 20 deg to 70 deg; (2)stagnation region and shock data to flight conditions. Photographs of streamline oil flow patterns. boundary layer interference effects at small angles of attack; (3) pressure distribution data. and heating data on the windward stagnation region interference effects only at large angles of attack; surface of low and high cross-range orbiters are presented and (4) suitability of the local angle of attack theory for predicting comparisons with theory are made. G.G. stagnation region interference effects provided the stagnation streamline is known; (5) significant wing root interference effects; and IS) peak interference temperature similarities at Mach = 7.4, = 1.10 times 1 million and at Mach = 15, Re = 0.03 times N71-26054*# McDonnell-Douglas Co.. St. Louis. Mo. Re AN ANALYSIS OF PREDICTED §PACE SHUTTLE 1 million. G.G TEMPERATURES AND THEIR IMPACT ON THERMAL PROTECTION SYSTEMS R. V. Masek and J. Alan Forney (NASA. Marshall Space Flight N71-26058*# National Aeronautics and Space Administration. Center) In NASA. Washington NASA Space Shuttle Technol. Langley Research Center, Langley Station, Va. Conf..Vol. 1 Apr. 1971 p 75-96 SHOCK INTERFERENCE HEATING AND DENSITY RATIO Avail: NTlS HC$9.00/MF$0.95 CSCL 20M EFFECTS. PART 2: HYPERSON.IC DENSITY RATIO Aeroheating prediction methods for the space shuttle EFFECTS configuration are evaluated by comparing evolved time-temperature James L. Hunt and Theodore R. Creel, Jr. In NASA SDace Shuttle histories computed at five lower centerline locations for various Technol. Conf.. Vol. 1 Apr. 1971 p 217-243 combinations of flow field method. transition criterium, turbulent, heating method and trajectory analysis. Considered are a metallic heat Avail: NTlS HC$9.00/MF$0.95 CSCL2OM shield and a surface insulation concept, low and high cross-range Ground test data obtained at hypersonic Mach numbers missions, and a conical flow field with normal shock expansion to and at various values of specific heat-gas ratios are. used to Newtonian pressure. The low cross-range mission peak temperature simulate the trends of equilibrium real gas effects expected for low was found to be most sensitive to flow field assumption and the cross-range shuttle flight. Appiied are data on shock shape, surface high cross-range mission was most affected by transition criteria. oil tlow patterns, and for the location of the body snock/wcng A conical flow assumption produces temperatures 166 C - 222 C shock intersection location obtained at various angles of attack and higher than the normal shock assumption; the effects c * transition with normal shock density ratios of 3.9, 5.6, and 12, respectively. criteria are noticeable about 111 C. For the low cross-range mission, Primary conclusions show that significant shock-density-ratio effects the thermal protection system unit weight for one aeroheating are strongly configuration and angle-of-attack dependent and that methodology proved 32.1 N/sq m lighter than for another prediction a high cross-range shuttle configuration which reenters at lower method. G.G. angles of attack is essentially a best choice. G.G.
N71-26056*# Grumman Aerospace Corp.. Bethpage. N.Y. A NUMERICAL PROCEDURE TO CALCULATE THE N71-26059*# General Dynamics/Convair. San Diego. Calif. INVISCID FLOW FIELD ABOUT A SPACE SHUTTLE Aerospace Div. ORBITER TRAVELING AT A SUPER§ONIC/HYPER§ONIC SHOCK INTERFERENCE HEATING ON THE SPACE VE LOClTY SHUTTLE BOOSTER DURING ASCENT B. Grossman, F. Marconi. Jr., and G.,Moretti In NASA, Washington 0. Brevig and C. Young In NASA, Washington NASA Space NASA Space Shuttle Technol. Conf.. Vol. 1 Apr. 1971 Shuttle Technol. Conf.. Vol. 1 Apr. 1971 p 245-266 p 157-184 refs Avail: NTlS HC $9.OO/iviF $0.95 Avail: NTlS HC$9.OO/MF$0.95 CSCL20M A technique for computing the complete inviscid, three Paint phase-change and thermocouple test results from dimensional flow field about a vehicle flying at supersonic speed space shuttle booster ascent wind tunnel simulations show that: at an angle of attack is reported. The flow field in the vicinity of (1) interferenp heating on the booster top surface is caused by the stagnation point at the nose of the body is determined using shock impingement due to orbiter and booster bow shocks in the a three dimensional. time dependent blunt body program. The gap region; (2) interference heating in the gap region increases with asymptotic steady state values of this flow field are then used as free stream Mach number; (3) a reasonable correlation between starting conditions for a supersonic, steady state numerical paint phase-change and thermocouple heat transfer rate test data calculation. This computation utilizes a three dimensional, finite is obtained: and (4) paint phase-change test data cannot be used difference marching technique which determined the flow field accurately to measure peak heat transfer rates in areas of highly downstream of the nose of the vehicle where the flow is supersonic. localized heating due to shock impingement. G.G. Within the physical model of an inviscid, perfect gas, the complete coupled calculation provides an approximation which uniformly converges to the exact solution. Agreement with experimental results is excellent and applications of the program are made for a typical N71-26060*# National Aeronautics and Space Administration. shuttle orbiter delta lifting body configuration at angle of attack. Langley Research Center, Langley Station, Va. Author LEE SIDE HEATING INVESTIGATIONS. PART 1: EXPERIMENTAL LEE SIDE HEATING STUDIES ON A DELTA N71-26057*# National Aeronautics and Space Administration. WING ORBITER Ames Research Center, Moffett Field, Calif. Jerry N. Hefner and Allen H. Whitehead, Jr. In its NASA Space SHOCK INTERFERENCE HEATING AND DENSITY-RATIO Sh~~ttleTechnol. Conf.. Vol. 1 Apr. 1971 p 267-287 refs
47 2 N71-26129
deficiencies are presented. It is shown that uncertainties inherent in Avail: NTlS HC$S.OO/MF$0.95 CSCL 20M high angle of attack stability data may be greatly reduced by The effects of Reynolds number and angle of attack on extending the existing two-dimensional cross-f!ow caefficient data the magnitude and distribution of lee surface heating at Mach 6 base. At low angles of attack, requirements for developing methods on a delta wing orbiter establish that: (11 the growths of laterai for predicting the onset of. discernible viscous components, and body dimensions in addition to nose shape and bluntness have a relating the strength of that component to Reynolds number, are strong influence on the nature of vortical flow and leeside heat cited. Author transfer: and (2) the flow about a cylindrical body is essentially two dimensional at the 55 deg angle of attack with reference to the body axis. G.G. N71-28066*# McDonnell-Douglas Astronautics Co.. St. Louis, Mo. CORRELATION OF SPACE SHUTTLE APPLICABLE EXPERIMENTAL HYPERSONIC AERODYNAMIC CHARACTERISTICS WITH THEORY N79-26061*# Grumman Aerospace Corp., Eethpage, N.Y. Richard K. Hamilton ln NASA. Washington NASA Space Shuttle LEE SIDE HEATlNG INVESTIGATIONS. PART 2: LEE Technol. Conf., Vol. 1 Apr. 1971 p 455-492 refs SIDE HEATlNG INVESTIGATIONS OF SIMPLE BODY LIKE CONFIGURATIONS Avail: NTlS HC$S.OO/MF$0.95 CSCL 228 George Maise In NASA, Washington NASA Space Shuttle Hypersonic theoretical-experimental correlations of Technol. Conf Val 1 Apr. 1971- p 289-309 refs aerodynamic characteristics pertinent to straight and blended delta wing shuttle designs are presented. The results substantiate the Avail: NTlS HC$9.00/MF$0.95 CSCLZOM usefulness of the theoretical techniques in supporting the assessment The leeside aerodynamic heating of various shapes flying of the hypersonic aerodynamic coefficients for delta wing shuttle hypersonically at an angle of attack was investigated. Intense designs. The use of the Hypersonic Arbitrary Body Program (HAEP) heating resulting from reattachment of leading-edge vortices on the also provides confidence in configurations as they are entered into lee side of the bodies was analyzed by: (1) correlation and the wind tunnel program. Emphasis is placed on those aerodynamic comparison of available leeside hezting data, and (2) an experimental characteristics which are influential with rgpect to the shuttle program to clarify some questions related to the vortical flow design. Characteristics correlated are shown on the slide. Areas of phenomenon. In the correlation of available data on circular cones, exceptional agreement will be noted as well as instances where a strong Reynolds number dependence has been observed. In the deviations exist. Oil flow visualization studies complement the wind tunnel study, the effect of increase in cross sectional area on vortical heating was examined. and an attempt was made to analysis. Author establish the angles of attack at which the flow about elongated bodies becomes two dimensional in the cross-flow plane, Le., negligible axial components. Heat transfer and oil flow models were N71-26110* National Aeronautics and Space Administration. tested in a hypersonic wind tunnel. Author Langley Research Center, langley Station. Va. DIRECT LIFT CONTROL SYSTEM Patent Joseph W. Stickle, inventor (to NASA) Issued 27 Apr. 1971 4 p .Fad 20 hn.1969 CI. 244-42: Int. CI. B64cZ1/08 N71-26062*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. (NASA- Case- LAR- 10249- 1 ; U S-Patent-3.57 6.30 1 ; US-Patent-Appl-SN-835060) Avail: US Patent Office CSCL 01C STATIC AND DYNAMIC AERODYNAMICS OF SPACE A dtrect lift control system IS proposed which is associated SHUTTLE VEHICLES with existing control mechanism on most aircraft, and particularly Victor L. Peterson. Elliott D. Katzen. John A. Axelson, Jack J. applicable to light-weight aircraft. This is accomplished by forming Brownson. Donald L. Ciffone et al In ~tsNASA Space Shuttle a slot through to the flap associated with the wing. When the flap Technol. Conf., Vol. 1 Apr. 1971 p 311 -373 refs is deflected, air is forced through the slot opening in the lower surface of the flap and discharged at the slot opening at the upper Avail: NTlS HC$9.00/MF$0.95 CSCL22B surface of the flap. this spoils the airflow over the flap thus Effects of Mach number, as well as chine radius and Reynolds reducing lift. Tests have shown that this arrangement has little effect number. on the aerodynamics of space shuttle vehicles at high on drag, since the actual shape of the airfoil flap combination has angles of attack are considered for delta wing configurations having not been changed to any degree. In addition, closure mechanisms single and'twin vertical tails. Resulting aerodynamic criteria for a are introduced for varying the size of the slots to regulate the wide range of shuttle configurations and test conditions show that: degree of spoiling of the flap induced lift and the resultant direct (1) aerodynamic stability designs must consider the effects of lift control. Author varying dynamic pressure and Mach numbers. Computer simulations can be utilized to determine which of the many derivatives have the greatest influence on flight behavior of space shuttle configurations. N71-26129# Royal Aircraft Establishment, Farnborough (England). G.G. AERODYNAMIC FORCES ON AUTOCABS, APPENDIX M K. T. Shaw In its Cabtrack Studies: Assessment of Autntgxi Urban Transport Systems Jan. 1969 p 123-128 refs N71-2606!5*# McDonnell-Douglas Astronautics Co., St. Louis, Mo. CONIIDERATION OF REYNOLDS NUMBER SIMULATION Lopyright. Avail: NTlS FOR SUSSONIC SHUTTLE TESTS Autocabs may be subject to substantial aerodynamic forces Thomas E. Sellers ln NASA, Washington NASA Space Shuttle when operating in windy conditions although the cab speed may Technol. Conf., Vol. 1 Apr. 1971 p 423-453 refs be relatively low. These forces can have a considerable effect upon the power required to maintain particular acceleration profiles and Avail: NTlS HC$S.OO/MF$0.95 CSCL20D upon the vehicle track required for lateral stability. The effect of The Reynolds number simulation requirements for conducting the yawing moment on longitudinal stability could limit the subscale wind tunnel ' tests of space shuttle aerodynamic types of guidance system which are acceptable. Some preliminary configurations are reviewed. and conclusions are reached that apply estimates of the aerodynamic forces and moments to which an to the acquisition of data at angles of attack from zero to 90 Autocab may be subjected, over a range of cab and wind speeds degrees. Methods for qualitatively evaluating effects of simulation within which a Cabtrack system in Central London may operate
473 N71-26150 are presented. The estimates refer to an idealized cab running on tunnel dynamic pressure of 383 newtons per square meter (8 a flat road surface of unlimited width and do not take into account pounds per square foot), corresponding to a Reynolds number of 2 9 th? effects of flow disturbances produced by particular track million The range of jet momentum coefficients was 0 to 1.07 configurations. Author Author
N71-26150# Research Inst. of National Defence. Sundbyberg N71-26194# Army Test and Evaluation Command. Aberdeen (Sweden). Proving Ground, Md ANTENNA FOR SPEECH COMMUNICATION SET FPL37 AVIATION EQUIPMENT AND AIRCRAFT ARMAMENT MEASUREMENTS OF IMPEDANCE ON THE PRODUCTION Final Report VERSION IN LIGHT METAL 29 Jan 1971 28 p refs [TALKOMMU MI KATIONSANTENN TILL FPL 37. (AD-720570. MTP-7-4-005) Avail NTlS CSCL 113 IMPEQANSMAETNIMGAR PA SERIEVERSION I Procedures are described for determining the ability of avlation LAETTMETALL] equipment and aircraft armament to withstand storage and operate Viggo Westerlin Oct. 4969 8 p refs In SWEDISH effectively in a tropic environment Author (GRA) (FOA-3-C-3602-61) Avail: NTlS The earlier antenna put forward has undergone certain alterations in changing to the production version made in light metal. The report briefly reviews impedance measurements for the N71-26195# Army Test and Evaluation Command, Aberdeen new design. Desirable alterations of the basic design are stated. Proving Ground, Md. Author RESCUE EQUIPMENT, AIRCRAFT CRASH Final Report 27 Jan. 1971 25 p refs N71-26170*# Princeton Univ.. N.J. (AD-720563; MTP-7-3-090) Avail: NTlS CSCL 617 Procedures are identified for evaluation of aircraft borne TURBULENCE AND LATERAL-DIRECTIONAL FLYING QUALITIES aircraft crash rescue equipment under simulated tactical conditions. James A. Franklin Washington NASA Apr. 1971 344 p refs Helicopter mounted rescue hoists and accessories are also included. (Contract NSR-3 1-001-1 04) Author (GRA) (NASA-CR-1718; Rept-890) Avail: NTlS CSCLOiB Trends in pilot rating obtained in the test'program for variations in turbulence disturbances and airplane dynamics are explained in N71-26298# National Aerospace Lab.. Tokyo (Japan). terms of measures of precision of task performance. pilot control GAS TURBINE COMBUSTORS Norkload, and pilot CompensPtory behavior derived from time Kunio Suzuki, Takasi Tamaru, Shoji Horiuchi. and Takashi Saito histories of the flight evaluations. Pilot-vehicle systems analyses Sep. 1970 82 p refs In JAPANESE; ENGLkSH summary substantiate the performance-workload data and provide a more (NAL-TR-208) Avail: NTlS fundamental understanding of the heading control task in turbulence A design method for lift engines is .proposed for applying The significant influence of turbulence on the evaluation task was recent data and experience. Various flame holders and their found to be the rms disturbance magnitude, with yaw disturbances characteristics, the admission of air and its distributions, and flow having, a more profound effect than roll disturbances. Spectral patterns in the combustion chambers are investigated. However, on bandwidth had less bearing on flying qualities than disturbance account of lack of tundamental knowledge concerning the magnitude. Reductions in either roll damping or directional stability phenomena occurring in a combustion chamber. the design details still adversely affected flying qualities. Additional roll damping and must be dependent on the practical data and model experiments. directional stability were desired when the level of turbulence was Therefore, design data which had 'been experienced in many increased. Data obtained for variations in aileron yaw indicate that practical engines, especially those of vaporizing types, are considered. favorable yaw is detrimental to the heading tracking task, particularly Experimental techniques necessary for developing or improving for low directional stability and when roll disturbances due to combustion systems such as temperature measurement by turbulence are large. Author thermocouples. and gas analysis by means of sampling probes, are also described. Author
N71-26183*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. N71-26301# Consortium of Universities, Washington, D.C. Urban LOW SPEED AERODYNAMIC CHARACTERISTICS OF A Transportation Center. LARGE SCALE STOL TRANSPORT MODEL WITH AN DULLES INTERNATIONAL AIRPORT ACCESS AUGMENTED JET FLAP Robert G. Baxter [1970] 44 p refs Prepared in cooperation Anthony M. Cook and Thomas N. Aiken Mar. 1971 89 p refs with Md. Univ. (NASA-TM-X-62017) Avail: NTlS CSCLOlA (PB-194094) Avail: NTlS CSCL13B An investigation was made to study the aerodynamic An examination of the growth potential and requirements characteristics of a large scale model equipped with an augmented-jet for continued improvement of Dulles International Airport is flap and undewing cruise engines with deflectable thrust capability. presented. An analysis of the relationship between the daily vehicular The augmented-jet flap is a jet flap with the primary jet thrust volumes on the Dulles Airport access road and the number of daily increased by means of a spanwise ejector system installed in the departing passengers is used as a basis for determining the wing trailing-edge flap. The flap installation was on the inboard part adequacy of access routes to the' airport. Author of the wing, with blown ailerons outboard. Primary configurations tested were those selected previously for landing approach and takeoff, for direct application of the data to a proposed flight research aircraft. Assessment was made of the effects of the N71-26303# Hydrospace Research Corp.. Rockville. Md. underwing engines and nacelles with variations in thrust magnitude AIRCRAFT NOISE TYPE CERTIFICATION ORIENTATION and direction. The effects of fuselage BLC were also measured. In SESSIONS: FAA PRESENTATIONS, SUPPLEMENT 1 Final addition. several methods of lateral control were investigated to Report obtain measurements of lateral derivatives and roll control power. Oct. 1970 70 p refs Presented in Washington, D.C., 5 Aug. The tests were made with and without the horizontal tail at a wind 1970. Conf. held in Washington, D.C., Rockville. Md., and Atlantic
474 N71-26387
City, 5- 12 Aug: 1970: sponsored by FAA LIFTING ENTRY VEHICLE (Contract DOT-FA70WA-2446) Charles L. Ladson washington Apr. 1970 44 p refs (HRC-TR-390-Suppl-1) Avail: NTlS (NASA-TM-X-1994; L-6592) Avail: NTlS CSCL 01A The proceedings of a conference to train personnel in Aerodynamic forces on a representative, high-performance. techniques for conducting aircraft noise certification are presented. entry configuration with a lift-drag ratio of about 3 have been Subjects discussed are: (1) development of noise rules, (2) obtained at Mach numbers of 6 and 10 in air and 20 in helium. aircraft noise measurements, (3) aircraft noise evaluation, (4) data These data are compared with theory to identify areas in which reduction, and (5) flights to determine maximum sideline noise the theoretical methods are adequate and the areas in which measurement .points. Author improvement is necessary. Experimental results of Mach 10 tests of tip-fin and body modifications ate also presented to show the attempts that have been made to develop a configuration which is stable about all axes. Author N71-26304# Hydrospace Research Corp., Rockville. Md. AIRCRAFT NOISE TYPE CERTIFICATION ORIENTATION SESSION Final Report John F. Waters and Ray E. Glass Oct. 1970 29 p refs Conf. N71-26355*# National Aeronautics and Space Administration. held in Washington, D.C.. 5 Aug. 1970, in Rockville. Md., 6-7 Lewis Research Center, Cleveland, Ohio. Aug. 1970, and in Atlantic City, 10- 12 Aug. 1970; sponsored by ANALYSES OF COOLED TURBINE AIRFOIL FAA CONFIGURATIONS AT CONDITIONS OF SUPERSONIC (Contract DOT-FA70WA-2446) FLIGHT (HRC-TR-300) Avail: NTlS Francis S. Stepka Washington Apr. 1969 77 p refs During the period 5 through 12 August, 1970, an aircraft (NASA-TM-X-1782) Avail: NTlS CSCLOlA noise type certification measurements orientation session was The results of an analysis of various first stage turbine conducted for the Federal Aviation Administration (FAA). The purpose stator vane and rotor blade cooling designs which would have of the orientation session was to familiarize FAA personnel with application to engines of aircraft for high-speed flight such as a the acoustic measurement techniques and procedures involved in the supersonic transport are presented. Also summarized are the influence noise certification of aircraft under Federal Aviation Regulations. of various factors on cooling design and performance of turbine Personnel from the FAA regional offices are actually involved in vanes and blades. These included use of future high-temperature aircraft noise type certifications. Author materials, usdof higher material thermal conductivity, changes in design geometry, changes in combustor gas temperature profiles, foreign object damage. and the effects of steady-state and transient engine and flight conditions. Author N71-26305# Hydrospace Research Corp , Rockville, Md AIRCRAFT NOISE TYPE CERTIFICATION ORIENTATION SESSION: LECTURE NOTES, SUPPLEMENT 2 Final Report N71-26383# Air Force Systems Command, Wright-Patterson John Waters, John V McFadden, and Ray Glass Oct F E lQ7O AFB, Ohio. Materials Lab. 98 p ref APPLICATION OF PHOTOCHROMIC COATINGS FOR (Contract DOT-FA70WA-2446) NONDESTRUCTIVE INSPECTION Final Technical Report, (HRC-TR-300-Suppl-2) Avail NTI S Jan. 1969-Jul. 1970 Details of the techniques and procedures for measuring Sidney Allinikov Dec. 1970 61 p refs the effective perceived noise level (EPNL) during aircraft noise type (AD-720239; AFML-TR-70-246) Avail: NTlS CSCL 14/2 certifications are presented EPNL values are averages based on at The application of a photochromic compound to provide least six takeoff and six landing measurements Allowable EPNL a nondestructive inspection (NDI) technique for aerospace values are given as a function of maximum aircraft weight Several materials and structures is discussed. The photochromic compound, EPNL tradeoffs are allowed to provide some margin for excesses incorporated into a paint formulation, is converted from a white to Author a bright violet color upon a brief irradiation from an ultraviolet source. The colored paint surface is then heated by any suitable N71-26334* National Aeronautics and Space Administration. means, such as a hot air blower. Heat serves to bleach the paint Langley Research Center, Langley Station, Va. to the original white color. Defects are disclosed because heat P R ECI P ITATl ON DETECTOR Patent conductivity at the defect site is different from that of the rest of Harold R. Long, Martin J. Menges. and Samuel W. Mugler, inventors the area under inspection. The defect thus appears as a colored (to NASA) Issued 20 Apr. 1971 4 p Filed 5 Feb. 1969 CI. or white area dependent upon the nature of \the defect and 317-153; Cl. 317-DIG3; CI. 340-235; Int. CI. HOlh47/36 originating direction of the heat source. Some of the types of (NASA-Case-XLA-2619: US-Patent-3.575.641 : defects and kinds of structures to which the NDI paint has been US-Patent-Appl-SN-79669 1) Avail: US Patent Office CSCL 09C applied are discussed, along with advantages and limitations of the A precipitation detector and mechanism used to shut down paint. Author (GRA) a load during precipitation and activate a load upon completion of precipitation is described. The detector has thermistors in a bridge circuit. One of the thermistors is exposed to the elements and cooled upon being contacted with precipitation. This causes an N71-26387* National Aeronautics and Space Administration. imbalance in the bridge circuit the output of which actuates a relay Langley Research Center, Langley Station, Va. that shuts down the load. Termination of precipitation allows the INSTRUMENT FOR MEASURING THE DYNAMIC BEHAVIOR thermistor to warm up balancing the bridge circuit and the relay OF LIQUIDS Patent closes activating the load. David G. Stephens and Clemans A. Powell. Jr.. inventors (to Official Gazette of the U.S. Patent Office NASA) Issued 21 Oct. 1969 5 p Filed 26 Jan. 1988 CI. 73-301 ; Int. CI. G01f23/00 (NASA-Case-XLA-05541; US-Patent-3.473.379; N71-26354*# National Aeronautics and Space Administration. US-Patent-AppCSN-700986) Avail: US Patent Office CSCL 20D Langley Research Center. Langley Station, Va. An instrument to determine the dynamic behavior of liquid HYPERSONIC AERODYNAMIC CHARACTERISTICS OF DL-4 in a tank is described including a pipe fixed to the tank and
475 N71-26416 extending throughout its height. An inlet of the pipe allows liquid N71-26466# Air Line Pilots Association, International. Chicago, to enter the pipe. A tube placed inside the pipe carries a plurality 111. of pressure transducers. one being exposed to the liquid in the ALPA: A SURVEY OF AIRPORT FIRE AND RESCUE tank. a second exposed to liquid within the pipe, and a third located FACILITIES, 1971. NORTH AMERICA at the end of the tube below the other transducers. Outputs from B. V. Hewes. P. R. Robinson, and A. L. Couch 1971 154 p the transducers are computed, and indicate the simultaneous Avail: NTlS acceleration of the tank. the amplitude of liquid slosh in the tank, A survey of airports in the United States in order to determine and the depth of liquid in the tank. the status of the crash fire and rescue equipment available for use Official Gazette of the U.S. Patent Office in case of an accident involving a scheduled trunk or local service air carrier aircraft is discussed. Only those airports receiving daily service are included and only fire and rescue equipment located within the airport boundaries is reported. Off airport equipment is not considered capable of meeting the response time requirement N71-26416* + Boeing Co.. Renton. Wash. Commercial Airplane of 2 to 3 minutes considered a maximum by expert authorities and. Div. therefore. can only be utilized for back up purposes. When this STATIC'TESTS OF A 0.7 SCALE AUGMENTOR WING FLAP survey was first conducted 4 years ago, almost 50% of airports in FOR THE MODiFIED C-EA AIRPLANE: TEST RESULTS the United States had no fire and rescue capability whatsoever. AND ANALYSIS This number has now been reduced to 25 percent. Author 0. L. Harkonen. C. F. Wintermeyer, and F. L. Wright May 1971 296 p refs (Contract NAS2-6025) (NASA-CR-114315; 06-24850) Avail: NTlS CSCLOl C N71-26516# Northrop Corp.. Hawthorne, Calif. Aircraft Div. A static test investigation was made of an augmentor-wing A WIND TUNNEL INVESTIGATION OF JETS EXHAUST- flap system for the modified C-EA jet STOL research airplane. ING INTO A CROSSFLOW. VOLUME 2: ADDITIONAL Tests were conducted using a 0.7 scale model which had a wing DATA FOR THE ONE JET CONFlGURATlON Lynn B. Fricke. Peter T. Wooler, and blenry Ziegler Wright- span of 95 inches, a flap chord of 30 inches, and a full span Patterson AFB. Ohio AFFDL Dec. 1970 508 p double slot nozzle. Flap surface static pressures and total pressures (Contract F33615-69-C-1602) within the augmentor were measured. The augmentor performance (AD-720232; AFFDL-TR-70-154-Vol-2) Avail: NTlS HC was found to be sensitive to the flap coanda surface position and $6.00/MF $0.95 CSCL 2014 flow blockage within the augmentor. Nozzle total pressure ratio A low speed wind tunnel test of a four-foot diamerar circular was also an imponant parameter. The optimum flap pivot point for plate model was conducted to determine surface static pressure the aircraft was determined. The augmentation ratios with this distributions; jet paths. and jet oecay characteristlcs in the presence pivot point location we* near the maximum measured for flap of a crossflow. Data were obtained for a one-jet configuration with angles from 30 to 65 degrees. The maximum augmentation ratio, the jet exiting at a number of angles to the plate and at various based isentropic thrust at the duct entrance, was .1.27 at 30 on velocity ratios and sideslip angles. The report is the second of four degrees flap angle. The corresponding augmentation [:.'> based on volumes. The test model. instrumentation. test procedure, and actual nozzle performance was 1.39. As the augmentor passage reduction and accuracy of the test data were discussed in Volume was blocked off by a moveable segment of the flap, the thrust of the augmentor decreased until slightly negative thrust occurred 1. Author (GRA) with the passage completely blocked. Author
N71-26517# Northrop Corp., Hawthorne, Calif. Aircraft Div. A WIND TUNNEL INVESTIGATION OF JETS EXHAUST- ING INTO A CROSS FLOW. VOLUME 3: ADDITIONAL DATA FOR TWO-JET CONFIGURATIONS N71-26417*# Boeing Co., Seattle, Wash. Commercial .Airplane Lynn 8. Fricke. Peter T. Wooler, and Henry Ziegler Wright- Group. Patterson AFB, Ohio AFFDL Dec. 1970 504 p PARAMETRIC STUDIES OF THE ACOUSTIC BEHAVIOR OF (Contract F33615-69-C-1602) LINED DUCTS AND DUCT LINING MATERIALS FOR (AD-720233; AFFDL-TR-70-154-Vol-3) Avail: NTlS HC TURBOFAN ENGINE APPLICATIONS $6.00/MF$0.95 CSCL 2014 J.Atvars Mar. 1971 216 p refs A low speed wind tunnel test of a four-foot diameter circular (Contract NAS1-10272) plate model with up to three exhausting jets was conducted to (NASA-CR-111887) Avail: NTlS CSCLOlC determine surface static pressure distributions, jet paths, and jet A'flow-duct test facility was developed to simulate turbofan decay characteristics in the presence of a crossflow. Two-jet engine bypass duct geometry and noise environment in the arrangements were tested with the jets exiting normal to the plate laboratory. The facility was used to study the effects of various for three different spacings between the two jets and at a number parameters of sound-absorbent wall liners. The liners consisted of velocity ratios and sideslip angles. Three-jet configuration data basically of a honeycomb sandwich and a porous face sheet. A were obtained with the jets exiting normal to the plate for a description is given of the flow-duct test facility and the data number of velocity ratios and sideslip angles. As a result of this reduction techniques. along with a listing of the reduced test results. investigation, several conclusions are deduced pertaining to the Analyses of the test data showed that the significant design interaction of multiple jets exhausting into a crossflow. The report parameters are the face sheet impedance. treatment length, treatment is the third of four volumes. The test model, instrumentation, test depth, honeycomb cell dimensions, duct size, number of walls procedure, and reduction and accuracy 'of the test data were lined. number of layers in the iinings. air velocity, and direction of discussed in Volume 1: The present volume contains additional data flow with reference to sound propagation. The influence of these pertaining to the two-jet configurations. Author (GRA) parameters is discussed. For simple single-layer linings, a design technology was developed by means of empirical equations. Experimental results show that this technology is valid for duct sizes N71-26526# Peat, Marwlck. Mitchell and Co., Washington. D.C. (or lining separations) from 4 to 12 in., lining depths of 0.25 to TRAFFIC CIRCULATION STUDY, NATIONAL AIRPORT. 1 in., and duct airflow Mach numbers from -0.4 to +0.4. It is BALTIMORE-WASHINGTON AIRPORT ACCESS STUDY: concluded that the flow-duct facility is a useful tool for investigating IMMEDIATE ACTION IMPROVEMENTS the basic properties of acoustically lined ducts. Author Jun. 1970 24 p refs Prepared for Metropol. Wash. Council
47 6 N7 1-26583 of Govt (Rept-3) Avail Issuing Activity The problem of surface transportation access and circulation at Washington National Airport. District of Columbia. IS discussed Recommendations for improving airport access and reducing traffic congestion are presented Author
N71-26626# Civil Aeronautics Board. Washington. D.C. AIR PASSENGER TRAFFIC IN SHORT-HAULMARKETS Max H. Burstein and Donna M. Kaylor Mar. 1971 106 p Avail: Issuing Activity The magnitude, growth. and carrier participation of passenger traffic in major short-haul markets (those under 500 miles) are analyzed. Concise and manageable information relating to growth. competition, and concentration of passenger traffic in short-haul markets, by distance intervals and iridividual markets, is presented. Author
N71-26538# Air Force Systems Command, Wright-Patterson AFB, Ohio. Foreign Technology Div. STABILITY AND CONTROLLABILITY OF SUPERSONIC AIRCRAFT V. Lutskii et al 4 Dec. 1970 10 p Transl. into ENGLISH from Aviatsiya i Kosmonavtika (Moscow). no. 5, 1970 p 34- 35 (AD-720740; FTD-HC-23-601-70) Avail: NTlS CSCL 1/3 A general description is given of methods by which a pilot can control the lateral motion of a supersonic aircraft. G RA
N71-26567# Forsvarets Forskningsanstalt. Stockholm (Sweden). Avdelning 2. MEASUREMENT OF A HELICOPTER'S GYRO DISPLACEMENTS IN SOME DIFFERENT FLYING CONDITIONS [MAETNING AV HELIKOPTRARS GIRROERELSER I NAGRA OLIKA FLYGFALL] C. Borg and B, Hoegrnan Nov. 1969 43 p refs In SWEDISH (FOA-2-C-2356-49472)) Avail: NTlS Measurements of rotations recprded at the helicopter school in Boden are reviewed as a basis for building a,simulator for the study of the helicopter's pilot's capacity to guide collimation guided ATGW from helicopters. The measurements were made with the rate gyro giving angular acceleration and were registered on tape. These signals were later integrated to give the angular deflection. Results are presented in tables and curves for angular rate and deflection. Author,
N71-26583 Rochester Univ., N.Y. A MODEL FOR THE WAKE GEOMETRY OF THE LIFTING ROTOR IN FORWARD FLIGHT AND AN EVALUATION OF THE SENSITIVITY OF COMPUTED BLADE LOADS TO THE WAKE GEOMETRY Mukund Madhav Joglekar (Ph.D. Thesis) 1969 241 p Avail: Univ. Microfilms Order No. 70-2877 Assuming that a helicopter rotor in forward flight can be represented by a flat circular disk with an appropriate steady pressure discontinuity across it, expressions were developed for relating the pressure field to: (1) the total aerodynamic thrust and the total steady pitching and rolling moments experienced by the rotor; or, (2) the time dependent aerodynamic flapping moments at the roots of the blades as they rotate. The selected pressure field satisfies: (1) the requirement of a loss of lift at the center and periphery of the disk, (2) accounts for first and second azimuthal harmonic variations in the lift density. and (31 satisfies Laplace's equation. A digital computing program was written for calculating the velocity field from the selected pressure field and for calculating the streamlines emanating from points above the disk. Two sample cases were chosen, corresponding to the UH-1 two-bladed teetering rotor at advance ratios of 0.26 and 0.08 respectively. Dissert. Abstr.
477 SUBJECT INDEX
AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 8) AUGUST 1971
Typical Subject Index Listing
ACCIDENT PREVENTIORdSuBJECTHEAD'NG 1 measurements, discussing engine operating conditions, speed and attitude an-30521 [ V&SA-C?- 111372 ] Jet aircraft sound spectrum on ground and in air, comparing calculation with experiment A71-30524 Noise measurement data on various types of blown flap configurations for STOL aircraft, NUMBER CONTENT NUMBER discussing integration effects between jet and flap assembly [AIAA PAPER 71-7451 A71-30785 The subject heading is a key to the subject content of the document. The Climbout and landing approach noise measurements Notation of Content (NOCI. rather than the title of the document. is used for three engine turbofan transport aircraft to provide a more exact description of the subject matter. The report number [ NASA-TN-D-61373 N71-24582 helps to indicate the type of document cited (e.g.. NASA report, translation. Interior sound pressure measurements in C-5A NASA contractor report). The accession number is located beneath and aircraft to the right of the Notation of Content. e.g.. N71-1 1466. Under any one [ AD-7197461 N71-25060 subject heading, the accession numbers are arranged in sequence with Acoustic measurements on prop-fan model propulsion system - Vol. 2, appendices the IAA accession numbers appearing first. [ NASA-CR-111842-2] N71-25784 Acoustic measurements on prop-fan model propulsion system [NASA-CR-111842-1] N71-25785 A Familiarization of Peaeral Aviation Administration ABSORBERS (MATERIALS) personnel in acoustic measurement techniques and Absorbent materials for sound attenuation in procedures involved in noise certification of turboreactor ducts, examining flow velocity, aircraft absorbent structure and cladding effects [ HRC-TR-300 3 N71-26304 A71-30518 Techniques and procedures for measuring effective ACCELERATION (PEYSICS) perceived noise level during aircraft noise type Normal accelerations experienced by transpur- certifications aircraft fleet from fatigue load meter data [HHC-TR-300-SUPPL-2] N71-26305 analysis, discussing counting rates seasonal ADJUSTING variations Cam profile selection for adjustment in computing- 871-29788 resolving unit of aneroid sensors of altimeters ACCELERATION TOLERANCE A71-28938 Pilot subjective evaluation of XB-70 aircraft AEBODYHAUIC CEABACTERISTICS response to atmospheric turbulence in comparison Aerodvnamic characteristics similarity and with measured accelerations variation in hypersonic flow transition region A71-29774 from free molecular flow to solid medium ACCIDENT INVESTIGATION A71-29172 Aviation and surface transportatation safety for Elevons as longitudinal and lateral control 1970 with related accident investigations and elements on low aspect ratio wings, calculating recommendations subsonic and supersonic aerodynamic C AR-4 1 N71-24925 characteristics ACCIDENT PREVENTION A71-29190 Aviation and surface transportatation safety for Elliptical cones at large angle of attack, 1970 with related accident investigations and calculating three-coaponent real gas properties recommendations effects on aerodynamic characteristics C AR-4 7 N71-24925 A71-29191 ACOUSTIC ATTENUATION Wing-jet interference effects in cross wind on Absorbent materials for sound attenuation in thrust and aerodynamic characteristics at large turboreactor ducts, exaoining flow velocity, distance from and near ground absorbent structure and cladding effects A71-29207 871-30518 Wind tunnel simulation of viscous hppersonic flow- Noise attenuation prediction in absorbing ducts laminar boundary layer interactions, presenting adaptable to bypass jet engines, using Morse similarity parameter effects on aerodynamic theory characteristics A71-30522 A71-29224 Acoustic linings for attenuation of fan generated Longitudinal stability of ground effect airplane, noise in turbofan engines, considering discussing influence on aerodynamic interaction between analytical lining characteristics of height, ground surface performance prediction and flow duct testing roughness and wing aspect ratio CAIAA PAPER 71-7311 A71-30778 A71-29228 ACOUSTIC DUCTS Aerodynamic behavior of bodies in wake of two Noise attenuation prediction in absorbing ducts dimensional bluff bodies, discussing loads adaptable to bypass jet engines, nsinq Morse 871-29265 theory Soviet book on helicopter design covering 871-30522 aerodynamic properties, power plants, control Flow-duct test facility data on acoustic behavior systems, fatigue minimization and strength of lined ducts and duct-lining materials for analysis turbojet engine applications A71-29944 [NASA-TR-l11887] N71-26417 Time dependent clearance changes effects on ACOUSTIC MEASUBEHENTS aerodynamic characteristics of sectorially sound fields of flying aircraft from noise grooved gas bearings, describing lift and drag
A- 1 AEBODYUAMIC COEFPICIEUTS SUBJECT INDEX
coefficients calculation AEBODYUAMIC HEATIHG A71-30227 Conductive heat transfer effect on temperature Aerodynamic characteristics of low-aspect-ratio distribution in vicinity of uing leading edge in uing mounted on cylindrical body, simulating by hypersonic flight system of horseshoe vortices [ ARC-CP-1126 ] B71-24446 A71-30264 Tests to determine short-term creep of metals and Multimission strategic aircraft installation alloys unaer conditions of aerodynamic heating effects testing in propulsion and aerodynamic with high velocity air flou uind tunnels, yielding flowfield definition, [ NASA-’3-F-13633 ] 871-25822 inlet internal performance, drag, forebody shape Comparison of space shuttle aerodynamic heating and orientation analyses for metallic heat shield and surface [AIAA PAPER 71-7591 A71-30792 insulation concepts 1-1011 Tristar antenna arrangement test results, N71-26054 considering weight, aerodynamic and structural Flow visualization, thermocouple measurements, and design requirements analyses of shock interference heating effects A71-31060 on straight uing space shuttle model Development of mathematical model for opening N71-26057 behavior of parachutes noting drag and velocity Rypersonic shock/density ratio effects in as functions of time aerothermodynamic heating of space shuttle [AD-71 96981 N71-24433 configuration Analysis of empennage loads and aeroelastic N71-26058 response of T-tail transport aircraft in Lee surface flou and aerodynamic heating on delta continuous atmospheric turbulence uing orbiter N71-24996 N71-26060 Flight evaluation of lateral handling, stability, Leeside aerodynamic heating of lifting reentry control, and flying qualities of jet transport vehicle configurations aircraft during up-and-away and approach flight 871-26061 in landing configuration AEBODYBAMIC LOIDS [ NASA-TN-D-6339 ] N71-25537 Supersonic flntter analysis of clamped skeu panels Hypersonic theoretical/experimental correlations uith in-plane forces by Galerkin method, using of aerodynamic characteristics for space shuttle two dimensional static approximation for design aerodynamic loading N71-26066 A71-30607 Hind tunnel tests to determine lou-speed Helicopter rotor blade airload by applying lifting aerodynamic characteristics of large-scale STOL surface solution transport model uith augmented jet flap CARS PREPRINT 5101 A71-31081 [ NASA-TK-X-620 171 N71-26183 Hake model and computer program to compute Analysis of aerodynamic forces on DL-4 lifting geometries. flous and velocity influence entry vehicle and comparison uith theoretical coefficients for helicopter blade load methods calculations [ NASA-TK-X-1994 ] N71-26354 [AHS PREERINT 5231 871-31089 AERODYNAMIC COEFFICIENTS Transonic uind tunnel tests of vertical fin loads Air flou about lou aspect ratio delta uing at and rudder hinge moments on K2-F3 lifting body large angles of attack, deriving lift scale model at Mach 0.50 to 1.30 coefficient [ NASA-TK-X-2286] N71-24581 A71-28282 Analysis of empennage loads and aeroelastic Supercavitating flou past straight cascade uith response of T-tail transport aircraft in arbitrary blade shapes, considering lift and continuous atmospheric turbulence drag coefficients, cavitation number, cavity N71-24996 shape and exit flou conditions AERODYNAMIC NOISE [ASEE PAPER 71-FE-61 A71-29448 Aerodynamic noise produced by supercritical jets, Measurements of aerodynamic drag, interference using high speed flash photography for schlieren lift, and pitching moment on delta wings and shadowgraph studies N71-24573 A71-28767 AERODYNAMIC CONFIGURATIONS Combustion generated aerodynamic noise, Effects of aeroelasticity on static longitudinal considering sound radiation from open turbulent aerodynamic derivatives flames, spectral content, pouer output and N71-24707 origin AERODYNAMIC DRAG [AIAA PAPER 71-7351 A71-30780 Isolated axisymmetric jet engine exhaust nozzles Noise measurement data on various types of blown thrust and drag predictions in sub-, trans- and flap configurations for STOL aircraft, supersonic flight regimes discussing integration effects between jet and [AIAA PAPER 71-7191 A71-30770 flap assembly Fuselage influence on total aircraft drag in [AIAA PAPER 71-7451 A71-30785 subsonic passenger aircraft, considering high AERODYNAMIC STABILITY aspect radio cylindrical fuselages Army rotorcraft performance data, discussing A71-30821 hovering and forward flight performance out of Low aerodynamic drag airfoil designing by ground and level flight pouer requirements and Lighthill method drag and compressibility effects [ ARC-R/B-3618] N71-24498 [AHS PREPRINT 5001 A71-31076 AERODYNAMIC FORCES Forward flight performance of coaxial rigid rotor Photoelectric, bolometric and photographic in NASA uind tunnel, comparing to aerodynamic recording assembly for measurement of light stability with conventional rotors pressure and aerodynamic forces on complex shape [AHS PREPRINT 5241 A71-31090 body in free raolecular flou Least squares method and iteration technique for A71-29155 obtaining aerodynamic stability derivatives Nonlinear mathematical model for dynamical N71-24703 behavior of extensible towing cable subjected to Aerodynamic characteristics of delta wing space aerodynamic forces generated by uniform flow shuttle configurations field, discussing system stability N71-26062 871-31026 Pressure sensor cetvork for measuring liquid Aerodynamic forces produced in turbine stage by dynamic response in flight including fuel tank vane cascade of cascade series acceleration, liquid slosh amplitude, and fuel [NASA-TT-F-136311 N71-25998 depth monitoring Investigation of aerodynamic forces imposed on [NASA-CASE-XLA-055417 ~71-263ai vehicles proposed for operation in improved AERODYNAMIC STALLING urkan transportation system Rotor blade stall induced helicopter control N7 1-261 29 loads, combining unsteady aerodynamics with aeroelastic rotor analysis
A-2 SUBJECT INDEX AIR POLLUTION
CARS PREPRINT 5131 A71-31084 Space shuttle airbreathing propulsion systems Relicopter rotor stall characteristics, requirements and design studies, considering investigating blade flexibility, nnsteady cruise, landing, go-ar.ound and ferry aerodynamics and variable inflow effects capabilities CARS PREPRINT 5201 A71-31086 [AIAA PAPER 71-6621 A71-30731 Retreating blade stall experiments on model AIR CARGO helicopter rotor, considering series of pressure Frankfurt terminal baggage conveyor system, distribution and boundary layer events describing passenger capacity and luggage CARS PREPRINT 5211 A71-31087 handling equipment AERODYNAUICS A71-29312 Soviet book on experimental aerodynamics covering AIR CONDITIONING EQUIPBENT wind tunnels, shock tubes, liquid and gas Performance of aircraft environmental control physical properties, flow parameter measnrement systems under simnlated tactical conditions equipment, etc [ AD-71 9 101] N71-24461 A71-29524 AIR DUCTS Aircraft development facility with wind tunnel Absorbent materials for soand attenuation in testing capability turboreactor ducts, examining flow velocity, [ AD-719802 3 N71-25048 absorbent structure and cladding effects AEROELASTICITY A71-30518 Mechanical support system role in determination of AIR PLOW aeroelastic stability of leeward cylinder Air flow about low aspect ratio delta wing at immersed in wake using undamped flutter theory large angles of attack, deriving lift A71-31021 coefficient Parameters contributing to aeroelastic problems in A71-28282 thermal protection of space shuttle Air bypass behind campressor into variable area N71-24661 exhaust nozzle, obtaining energy losses from gas Aeroelasticity and unsteady flow problems of turbine jet engine indices aircraft A71-28586 N71-2470 6 Flow direction effect on combined forced and free Effects of aeroelasticity on static longitudinal convective heat transfer from cylinders to air aerodynamic derivatives A71-28985 N71-24707 Air flow past small aspect ratio thick-section AERONAUTICAL ENGINEERING wing at small angles of attack, investigating Criteria for converting aeronautical project vortex system effect on flow characteristics in operational targets into actual requirements and absence of lift technical specifications, emphasizing cost A71-29234 effectiveness separation control of two dimensional air flow A71-30824 with turbulent boundary layer along circular Scientific results from ESRO satellites and from cylindrical wall by jets or suction sounding rocket campaign including aeronautical A71-29433 fields, management planning, satellite stratospheric air flow patterns and CAT development, and telecommunication - 1969 report measurements onboard aircraft over and downwind N71-24447 of Western U.S. mountain terrain Tropospheric and ionospheric absorption at VRF for A71-29755 North Atlantic aeronautical satellite sy'*em RF rake probes with high temperature integrated [NASA-TM-X-65507] 871-2491 4 sensor for inflight aircraft engine intake air ABRONAUTICS flow distortion measurements Ristory of development of aviation and A71-30321 astronautics in USSR AIR INTAKES [ NaSA-TT-F- 131421 871-25024 Air inlet for simulation of shock wave separated Survey of very high and ultrahigh frequency flow in supersonic diffusers, deriving pressnre utilization in OS aeronautics for communication variation profile along free boundary satellite frequency assignment A71-29175 C NASA-TE-X-655271 N71-25920 AIR NAVIGITIOB AEROSPACE ENGIEEERIBG Onboard area navigation systems in ATC Aerospace materials - Conference, Anaheim, environment, discussing route structure and California..- April 1971 flight instruments A71-29633 [SAE PAPER 7104551 A71-28332 AEROSPACE ENVIROEIEUTS Area navigation system based on radio aids by SAE/DOT conference on aircraft and environments airborne receivers and sensors for aircraft covering noise pollution, airport noise, sonic movement improvement, noting advantages of pilot booms, regnlatory/legal aspects and air displays pollution [SAE PAPER 7104571 A71-30533 [AIAA PAPER 71-7293 A71-30776 Inertial navigation systems improvements for AEROSPACE IEDUSTRY commercial air transportation, noting digital Instrnmentation in aerospace industry - computer program revision and increased Conference. Las Vegas, May 1971 functional capability 871-30309 [SAE PAPER 7104581 A71-30534 ABROSPACB SYSTEBS Combined inertial and instrument landing aircraft Consideration by NATO of transonic wind tunnel navigation systems with reduced cross runvay requirements to support evolution of position and velocity errors, using optimal aeronautical and aerospace systems during next linear estimation decade 1171-30606 [AGARD-AR-35-71] N71-25073 Air navigation techniques history. considering
AEROTBERBODYNABICS radio, radar, loran Doppler and inertial I Wind tunnel simulations of flow fields and navigation aerothermodynamics of space shuttle orbiters 871-30712 N71-26053 AIR POLLUTION APTBRBURIIBG Modular concept mathematical model for combustion Afterburning turbofan engine thrust calculation by and pollution formation processes in jet engine gas generator method, using F-1118 for combnstors, including turbulent mixing and comparison tests reaction kinetics [AIAA PAPER 71-6803 A71-30744 [AIAA PAPER 71-7147 A71-30766 AIR BREAT6IUG EIIGIBBS SAE/DOT conference on aircraft ana environments Air breathing nuclear propulsion, Considering covering noise pollntion, airport noise, sonic reactor safety in air cushion vehicles and booms, regulatory/legal aspects ana air aircraft pollntion A7 1-29930 [AIAA PAPER 71-7291 A71-30776
A-3 AIR TRAPPIC SUBJECT INDEX
AIR TRAFFIC Aviation within total transport system, discussing Roissy-en-Prance airport, describing construction, decision making and management planning passenger handling. terminal facilities, traffic A71-30165 volume and runway system Air transport development trends, considerinq A71-29309 increased speed and capacity, STOL aircraft, Book on air law and civil air policy covering urban service, and European cooperation for international regulation, air traffic market, manufacturing passenger and cargo services, etc A71-30302 A71-29938 STOL vehicle and systems air transportation Long haul international air transport, analyzing expansion by reducing trip time, congestion, traffic growth rates noise exposures and pollution for DOT, DOD and A71-30161 NASA roles Long term prospects of air traffic development in [SAE PAPER 7104641 871-30535 competition with other modes, estimating VTOL Aviation and surface transportatation safety for service demand 1970 with related accident investigations and A71-30164 recommendations AIR TRAFFIC CONTROL CAR-41 N71-24925 Onboard area navigation systems in ATC AIRBONNE EQUIPMENT environment, discussing route structure and Airborne Doppler radar receiver transmitter flight instruments failure testing by Versatile Avionics Shop Test [SAE PAPER 7104551 871-28332 computer controlled system Optimum functional integration and performance 871-28778 requirements of navigation aids and ATC in Self contained lightweight airborne data terminal area acquisition system for atmospheric and [SAE PAPER 7104561 871-28333 meteorological research, using analog recorder Feasibility of VHF aeronautical satellite system and telemetry system frequency sharing band used by ATC service, A71-30311 employing spatial separation, antenna Integrated flight test data system combining directivity and frequency offset digital airborne data acquisition/recording A71-28873 system with telemetry/microwave link to En route turbojet aircraft flight speed control, computerized ground station assessing impact on ATC procednres A71-30318 A71-28884 Onboard weighing system for gross weight ATC radar display systems mapping techniques using determination and center of gravity location of vectors and optical projections Alouette helicopter, using load sensors, A71-30014 electrical circuits and visual indicators French ATC, discussing automatic coordinator A71-30320 systems, computer utilization and flight plan High speed airborne scanning navigational radar data processing antenna with matched patterns, using offset horn A71-30382 fed relector and polarization modes for improved aaastricht Automatic Data Processing and Display visual display ATC system with digital computers for aiding A71-31036 controllers in issuing instructions and making Helicopter aerial design problems, considering decisions antenna multiplicity use of nonmetallic A71-30383 structures and complexity of airborne radio Aircraft phased arrays for L-band ATC satellite^ systems system application, alleviating problems of 871-31048 power budget and vulnerability to multipath and Interference prediction model for evaluating interference expected interactions between avionics equipment 871-3 10 54 on aircraft Terminal air traffic control facility for approach [AD-718997] 871-24357 systems tests Test procedures to evaluate aircraft borne [ AD-719 104 ] N71-24451 equipment for use in crash rescue operations Evaluation of dual input transponder with upper [ AD-7205631 N71-26195 and lower aircraft antennas as resolution for AIRBORNE/SPACEBOBNE COMPUTERS problems with air traffic control radar beacon Airborne integrated data system capabilities based system limitations on flight tests with commercial aircraft [PAA-NA-71-39] 171-24882 A71-30319 General aviation traffic implied densities and Onboard computer for aircraft engine testing, interaction frequencies computed with model monitoring and data reduction, emphasizing using southern California to judge difficulty automatic in-flight recording for post-flight for naval air traffic displays [AD-719906] N71-25621 [AIAA PAPER 71-6511 A71-30727 AIR TEABSPORTATION Weapons delivery computer for attack helicopters, STOL aircraft/engine integrated systems for medium using planar distributed function generator for distance air transportation, discussing tradeoff general closed form instantaneous solution factors involving performance, noise, weight and capability cost [AHS PREPRINT 5311 A71-31092 [SAE PAPER 7104691 A71-28337 AIRCRAFT SST in relation to U.S. world leadership in air Aeroelasticity and unsteady flow problems of transportation, discussing federal funding needs aircraft for technological capability ensnrance 871-24706 A71-29387 Random process theory method for estimating Integrated short-haul interurban transportation response of flexible airplanes to atmospheric system, considering combination of conventional turbulence jet aircraft, STOL aircraft and high-speed N71-24708 ground transportation Potential feasibility of safe, practical, and [ AIBA PAPER 71-5081 A71-29550 economical air breathing nuclear propulsion Aviation within total transport system - system for aircraft and air cushion vehicles Conference, London, May 1971 [ NASA-TU-X- 67837 ] N71-25524 A71-30158 Calculating and testing antiicing systems of Air transport and travel expansion rate, aircraft and helicopters discussing motivations and cost [AD-7199221 N71-25622 A71-30159 AIRCRAFT ACCIDEIIT IIIVESTIGATIOH Circumstances inducing growth in different air Computerized simnlation techniques for transport sectors, discussing transportation investigating aircraft accidents due to cost, aviation capital requirement and business atmospheric turbulence and leisure air travel A71-29779 A71-30160
A-4 SUBJECT IUDEX AIRCRAFT COBTROL
AIRCRAFT ACCIDEBTS Impedance measurements on modified broadband metal Turbulence-related accidents frequency and antenna for speech communication severity during past few years from worldwide [ FOA-3-C-3602-611 N71-26150 synopsis AIRCRAFT BRAKES ~71-28885 C-5A airplane Be brakes, considering critical U.S. air carrier accidents dne to atmospheric design weight environment for optimum load turbulence, considering in-flight weather carrying capacity problems, airborne meteorological radar. CAT [SAE PAPER 7104271 871-28313 detection systems, etc AIRCRAFT COUUUBICATIOB A71-29770 Blade antenna linear array design for aircraft- Satellite aided aircraft collision avoidance satellite communication, determining mntnal system effective for large number of aircraft influences by array measurements in simulated [NASA-CASE-ERC-l0090] ~71-24948 electrical environment Studying aircraft accidents to determine impact A71-31062 angle and speed criteria for designing nuclear Viability of L band communication system between airplane fission product containment vessel geostationary satellites and aircraft terminals [NASA-TN-X-2245] N71-25411 [NASA-TN-X-65508] N71-24913 Aircraft accident at Miami, Florida involving AIRCRAFT COIIPARTIIEHTS Republic of Ecuador C-54D during climb following Fluidic cabin pressure automatic control systems instrument takeoff for military and civil aircraft, discussing [ NTSB-AAR-71-2] 871-26032 design, operation and performance Test procedures to evaluate aircraft borne ~71-30308 equipment for use in crash rescue operations AIRCRAFT COBFIGUBATIOBS [AD-720563 1 N71-26 195 Aircraft with T tail configuration, examining Survey of civil airports to determine status of dynamic response to lateral gusts crash fire and rescue equipment available for ~71-29786 use following accidents involving scheduled or wind tunnel force test program design for jet local service air carrier aircraft aircraft confiqurations. inclodinq__ propulsion . N71-26466 system simulation AIRCRAFT ABTEBUAS A71-30605 Multiple planar Luneberg lens circular array for AIRCRAFT COBTROL airborne electronically scanned X band narrow V/STOL aircraft instruments, deck display and beam antenna mounted under aircraft nose or automatic flight controls for takeoff and fuselage landing operation ~71-31038 871-29132 Structural design, mechanical stability and Quasi-stationary gliding trajectories of aircraft aircraft compatibility for airborne side-looking in planetary atmosphere during constant control radar antennas. using end fed slotted waveguide of attack and bank angles arrays A71-29185 A71-31041 Elevons as longitudinal and lateral control Flush mounted aeronautical Waveguide antennas with elements on low aspect ratio wings, calculating dielectric plug for 5GRZ operation subsonic and supersonic aerodynamic A71-31043 characteristics Airborne blade antenna tunable for 26-100 MHz by 871-29190 individual bands, using binary related irauctors Jet-supported VTOL aircraft fuel-time-optimal switched by miniature high vacuum relays landing control. using mathematical model, 871-31044 Pontryagin maximum principle and analog computer Low carrier power aircraft antenna module for solution airborne UHF communications system, considering 8-11-29281 range/field strength measurements Third Chance flight control system, discussing A71-31046 aircraft control capability with backup Fincap communication antennas design and hydraulic system after loss of dual main environmental tests tor vibration, acceleration, hydraulic systems due to combat damage waterproofing, salt corrosion, ice formation and 871-29382 compass safe distance Air turbulence primary and secondary effects on A71-31047 aircraft flight and avoidance criteria Helicopter aerial design problems, considering considerations antenna multiplicity use of nonmetallic ~71-29768 structures and complexity of airborne radio V/STOL aircraft flight path and attitude controls systems in turbulence, discussing design based on state ~71-31048 variable methods of control theory Light aircraft notch antenna for efficienf. A71-29776 radiation at HF band lower end and minimal Aircraft gust alleviation, considering movement interference with aircraft structure correction based real time atmospheric A71-31053 turbulence measurement Aircraft phased arrays for L-band ATC satellite system application. alleviating problems of Soviet book on helicopter design covering power budget and vulnerability to multipath and aerodynamic properties, power plants, control interference systems, fatigue minimization and strength A71-31054 analysis High efficiency narrow beam aircraft Cassegrain A71-29944 antenna design for horizon without excessive control, navigation and guidance review, ground illumination considering application of earth reference A71-31056 coordinates for aircraft, missiles and L Dand aircraft antenna array consisting of spacecraft circularly polarized elements and static A71-30710 electronic steering circuits for synchronous VTOL aircraft minimum climb-to-cruise time satellites radio links transition optimal open loop and suboptimal A71-31074 closed loop control synthesis AeLospace antenna design, calculating one- A71-30799 wavelength circular slot aperture radiation from Controlled aircraft motion under strict kinematic circular cylindrical surface constraints in terms of simple subsystems, 871-31075 noting pilots role in Newmark theory Evaluation of dual input transponder with upper A71-31024 and lower aircraft antennas as resolution for Handling qualities of V/STOL research vehicles problems with air traffic control radar beacon during steep terminal area approaches, .system limitations discussing powered lift fan VTOL aircraft [ FAA-N A-7 1-39 ] ~71-24882 limitations and instrument landing approach [ AHS PREPRINT 5441 871-31101
A-5 AIRCRAFT DESIGN SUBJECT IUDEX
Stability, control, and handling quality [SAE PAPER 7104651 A71-30536 characteristics of STOL and V/STOL airplanes Aircraft development facility with wind tunnel N71-24702 testing capability En route aircraft flap control during descent and [AD-719802) N71-25048 holding AIBCRULPT EUGIUES [ ARB-TN-991 N71-24920 VTOL propulsion, discussing gas turbine pressure Comparison of pilot performance nsing center ratio inlet temperatnre and lifting and high stick, dual side stick, and single side stick bypass fans configuration A71-27838 [ AD-7208461 N71-25846 Visible exhanst smoke trails from aircraft jet Direct lift control system having flaps with slots engines, measuring optical density by adjacent to their leading edge and particnlarly photographic photometry adapted for lightweight aircraft [SAE PAPER 7104281 A71-28314 [ NASA-CASE-LAR-10249-11 N71-26110 Rednction gearhox reliability problems from AIRCRAFT DESIGN development and service experience with PT6A Landing load estimation methods for preliminary turboprop engine design weight prediction for military aircraft [SAE PAPER 7104333 A71-28318 A71-28211 Commercial aircraft powerplant development, Economic analysis of subsonic transport airplane discussing engine and components test programs design, evaluation and operation and techniques [SAE PAPER 7104231 A71-28310 [SAE PAPER 7104491 871-28327 FAA aircraft design appraisal for maintainability, Aircraft propulsion system testing, stressing considering maintenance concepts and adverse noise reduction and inlet-engine exhaust system airworthiness situations compatibility [SAE PAPER 7104313 A71-28316 [SAE PAPER 7104501 A71-28328 Nilitary/commercial STOL transport design, Airline engine performance testing from operator discussing performance, payload and equipment perspective, nsing automated test cell data requirements with emphasis on production cost acquisition system benefits [SAE PAPEX 7104511 A71-28329 [ SAE PAPER 7104683 A71-28336 High temperature aircraft gas turbine engine STOL aircraft/engine integrated systems for medium design, discussing developments in manufacturing distance air transportation, discussing tradeoff processes, materials, cooling techniques, factors involving performance, noise, weight and aerodynamic and mechanical design improvements cost [SAE PAPER 7104623 871-28335 [SAE PAPER 7104691 A71-28337 Gas temperature measurement in aircraft combustion Structural fatigue in aircraft design, discussing chambers, using calorimetric probe twin engine transport tests, crack propagation A71-28757 rate, residual strength, etc Aircraft engine production components and alloys A71-29434 mechanical properties evaluation for improved Aircraft capabilities in intraurban transportation reliability of mass produced products for Detroit metropolitan area, considering 871-28944 vehicle design, fleet size, cost and terminal Subsonic and supersonic turbojet aircraft engines location development, discussing design, operation, [AIAA PAPER 71-5041 A71-29548 reliability, weight, fuel consumption and cost Materials and structural design development by A71-29811 high velocity impact testing due to transport Thrust measurement of aircraft propulsion systems, and subsonic military aircraft susceptibility to considering hydraulic piston device, edge bird collision damage clearance. oil quantity and calibration A71-29642 A71-29860 Atmospheric turbulence statistical models concorde power plant fire protection system, assessment for aircraft design and operation, describing prototype engine bay overheat considering CAT and thunderstorm turbulence data detection system and additional IJV optical fire A71-29751 detection system V/STOL aircraft flight path and attitude controls 871-30300 in turbulence, discussing desiqn based on state Aircraft jet engines technological progress review variable methods of control theory over past 25 years, emphasizing industry A71-29776 economics considerations Jet transport aircraft design for safety under air A71-30303 turbulence conditions, considering cruise HF rake probes with high temperature integrated altitude limitations and pitch and g excursion sensor for inflight aircraft engine intake air reduction by special autopilot mode flow distortion measurements A71-29777 A71-30321 Aircraft structural design requirements based on Low cost go/uo-go portable aircraft engine tester statistical analysis of air turbulence intensity connected to engine mounted sensors and gust loads records from large number of A71-30327 research fliqhts sound fields of flying aircraft from noise A71-29784 measurements, discussing engine operating Aircraft design and fatigue life monitoring, conditions, speed and attitude investigating effects of gust velocity frequency 871-30521 distribution in patches of atmospheric Transport aircraft JT9D hiqh bypass ratio engine turbulence development, noting maintainability and A71-29789 stability improvements Air transport development trends, considering [SAE PAPER 7104191 A71-30527 increased speed and capacity, STOL aircraft, Aircraft JT9D engine development for airlipe urban service, and European cooperation for operation, discussing construction, condition manufacturing monitoring, maintenance, noise and smoke A71-30302 reduction Computer aided design program for civil transport [SAE PAPER 7104341 871-30528 aircraft configuration, performance, propulsion, Design interface requirements for optimal aircraft weight and costs to meet given specifications engine condition monitoring system, using A71-30398 parameter, vibration, oil, borescope and Aircraft quantitative maintenance cost radiography analysis requirements translation into design criteria, [SAE PAPER 7104473 A71-30531 considering airline operations influence on V/STOL propulsion units lift ratings based on manufacturer aircraft system requirements [SAE PAPER 7104371 A71-30529 [SAE PAPER 7104711 A71-30537 Commercial vs military design criteria for STOL Onboard computer for aircraft engine testing, transport aircraft, noting landing and takeoff monitoring and data reduction, emphasizing distances and noise levels automatic in-flight recording for post-flight
A-6 SUBJECT INDEX AIRCRAFT MAINTEBABCE
displays over past 25 years, emphasizing industry EAIAA PAPER 71-6511 A71-30727 economics considerations Engine condition monitoring systems, discussing A71-30303 engineering design requirements with respect to AIRCRAFT INSTRUMENTS accessibility. accuracy, economics, Onboard aircraft refractometer design. operation effectiveness, reliability and maintainability and effectiveness [AIAA PAPER 71-6521 A71-30728 A71-28250 VTOL turboshaft engine powered propulsion system Electrical and physical nature of microbial development, detailing design requirements, membranes implicated in aircraft fuel quantity program planning, component research and system probe malfunction integration [SAE PAPER 7104391 A71-28321 [AES PREPRINT 5621 871-31109 V/STOL aircraft instruments, deck display and Evaluation of fuel flowmeter instrumentation automatic flight controls for takeoff and conducted during flight tests landing operation [ AD-7192801 171-24479 A71-29132 Assembly methods for three types of aircraft gas Aircraft instrumentation and data analysis for turbine engines clear air turbulence, including orthogonal [ AD-7198235 N71-25209 components and temperature and wind Pundamentals of aircraft gas turbine engines distributions [ AD-7 19913 3 N71-25808 871-29753 Aircraft gas turbine combustion chamber design Instrumentation in aerospace industry - [ HAL-TR-2081 N71-26298 Conference, Las Vegas, Xay 1971 AIRCRAFT EQUIPMENT 871-30309 Soviet book on airplane and helicopter electrical Aircraft barometric altimeter errors caused by power supply systems covering storage batteries, atmospheric temperatnre deviations from DC generators, alternators, voltage regulators, International Standard Atmosphere current and frequency control, etc 871-30323 A71-29525 Holographic techniques, optical data processing Soviet handbook of aircraft electrical equipment and laser properties for aerospace covering DC and turbine powered generators. instrumentation lubrication materials, electromagnetic A71-30329 interference countermeasures, etc Eeavy lift helicopters IFR hover capability with 871-29530 slung load, discussing sensors controls and Airborne equipment for CAT detection ahead of displays aircraft, considering pulsed Doppler laser and [AES PREPRINT 5401 A71-31097 IR detectors AIRCRAFT LAIDIBG A71-29765 Transport aircraft all weather antomatic landing Test procedures for aircraft defoaaer/defroster-- . operation, examining guidance system and equipment independent monitors [ AD-7191 09 ] N71-24452 [SAE PAPER 7104413 A71-28323 Procedures for evaluatinq compatibilitv of Jet-supported VTOL aircraft fuel-time-optimal aviation materiel with-related equipment landing control, using mathematical model, [ AD-7191071 371-24457 Pontryagin maximum principle and analog computer Performance of aircraft environmental control solution systems under simulated tactical conditions 871-29281 [ AD-719101 ] N71-24461 Automatic aircraft landing system modification for Design, devzlopment, and test of ground support improvement of response to air turbulence equipment for analyzing aircraft equipment effects condition and performance A71-29773 [ AD-7196751 N7 1-24 6 03 Anemometer measurement optimum averaging time of Evaluation of dual input transponder with upper wind speed for conventional aircraft landings and lower aircraft antennas as resolution for 871-30394 problems with air traffic control radar beacon single anemometer wind measurement required for system limitations aircraft lanaing, comparing data from different [FAA-NA-71-39] N71-24882 sampling periods Test procedures to determine ability of aircraft A71-30395 equipment and armament to withstand storage and Combined inertial and instrument landing aircraft operate effectively in tropic environment navigation systems with reduced cross runway [ AD-720570 3 871-26 194 position and velocity errors, using optimal AIRCRAFT FUEL SISTKMS linear estimation Airport jet fuel delivery system salt driers for 871-30606 redncing water content belou saturation, Design and characteristics of continuous wave, lengthening filter life and improving downstream microwave scanning-beam aircraft landing system system components performance operating at C band and superhigh frequencies [SAE PAPER 710440] A71-28322 [ AD-7189721 N71-24555 AIRCRAFT FUELS Climbout and landing approach noise measurements Kerosene type fuels for aircraft gas turbine for three engine turbofan transport aircraft engines, discussing combustion problems, smoke C NASA-TN-D-6137 1 N71-24582 emission reduction and bacterial or fungal AIRCRAFT HAINTENANCE contamination Methods for engine condition monitoring A71-28754 application to airline operation Energy state approximation and supersonic aircraft A71-28177 minimum fuel fixed range trajectory UAC malfunction detection, analysis and recording optimization, noting not convex velocity set system applications in commercial airlines, A71-30609 emphasizing real time response for maintenance AIRCRAFT EAZARDS function Aircraft hazards due to frequent low cloud [SAX PAPER 7104251 871-28311 occurrences at Kenya airport, forecasting FAA aircraft design appraisal for maintainability, weather with statistical analysis and considering maintenance concepts and adverse radiosounding airworthiness situations A71-29 106 [SAE PAPER 7104311 A71-28316 AIRCRAFT EYDRAULIC SYSTEMS Airline operator evaluation of maintainability, Optimization of military VTOL aircraft secondary considering costs and investment return power systems, considering alternate power [SAE PAPER 7104327 A71-28317 source for aircraft hydraulics, pneumatic Bicrobiological contamination of jet aircraft fuel drives, etc tanks in tropical regions, considering [SAE PAPER 7104451 871-28326 maintenance AIRCRAFT INDUSTRY [SAE PAPER 7104381 A71-28320 Aircraft jet engines technological progress review
A-7 BIRCRAFT NOISE SUBJECT INDEX
Transport aircraft JT9D high bypass ratio engine conditions, examining ejection seat design development. noting maintainability and features and tra'jectories stability improvements A71-29385 [SAE PAPER 7104191 171-30527 Atmospheric turbulence effects on handling Aircraft quantitative maintenance cost qualities and structural loads on aircraft requirements translation into design criteria, A71-29787 considering airline operations influence on LOW wing loading sTOL transport ride smoothing manufacturer using Boeing aircraft [SAE PAPER 7104371 871-30529 [ NASA-CE- 11 1819 1 871-24586 Boeing 747 aircraft integrated data system progralo Alleviation of lateral and longitudinal gust for reducing engine maintenance and operating effects on aircraft costs A7 1-24709 [AIAA PAPER 71-6483 A71-30725 Jet vertical takeoff aircraft piloted cockpit Army aircraft automatic inspection and maintenance simulator for controlling aircraft fliaht monitoring system, considering feasibility, performance technology approach and effectiveness [ARC-R/H-3647] N71-25065 [AIAA PAPER 71-6491 A71-30726 AIRCRAFT PRODUCTIOB onboard computer for aircraft engine testing, Aircraft engine production components and alloys monitoring and data reduction, emphasizing mechanical properties evaluation for improved automatic in-flight recording for post-flight reliability of mass produced products displays A71-28944 [AIAA PAPER 71-6511 A71-30727 Complex structural aircraft components Evaluating adequacy of tool sets for aircraft manufacture, using group technology principle maintenance based on subdivision of parts classes [AD-719103] N71-24379 A71-30267 Aircraft maintenance for civil aviation Air transport development trends, considering [AD-720366] N71-25955 increased speed and capacity, STOL aircraft, AIRCRAFT BOISE urban service, and European cooperation for Aircraft noise on and near airports and factors manufacturing affecting its intensity A71-30302 A71-29304 AIRCRAFT RELIABILITY Operations research minimum cost model of aircraft Costs-reliability relationships in helicopter noise abatement in airport communities development testing and demonstration, [AIAA PAPER 71-5253 A71-29551 emphasizing decision making in program sound fields of flying aircraft from noise management measurements, discussing engine operating [SAE PAPER 7104521 A71-28330 conditions, speed and attitude Yak 40 aircraft flight test program, discussing A71-30521 airworthiness requirements, static structural. STOL vehicle and systems air transportation vibration and wind tunnel tests expansion by reducing trip time, congestion, A71-29911 noise exposures and pollution for DOT, DOD and Fail-safe helicopter rotor control design, NASA roles discussing damage tolerant components, redundant [SAE PAPER 7104641 A71-30535 system, failure warning and maintenance Commercial vs military design criterh for STOL [AHS PREPRINT 5501 A71-31102 transport aircraft, noting landing and takeoff AIRCRAFT SAFETY distances and noise levels Airport certification and safety inspection [SAE PAPER 7104651 A71-30536 procedures and minimum safety standards SAE/DOT conference on aircraft and environments [SAE PAPER 7104131 A71-28305 covering noise pollution, airport noise, sonic Plug-in relay hazards and minimization for booms, regulatory/legal aspects and air aircraft flight safety applications pollution 871-28841 [AIAA PAPER 71-7291 A 7 1- 3077 6 Jet transport aircraft design for safety under air Interior sound pressure measurements in C-5A turbulence conditions, considering cruise aircraft altitude limitations and pitch and g excursion [ AD-7197461 N7 1-2 50 60 reduction by special autopilot mode Proceedings of conference to train personnel in A71-29777 conducting aircraft noise certification tests High intensity xeon flashtube lights for [RRC-TR-30O-SUPPL-l] N71-26303 increasing conspicuity of trainer helicopters Familiarization of Federal Aviation Administration during daytime and nighttime flights personnel in acoustic measurement techniques and [ AD-7 186391 N71-24669 procedures involved in noise certification of Potential feasibility of safe, practical, and aircraft economical air breathing nuclear propulsion [ HRC-TR-3001 N71-26304 system for aircraft and air cushion vehicles Techniques and procedures for measuring effective [ NASA-TN-X-67837 1 N71-25524 perceived noise level during aircraft noise type Calculating and testing antiicing systems of certifications aircraft and helicopters [ ARC-TR-300-SUPPL-21 N71-26305 [ AD-7199221 N71-25622 AIRCRAFT PARTS AIRCRAFT SPECIFICATIONS Advanced composite vs conventional material DC 10 specifications for airport planning, components in cost comparison for aircraft parts including ground clearances, payload-range A71-29656 characteristics and jet engine exhaust Complex structural aircraft components velocities manufacture, using group technology principle A71-30239 based on subdivision of parts classes computer aided design program for civil transport A71-30267 aircraft configuration, performance, propulsion, AIRCRAFT PERFORIIABCE weight and costs to meet given specifications Supersonic staggered gutter colander combnstion A71-30398 system for plenum chamber burning on high bypass AIRCRAFT STABILITY Pegasus turbofan engine of Harrier VTOL Longitndinal stability of ground effect airplane, aircraft, noting performance improvement discussing illfloence on aerodynamic 871-28743 characteristics of height, ground surface German monograph on game theory and planning roughness and wing aspect ratio techniques for aircraft evaluation A71-29228 A71-28880 Jet transport aircraft stability and Aircraft flight characteristics dependence on controllability under atmospheric turbulence angle of attack, roll and pitch conditions, discussing longitudinal and lateral- A71-29043 directional characteristics with particular Ejection system performance in relation to attention to unstable spiral mode aircraft performance dependent extreme flight A71-29772
A-8 SUBJECT IADEX AIRPORT PLAANIAG
Pilot subjective evaluation of XB-70 aircraft analysis techniques response to atmospheric turbulence in comparison [ AD-7197561 N71-25092 with measured accelerations Application of photochromic coatings to provide A71-29774 nondestructive inspection for aerospace Eelicopter rotor system vibratory and mechanical materials and structures stability characteristics, investigating [ AD-7202391 871-26383 anisotropically mounted flexible swash plate and anmauEs blade out of track effects Fatigue and fracture mechanics of airframes and [AHS PREPRINT 5111 A71-31082 materials including structural design and stress Hingeless rotor helicopter stability and control analysis techniques characteristics, considering induced flow field, [ AD-7197561 N71-25092 flapwise bending modes and blade-fnselage AIRLINE OPERATIONS
dynamic coupling methods for engine condition monitoring ~ [AES PREPRINT 5411 1171-31fl98 application to airline operation Stability, control, and handling quality A71-28177 characteristics of STOL and V/STOL airplanes Airline operator evaluation of maintainability. N71-247 02 considering costs and investment return Investigation of stability and controllability [SAE PAPER 7104321 1171-28317 parameters for supersonic aircraft under varying Airline engine performance testing from operator aerodynamic load conditions perspective, using automated test cell data [ AD-7198041 N71-25032 acquisition system Stability and controllability of supersonic swept [SAE PAPER 7104511 A71-28329 wing aircraft Commercial airlines flight training program, using [ AD-719803 1 N71-25049 simulation and improved techniques for safety AIRCRAFT STRUCTURES and economy Artificial corrosion pits effect on fatigue [SAE PAPER 7104751 A71-28340 durability of smooth samples and aircraft Aircraft noise on and near airports and factors duraluminum skin elements affecting its intensity A71-27819 A71-29304 Filamentary composite reinforced metal aircraft Helicopter systems operations in, around and structures, considering boron/epoxy in between major metropolitan areas, considering combination with aluminum performance of New York Airways A71-28168 [AIAA PAPER 71-5077 A71-29549 Locating neutral layer and critical curvature Air turbulence primary and secondary effects on radius in aircraft components waffle panels aircraft flight and avoidance criteria under elastoplastic bending considerations A71-28940 A71-29768 Structural fatigue in aircraft design, discussing U.S. air carrier accidents due to atmospheric twin engine transport tests, crack propagation turbulence, considering in-flight weather rate, residual strength, etc problems, airborne meteorological radar, CAT A71-29434 detection systems, etc Soviet book on aircraft materials science and 871-29770 treatment covering steel/cast iron processing, Book on air law and civil air policy covering metallography, heat/thermochemical conditioning, international regulation, air traffic market, surface protection and corrosion preventiou passenger and cargo services, etc A71-29529 A71-29938 Atmospheric turbulence effects on handling Long haul international air transport, analyzing qualities and structural loads on aircraft traffic growth rates 871-2 9787 A71-30161 Nondestructive testing of aircraft structures VTOL and STOL aircraft comparative study covering using thulium and iridium gamma sources site area, cost and noise and toxic gas [JAERI-EEHO-4163] N71-24849 production Development and characteristics of high strength, A71-30163 stress corrosion resistant aluminum alloys for Aircraft JT9D engine development for airline aircraft structures operation, discussing construction, condition [ AD-720398 1 N71-25876 monitoring, maintenance, noise and smoke AIRCRAFT UAKES reduction Vortex wakes behind STOL operations high lift [SAE PAPER 7104341 871-30528 wings. discussing height above ground and Aircraft quantitative maintenance cost various wind tunnel dimensions effects requirements translation into design criteria, A71-28033 considerina airline ooerations influence on Trailing vortices shed by aircraft lifting manufacturer surfaces, noting wake effects importance at low [ SAE PAPER 7104371 A71-30529 speeds Analvsis of maqnitude. qrowth. and carrier A71-28176 pakicipation of passenger traffic in major aIRFoIL PROFILES short-haul markets Aerofoil cascades with axial velocity change in N71-26528 incompressible flow. determining turbine blade aIRPortT PLAAUING force dependence on circulation Airport certification and safety inspection A71-28467 procedures and minimum safety standards Rind tunnel tests of geometrically compatible [SAE PAPER 7104131 871-28305 airfoils for variable chord sailplane National Airport Plan changes since 1946, 871-29257 discussina-- airport management involvement TWOdimensional flow research on high lift increase airfoils for STOL aircraft, using vorticity [ SAE PAPER 7104141 A71-28306 distribution and wind tunnel wall blowing Airport terminal buildinq desiqu and construction, techniques nbting economy and expansibility corequirements A71-29910 [SAE PAPER 7104181 871-28307 High lift and boundary layer separation behavior Aircraft noise on and near airports and factors of sweptback wing airfoil profile noting affecting its intensity trailing and leading edge stall pattern 871-29304 [ ARC-R/H-3648] Nll-24488 Airport pavement design principles, considering AIRFOILS imposed stresses at flight operation areas, Low aerodynamic drag airfoil designing by runways, taxiways, apron and waiting position Lighthill method overrun areas, shoulders and strips [ ARC-R/E-3618 3 N71-24498 A71-29311 AIRPBAUE UATERIILLS Ultra Compact Airport Terminal, describing Fatigue and fracture mechanics of airframes and landside, terminal and airside elements materials including structural design and stress A71-29313
a-9 AIRPORTS SUBJECT IBDBX
Aircraft capabilities in intraurban transportation durability of smooth samples and aircraft for Detroit metropolitan area, considering duraluminnm skin elements vehicle design, fleet size, cost and terminal A71-27819 location Development and characteristics of high strength, [AIAA PAPER 71-5041 871-29548 stress corrosion resistant aluminum alloys for Operations research minimum cost model of aircraft aircraf t st rnctures noise abatement in airport communities [AD-7203981 N71-25876 [AIAA PAPER 71-5251 A71-29551 ALUUIBUI COATIBGS DC 10 specifications for airport planning, Aluminide coatings for nickel-base superalloy including ground clearances, payload-range developed for high temperatnre jet engine characteristics and jet engine exhaust components velocities [ NASA-CR-72863 ] N71-25454 A71-30239 ABEUOUETEBS SAE/DOT conference on aircraft and environments Anemometer measurement optimum averaging time of covering noise pollution, airport noise, sonic wind speed for conventional aircraft landings booms, regulatorp/legal aspects and air A71-30394 pollution single anemoneter wind measurement required for [AIAA PAPER 71-7293 A71-30776 aircraft landing, comparing data from different Analysis of adequacy of access routes to Dulles sampling periods International Airport and need for additional A71-30395 facilities to accommodate future expansion Fan-produced sound pressure fluctuatiou in very [PB-1940943 871-26301 low speed subsonic wind tunnel test stream, Analysis of road traffic problems at Washington noting resulting anemometer calibration errors National Airport and recommendations to improve A71-30526 airport access AB6I.E OF ATTACK [ REPT-3 ] N71-26526 Air flow about low aspect ratio delta wing at AIRPORTS large angles of attack, deriving lift Roissy-en-Prance airport, describing construction, coefficient passenger handling, terminal facilities, traffic A71-28282 volume and runway system Aircraft flight characteristics dependence on A71-29309 angle of attack, roll and pitch nelbourue/Tullamarine airport, describing A71-29043 facilities, capacity, road system, cargo and Quasi-stationary gliding trajectories of aircraft passenger handling areas and runway layout in planetary atmosphere during constant control A7 1-2931 0 of attack and bank angles Survey of civil airports to determine status of A71-29185 crash fire ana rescue equipment availahle for Aypersonic flou around delta uing at small angles use following accidents involving scheduled or of attack, using pressure sources method and local service air carrier aircraft Fredholm integral equation N71-26466 A71-29189 AIRSPEED Elliptical cones at large angle of attack, Altimeter-airspeed and Mach number pressure calculating three-component real gas properties transducer with diaphragm free of tnaperature effects on aerodynamic characteristics and vibration effects A71-29191 871-30322 Spacecraft optimal atmospheric reentry trajectory ALL-WEATHER AIR IAVIGATIOE for minimum flight distance, investigating angle Transport aircraft all weather automatic landing of attack control uith allowance for load operation, examining guidance system and constraints independent monitors A71-29229 [SAE PAPER 7104411 A71-28323 Air flow past small aspect ratio thick-section ALLOYS wing at small angles of attack, investigating Aircraft engine production components and alloys vortex system effect on flow characteristics in mechanical properties evaluation for improved absence of lift reliability of mass produced products A71-29234 A71-28944 Slender cone boundary layer transition under angle Tests to determine short-term creep of metals and of attack at Mach 21 with promoted leeward and alloys under conditions of aerodynamic heating fixed uindward ray uith high velocity air flow A71-29887 [ NASA-TT-F-136331 N71-25822 Supersonic mass flux probe description, discussing ALOUETTE HELICOPTERS inlet geometry, angle of attack and Reynolds and Onboard weighing system for gross weight uach numbers effects on performance determination and center of gravity location of A71-29925 Alouette helicopter, using load sensors, Beasurement of oscillatory pitching moment electrical circuits and visual indicators derivatives on sharp-edged delta wing at vortex 871-30320 breakdown angle of attack ALTILIETERS N71-24572 Cam profile selection for adjustment in computing- ABGOLAR ACCELEBATIOE resolviua unit of aneroid sensors of altimeters Aelicopter gyro displacement measurements at A71-28938 differing flying conditions High altitude balloons pressure-altitude [FOA-Z-C-2356-49-/72/] N71-26567 transducer assembly. discussina electronic AUISOTBOPIC PLATES circuitry, calibration and temperature and Helicopter rotor system vibratory and aechanical vibration effects stability characteristics, investigating, A71-30070 anisotropically mounted flexible swash plate and Altimeter-airspeed and Each number pressure blade out of track effects transducer with diaphragm free Qf temperature [AAS PREPRINT 5111 A71-31082 and vibration effects ABBUAL VARIATIONS A71-30322 Normal accelerations experienced by transport Aircraft barometric altiraeter errors caused by aircraft fleet from fatigue loa3 meter data atmospheric temperature deviations from analysis, discussing counting rates seasonal International Standard Atmosphere variations A71-30323 A71-29788 ALTITUDE AITENNA ARRAYS Radarscope net for target azimuth and distance and Eultiple planar Luneberq lens circular array for for direct altitude readout through beacon airborne electronically scanned X band narrow numerics beam antenna mounted under aircraft nose or A71-28886 fuselage ALUUIIUU ALLOYS A71-31038 Artificial corrosion pits effect on fatigue
A-10 SUBJECT IBDEX ATMOSPHERIC TEMPERATURE
Blade antenna linear array design for aircraft- aircraft and helicopters satellite communication, determining mutual [AD-719922 1 N71-25622 influences by array measurements in simulated ANTISUBMABIUE UARFABE electrical environment Helicopter handling under ASK flight conditions, A7 1-3 1062 discussing sea state effect on low altitude L hand aircraft antenna array consisting of hover stability circularly polarized elements and static A71-29384 electronic steering circnits for synchronous APPLICATIONS TECHNOLOGY SATELLITES satellites radio links ATS 1 and 3 satellite VHF transponders for ships A71-31074 and aircraft location, communication and remote ANTENNA DESIGN sensing, discussing performance test results Structural design, mechanical stability and A71-30898 aircraft compatibility for airborne side-looking APPROACH radar antennas, using end fed slotted waveguide Computerized simulation of V/STOL terminal arrays approach and departure paths at landing sites A71-31041 [NASA-CR-1183151 N71-24869 Flush mounted aeronautical waveguide antennas with APPROACH CONTROL dielectric plug for 5GHz operation Design and characteristics of continuous wave, A71-31043 microwave scanning-beam aircraft landing system Airborne blade antenna tunable for 26-100 KHz by operating at C hand and superhigh frequencies individual bands, using binary related inductors [AD-7189721 N71-24555 switched by miniature high vacuum relays Flight tests for controlling slope approach of A71-31044 short takeoff aircraft Fincap communication antennas design and [ARC-CP-1138] N71-25050 environmental tests for vibration, acceleration, APPROACH INDICATOBS waterproofing, salt corrosion, ice formation and Terminal air traffic control facility for approach compass safe distance systems tests A71-31047 [AD-719104] N71-24451 Helicopter aerial design problems, considering Design and characteristics of continuous wave, antenna multiplicity use of nonmetallic microwave scanning-heam aircraft landing system structnres and complexity of airborne radio operating at C hand and superhigh frequencies systems [AD-7189721 N71-24555 A71-31048 APPROPBIATIOUS Light aircraft notch antenna for efficient Authorization hearings on NASA space flight radiation at HF band lower end and minimal program - Part 4, 1972 interference with aircraft structure W71-25196 A71-31053 aBnm FORCES (UUITED STATES) Aircraft phased arrays for L-band ATC satellite General aviation traffic implied densities and system application, alleviating problems of interaction frequencies computed with model power budget and vulnerability to multipath and using southern California to judge difficulty interference for naval air traffic A71-31054 [AD-7199061 N71-25621 High efficiency narrow beam aircraft Cassegrain ASCENT antenna design for horizon without excessive Aerothermodynamic shock heating of space shuttle ground illumination booster surface during atmospheric ascent A71-31056 N71-26059 L-1011 Tristar antenna arrangement test results, ASPECT RATIO considering weight, aerodynamic and structural Aspect ratio effect on oscillatory pitching moment design requirements derivatives of slender sharp-edged delta wing in A71-31060 incompressible flow Blade antenna linear array design for aircraft- N71-24571 satellite communication, determining mutual ASSEMBLING influences hy array measurements in simulated Assembly methods for three types of aircraft gas electrical environment turbine engines P71-31062 [ AD-71 98231 171-25209 Aerospace antenna design, calculating one- ASTBOUAUTICS wavelength circular slot aperture radiation from History of development of aviation and circular cylindrical surface astronautics in USSR A7 1-31 075 [ NASA-TT-F- 13142 1 171-25024 ABTBNUA FEEDS ATKOSPHEBIC BUTBY High speed airborne scanning navigational radar Conical body lift/drag ratio increase by medge antenna with matched patterns. using offset horn shaped nose, noting applications to space fed relector and polarization modes for improved vehicles entering atmosphere above escape visual display velocity A71-31036 A71-29183 AUTENUA RADIATION PATTERNS ATMOSPHERIC MODELS Feasibility of VHF aeronautical satellite system Atmospheric models of partially trapped waves frequency sharing band used by ATC service, propagation in layer above tropopause uith large esploying spatial separation, antenna stratospheric Scorer parameter directivity and frequency offset 871-29763 1171-28873 ATIOSPBEBIC PHYSICS Light aircraft notch antenna for efficient Self contained lightweight airborne data radiation at HF band lower end and minimal acquisition system for atmospheric and interference with aircraft structure meteorological research, using analog recorder A71-31053 and telemetry system High efficiency narrow beam aircraft Cassegrain A71-30311 antenna design for horizon without excessive Clear air tnrbulence in stratosphere and effects ground illumination on weather formation, atmospheric physics, and A71-31056 supersonic flights Aerospace antenna design, calcnlating one- [ JPBS-53133 3 N71-25746 wavelength circular slot aperture radiation from ATIOSPHEBIC TEuPsBaTaBE circular cylindrical surface Aircraft instrumentation and data analysis for 871-31075 clear air turbulence, including orthogonal AITENNAS components and temperature and mind Aerospace antennas - IEE Conference, London, Jnne distributions 1971 A71-29753 871-31034 Aircraft barometric altimeter errors caused by ABTIICIEG ADDITIVES atmospheric temperature deviations from Calculating and testing antiicing systems of International Standard Atmosphere
A-1 1 ATMOSPHERIC TURBULENCE SUBJECT IUDEX
A71-30323 [HMO-264-TP-1481 N71-24394 ATHOSPEERIC TUBBULEBCE Random process theory method for estimating Turbulence-related accidents fresuencv and response of flexible airplanes to atmospheric severity during past few years-from- worldwide turbulence synopsis N71-24708 ~71-2a885 Alleviation of lateral and longitudinal gust Atmospheric turbulence - Conference, London, May effects on aircraft 1971. 871-24709 871-29749 Analysis of empennage loads and aeroelastic Atmospheric turbulence effect on turbine powered response of T-tail transport aircraft in transport aircraft, discussing gust continuous atmospheric turbulence accelerations, avoidance, detection, forecasting N71-24996 and pilot control Flight evaluations using variable stability A71-29750 aircraft to determine effects of turbulence Atmospheric turbulence statistical models induced aerodynamic disturbances and lateral assessment for aircraft design and operation, directional dynamics on pilot performance considering CAT and thunderstorm turbulence data [ NASA-CR-1718 ] N71-26170 A71-29751 ATOMIZERS Oklahoma and Ealaysia thunderstorms comparison Optical measurement of sprays mean droplet size, based on weather reconnaissance aircraft assessing operating variabJes effect on measurements, considering turbulence patches air-blast atomizer characteristics A71-29752 A71-28756 Stratospheric turbulence correlation to mesoscale Gas turbine engine startup igniter with modified horizontal temperature gradient at altitudes propellant atomizer enhanced by air injection flown by SST from Colascan program A71-28969 A71-29767 ATOMIZIUG Air turbulence primary and secondary effects on Gas turbine engine combustion chamber start-up and aircraft flight and avoidance criteria burning performance, considering air injection considerations and propellant atomization ~71-2976a A71-28968 U.S. air carrier accidents due to atmospheric ATTACK AIBCRAPT turbulence, considering in-flight weather Cheyenne attack helicopter weapons system, problems, airborne meteorological radar, CAT discussing night vision capability, armament. detection systems, etc fire control and navigation equipment A71-29770 integration Flight characteristics under atmospheric [AHS PREPRINT 5301 A71-31091 turbulence conditions, analyzing analog trace Weapons delivery computer for attack helicopters, records of airspeed, normal acceleration, using planar distributed function generator for altitude, air temperature, control surface and general closed form instantaneous solution flight attitude parameters capability A71-29771 [AHS PREPRINT 5311 A71-31092 Jet transport aircraft stability and AUTOUATIC COUTROL controllability under atmospheric +*-rbulence Fluidic cabin pressure automatic control systems conditions, discussing longitudinal and lateral- for military and civil aircraft, discussing directional characteristics with particular design, operation and performance attention to unstable spiral mode A71-30308 A71-29772 French ATC, discussing automatic coordinator Automatic aircraft landing system modification for systems. computer utilization and flight plan improvement of response to air turbulence data processing effects 871-30382 871-29773 Maastricht Automatic Data Processing and Display Pilot subjective evaluation of XB-70 aircraft ATC system with digital computers for aiding response to atmospheric turbulence in comparison controllers in issuing instructions and making with measured accelerations decisions A71-29774 A71-30383 V/STOL aircraft flight path and attitude controls AUTOMATIC FLIGHT COUTBOL in turbulence, discussing design based on state V/STOL aircraft instruments, deck display and variable methods of control theory automatic flight controls for takeoff and 1171-29776 landing operation Jet transport aircraft design for safety under air 871-29132 turbulence conditions. considering cruise Controlled aircraft motion under strict kinematic altitude limitations and pitch and g excursion constraints in terms of simple subsystems, reduction by special autopilot mode noting pilots role in Newmark theory A71-29777 871-31024 Computerized simulation techniques for Helicopter gyro displacement measurements at investigating aircraft accidents due to differing flying conditions atmospheric turbulence [ FOA-2-C-2356- 49-/72/] N71-26567 A71-29779 AUTOMATIC LAUDIBG COBTBOL Commercial aircraft piloting in atmospheric Transport aircraft all weather automatic landing turbulence, discussing aircraft characteristics, operation. examining guidance system and instrumentation, flying procedures, pilot independent monitors training and kinesthetic cues [SAE PAPER 7104411 A71-28323 A71-29782 Automatic landing systems independent monitor for Aircraft structural design requirements based on L-1011 aircraft, providing pilot confidence statistical analysis of air turbulence intensity under reduced visibilities and gust loads records from large number of [SAE PAPER 7104431 A71-28324 research fliqhts Trident aircraft autopilot for automatic landings A71-29784 in blind conditions, discussing operational Aircraft gust alleviation, considering movement problems correction based real time atmospheric A71-29261 turbulence measurement Automatic aircraft landing system modification for A71-29785 improvement of response to air turbulence Atmospheric turbulence effects on handling effects qualities and structural loads on aircraft A71-29773 A71-29787 AUTOMATIC PILOTS Meteorological radar for detection of Trident aircraft autopilot for automatic landings thunderstorms, hail, and turbulence hazardous to in blind conditions, discussing operational aviation noting echo interpretation and radar problems transmission 171-29261
A-12 SUBJECT INDEX BOEIEG AIRCRAFT
AUTO'3ATIC TEST EQUIPMENT A71-29774 Airborne Doppler radar receiver transmitter. BACKUPS failure testing by Versatile Avionics Shop Test Third Chance flight control system, discussing computer controlled system aircraft control capability with backnp A71-28778 hydraulic system after loss of anal main Gas tnrbine engine condition analysis by digital hydranlic systems due to combat damage computer and fault isolation techniques A71-29382 [SAE PAPER 7104481 A71-30532 BAGGAGE Army aircraft automatic inspection and maintenance Frankfurt terminal baggage conveyor system, monitoring system, considering feasibility, describing passenger capacity and luggage technology approach and effectiveness handling equipment [AIAA PAPER 71-6491 A71-30726 871-29312 Onboard computer for aircraft engine testing, BALLISTIC TRAJECTORIES monitoring and data rednction, emphasizing Roll moment of inertia to static margin ratio automatic in-flight recording for post-flight effect on yaw of repose angle magnitude in displays ballistic match of projectiles [AIAA PAPER 71-6511 A71-30727 A71-29890 AUTOUATION BASE PRESSURE Automated orifice drilling optimal treatment Low thrust jet effect on base pressures on routines, including proper timing and adequate boat-tailed afterbodies in Mach number 0.8-1.2 total depth allowance flow A71-28941 A71-29889 AUTOUOBILE ENGIEES BERYLLIUM Chemical kinetic calculation of nitric oxide C-5A airplane Be brakes, considering critical formation in spark ignition automobile engines design weight environment for optimnm load and gas turbine combustors carrying capacity A71-30454 [SAE PAPER 7104271 A71-28313 AUXILIARY POUER SOURCES BIBLIOGRAPHIES Optimization of military VTOL aircraft secondary Aeroelasticity and unsteady flow problems of power systems, considering alternate power aircraft source for aircraft hydraulics..- pneumatic N71-24706 drives, etc BIRDS rSAE PAPER 7104451 A71-28326 Baterials and structural design development by Gas turbine auxi1ia;y power unit accessories, high velocity impact testing due to transport discussing high energy igniters. cables and and subsonic military aircraft susceptibility to connectors, thermocouples and speed and bird collision damage temperature monitoring equipment A71-29642 A71-29262 BLADE TIPS ABIOEICS Combination tone noise generation from turbofans Airborne Domler radar receiver transmitter with supersonic fan blade tip speed, determining failure testins by Versatile Avionics Shop Test sound power distribution among engine rotation computer controlled system frequency harmonics A71-28778 [AIAA PAPER 71-7301 A71-30777 Interface IC circuits for driving high voltyge BLADES transistor switches from low level logic Inputs, Helicopter rotor stall characteristics, noting avionics application investigating blade flexibility, unsteady A71-28910 aerodynamics and variable inflou effects Interference prediction model for evaluating [ AHS PREPRINT 5201 A71-31086 expected interactions between avionics equipment BLIED LANDIEG on aircraft Trident aircraft autopilot for automatic landings [AD-7189971 N71-24357 in blind conditions, discussing operational Development and characteristics of electronic problems equipment for digital processing of stochastic A71-29261 signals for military aircraft avionics systems BLOUDOUN UIND TUNEELS [ AD-719822 1 N71-24954 Hypervelocity blowdown nitrogen wind tunnel with AXIAL FLOU graphite resistance heater noting nozzles, Aerofoil cascades with axial velocity change in diffnser, and calibration incompressible flow, determining turbine blade [ IC-AERO-71-01 3 N71-24675 force dependence on circulation BLOSING 871-28467 Low-speed wind tunnel longitudinal stability tests Multistage axial flow compressors on digital on sweptback wing model with blowing at leading computer, testing gas dynamic design in final edge slats and trailing edge flaps for Buccaneer adjustment phase aircraft performance A71-28584 [ ARC-R/M-3655] N71-24565 Monograph on potential flow interaction between BLUFF BODIES blade rows in axial flow compressors covering Aerodynamic behavior of boaies in wake of two mathematical model. numerical analysis and dimensional bluff bodies, discussing loads experiment A71-29265 A71-28883 BOATTAILS AXIAL PLOP TURBIEBS Low thrust jet effect on base pressures on Beasurement errors in testing single stage air boat-tailed afterbodies in Mach number 0.8-1.2 driven axial flow compressors and turbines flow A71-28582 A71-29889 Axial flow turbines comparative performance tests BODIES OF RBVOLUTIOE under steady and pulse flow conditions for Soviet papers on three dimensional structures turbocharger application covering strength and stability of compound A71-29819 curvatnre shells, bodies of revolution and AXISIIEETRIC FLOP multilayer plates Axisymmetrical three component flow equations for A71-30888 incompressible viscous fluid in cylinder with BODT-UIEG AND TAIL COBFIGURATIONS rotating disk Minimum drag wing-fuselage combination for A71-30855 supersonic speeds and prescribed lifting force, longitudinal moment and volume, using method of successive approximations B 871-29182 B-70 AIRCRAFT BOEING AIRCRAFT Pilot subjective evaluation of XB-70 aircraft Low wing loading STOL transport ride smoothing response to atmospheric turbulence in comparison using Boeing aircraft with measured accelerations [ NASA-CR- 11 1819 ] N71-24586
A-13 BOEENG 747 AIRCRAFT SUBJECT INDEX
BOEIBG 447 AIRCRAFT Boeing 747 crew members training program. describing ground trainins. classrooms. inertial c navigation system and cockpit trainers~ C-5 IHRCRAFT rSAE PAPER 7104731 A71-28339 C-5A airplane Be brakes, considering critical Boeing 747 aircraft -integrated data system program design weight environment for optimum load for reducing engine maintenance and operating carrying capacity costs [ SAE PAPER 7104271 A71-28313 [AIAA PAPER 71-6483 A79-30725 Interior sound pressure measurements in C-58 BOOSTER ROCKETS aircraft Aerothermodynamic shock heating of space shuttle [ AD-71 9746 1 N71-25060 booster surface durina atmosDheric ascent C-5Y AIRCRAFT N71-26059 Aircraft accident at Xiami. Florida involving BOUBDARY LATER COBTROL Republic of Ecuador C-54D during climb following Separation control-of two dimensional air flow instrument takeoff with turbulent boundary layer along circular [ NTSB-BAR-71-2 ] N71-26032 cylindrical wall by jets or snction CABLES A71-29433 Nonlinear mathematical model for dynamical Bigh entrainment constant area multiple nozzle behavior of extensible towing cable subjected to ejectors with two mixing tube lengths for aerodynamic forces generated by uniform flow boundary layer control, estimating performance field, discussing system stability with analytical model A71-31026 [ASME PAPEE 71-FE-341 A71-29469 C&LIBRATING BOUNDARY SAYER SEPBRATIOB Fluctuating pressure measurements in jet engine High lift and boundary layer separation behavior testing, using miniature transducers with of sweptback wing airfoil profile noting calibration and data acquisition equipment trailing and leading edge stall pattern A71-30325 [ ARC-R/M-3648] N71-211488 Aircraft flight load measurements in high BOUNDARY LAYER TRANSITION temperature environment, determining optimal Slender cone boundary layer transition under angle strain gage installation and calibration of attack at Bach 21 with promoted leeward and 1171-30681 fixed windward ray CALIFORNIA A71-29887 General aviation traffic implied densities and BOUNDART LAYERS interaction frequencies computed with model Data correlation and effectiveness prediction from using southern California to judge difficulty film cooling injection geometries, considering for naval air traffic finitely thick slot lip and boundary layers [ BD-7199061 N71-25621 871-28751 CABS Retreating blade stall experiments on model Cam profile selection for adjustment in computing- helicopter rotor, considering series of pressure resolving unit of aneroid sensors of altimeters distribution and boundary layer events A71-28938 [AHS PREPRINT 5211 871-31087 CARBON Application of research in panel flut’er and Carbon deposition rates in gas turbine engine boundary layer thickness to space shuttle cornbustion chambers with airstream-mechanical N71-24660 propellant atomization Flow meter for measuring stagnation pressure in A71-28970 boundary layer around high speed flight vehicle CARGO AIRCRAFT [NASA-CASE-XFR-O2007] N71-24692 Soviet Bil V-12 heavy lift helicopter for civil BRAYTON CYCLE and military missions, noting turbine engines. Design point characteristics of 15-80 kwe nuclear rotor configuration, cargo hold and navigation reactor Erayton cycle power system system [ NASA-TM-X-678 11 1 N71-24689 A71-30420 Predicted performance of 15-80 kwe reactor Brayton CARGO SHIPS power system over range of operating conditions Army/Navy operational evaluation of offshore [ NASA-TM-X-678 331 N71-24690 containershhips discharge by CH-54 helicopters Motor starting techniques for 2-15 kW Brayton [AHS PREPRINT 5731 A71-31114 space power system CASCADE FLOW [NASA-TM-X-678191 N71-24691 Aerofoil cascades with axial velocity change in BRISTOL-SIDDELEY OLPHPUS 593 ENGINE incompressible flow, determining turbine blade Olympus 593 Concorde enqine combustion system. force dependence on circulation discussing operating conditions, combnstion A71-28467 performance criticality and altitude relighting Supercavitating flow past straight cascade with A71-28740 arbitrary blade shapes, considering lift and Olympus 593 supersonic engine lubricants tests. drag coefficients, cavitation number, cavity defining requirements in terms of bulk thermal shape and exit flow conditions stability, resistance to hot bearing breakdown, [ASME PAPER 71-FE-61 A71-29448 oil mist coking. etc Two dimensional jet flap cascades, presenting A71-29826 stream deflection angles as function of jet to BUCCANEER PIRCRAFT mainstream momentum flux Low-speed wind tunnel longitudinal stability tests f ASME PAPER 71-FE-14 1 871-29453 on seeptback wing model with blowing at leading CASCADES edge slats and trailing edge flaps for Buccaneer Aerodynamic forces produced in turbine stage by aircraft performance vane cascade of cascade series [ ARC-R/M-3655] N71-24565 [ NASA-TT-F- 13631 3 N71-25998 BUFFETING CASSEGRBIN ANTENNAS Transonic flutter and buffeting for elastic wind High efficiency narrow beam aircraft Cassegrain tunnel models of straight wing proposed for antenna design for horizon without excessive space shuttles ground illumination N71-24659 A71-31056 Buffet response of straight wing and delta wing CAVITATION FLOW model of space shuttle launch configuration Structure and shape of vortex wake associated with N7 1-24662 oblique flow past multiblade hinged rotor, using BURNING BATE cavitation method Gas turbine enqine combustion chamber start-up and A71-29217 burning performance, considering air injection CilBITY RESOBATORS and propellant atomization Heat transfer within resonant cavities at subsonic 871-28968 and supersonic flow, discussing wind tunnels, test procedures and data reduction [ASME PAPER 71-FE-91 A7 1-29450
A-14 SUBJECT IADEX COPlBUSTION
CENTER 3F GRAVITY Plightworthy 25-foot diameter proprotor Hind Onboard weighing system for gross weight tunnel test, considering civil and military need determination and center of gravity location of for VTOL transportation Alouette helicopter, using load sensors, [AHS PREPRINT 5011 A71-31077 electrical circuits and visual indicators General aviation traffic implied densities and A71-30320 interaction frequencies computed with model CERTIPICATIOA using southern California to judge difficulty Airport certification and safety inspection for naval air traffic procedures and minimum safety standards [ AD-71 99061 N71-25621 [SAE PAPER 7104131 A71-28305 Aircraft maintenance for civil aviation Proceedings of conference to train personnel in [ AD-720366 ] N71-25955 conducting aircraft noise certification tests Analysis of maquitude. growth, and carrier [ HRC-TR-300-SUPPL-11 N71-26303 participation of passenger traffic in major CE-46 EELICOPTER short-haul markets Integral spar inspection system for making CH-46 N71-26528 rotor blade fail-safe CLEAR AIR TURBULENCE [IHS PREPRINT 5511 A71-31103 Aircraft instrumentation and data analysis for CE-47 EELICOPTER clear air turbulence, including orthogonal Turbine engine foe1 control stability on CH-47C components and temperature and Hind helicopter, using flight tests and lag damper distributions simulation A71-29753 [AHS PREPRINT 5601 A71-31107 Stratospheric air flow patterns and CAT Boeing 347 helicopter program consisting of measurements onboard aircraft over and downwind analysis. vibration simulation. Hind tunnel, of lestern U.S. mountain terrain vhirl tower and bench tests A71-29755 [AHS PREPRINT 5711 A71-31112 Thunderstorm, CAT, weather and mountain wave CB-54 HELICOPTER induced turbulence forecasting and analysis for Army/Navy operational evaluation of offshore transport aircraft containershhips discharge by CH-54 helicopters 871-29764 [AHS PREPRINT 5731 A7l-31114 Airborne equipment for CAT detection ahead of CIRCULAR CONES aircraft, considering pulsed Doppler laser and Unsteady hypersonic self similar gas floar and drag IR detectors on circular cone accelerated according to power 871-29765 law, using small perturbation theory Clear air turbulence in stratosphere and effects A71-29205 on Heather formation, atmospheric physics, and CIRCULAR CYLINDERS supersonic flights Mechanical support system role in determination of [ JPRS-53133 ] N71-25746 aeroelastic stability of leeuard cylinder CLEABAACES immersed in wake using undamped flutter theory Time dependent clearance changes effects on A71-31021 aerodynamic characteristics of sectorially CIVIL AVIATIOX grooved gas bearings. describing lift and drag EAC malfunction detection, analysis and recording coefficients calculation system applications in commercial airlines, A71-30227 emphasizing real. time response for maintenanbe CLIPlBIBG FLIGHT function Climbout and landing approach noise measurements [SAE PAPER 7104251 871-28311 for three engine turbofan transport aircraft commercial airlines fliqht traininq proqram. usinq [ NASB-TN-D-61371 N71-24582 simulation and improved techniques-fo; safety Computerized simulation of V/STOL terminal and economy approach and departure paths at landing sites [SAE PAPER 7104751 A71-28340 [ NASA-CR-1183151 871-24869 Commercial V/STOL and jet VTOL transport, Aircraft accident at aiami, Florida involving discussing Do-31 test results, landing approach. Republic of Ecuador C-54D during climb following air traffic control automation and electronic instrument takeoff control [ NTSB-AIR-7 1- 2 7 N71-26032 871-29131 CLOUD COVER Book on air law and civil air policy covering Aircraft hazards due to frequent low cloud international reqnlation. air traffic market, occurrences at Kenya airport, forecasting passenger and cargo services, etc reather with statistical analysis and A71-29938 radiosounding Air transport and travel expansion rate, A71-29106 discussing motivations and cost CLOUDS 871-30159 Aircraft mounted infrared detectors for remote Circumstances inducing growth in different air measurements of optical cloud properties transport sectors, discussing transportation N71-25260 cost, aviation capital requirement and business COANDI EFFECT and leisure air travel Propulsion, guidance and stahility of ground A71-30160 effect vehicle with perimetric Coanda fluid Long haul international air transport, analyzing boundary traffic growth rates 871-29308 A71-30161 COCKPIT SIPlULATORS civil aviation customer /operator, pass.enger and Boeing 747 crew members training program, community/ needs, describing STOL and V/STOL describing ground traininq, classrooms, inertial aircrafts navigation system and cockpit trainers 871-30 162 [ SAE PAPER 7104731 871-28339 Computer aided design program for civil transport Jet vertical takeoff aircraft piloted cockpit aircraft configuration, performance, propulsion, simulator for controlling aircraft flight weight and costs to meet given specifications performance A71-30398 [ ARC-R/M-3647] N71-25065 Soviet Mil V-12 heavy lift helicopter for civil COLLISION AVOIDAACE and military missions, noting turbine engines, Satellite aided aircraft collision avoidance rotor configuration, cargo hold and navigation system effective for large number of aircraft system [NASA-CASE-EHC-10090] N71-24948 A71-30420 COHBUSTIBLE FLOB Inertial navigation systems improvements for Soviet papers on combustion processes in turbulent commercial air transportation, noting digital and laminar flows of kerosene and gasoline computer program revision and increased mixtures, stressing gas turbine engines problems functional capability A71-28954 [ SAE PAPER 7104581 A71-30534 COBBUSTIOH Combustion and heat transfer in gas turbine
A-15 COMBUSTION CHAMBERS SUBJECT INDEX
systems - Conference, Cranfield. England, April COMMERCIAL AIHCRAFT 1969 Military/commercbal STOL transport design, A71-28739 discussing performance, payload and equipment COIIBUSTION CHAMBERS reauirements with emDhasis on Droduction cost Olympus 593 Concorde engine combustion system, benefits discussing operating conditions, combustion [SAE PAPER 7104681 871-28336 performance criticality and altitude relighting Cost efficient sound limit expenditnres per A71-28740 parameter unit in commerciai transport- aircraft RE 162 turbojet engine combustors for VTOL design aircraft, achieving ignition by two pressure jet A71-28945 atomizers operative during starting cycle Commercial aircraft piloting in atmospheric A71-28742 turbnlence, discussing aircraft characteristics, Diffusion and thermal mechanism ignition theories, instrumentation. flying procedures, pilot applying to altitude relighting of gas turbine training and kinesthetic cues engine combustors A71-29782 A71-28745 Airborne inteqrated data system capabilities based Annular vaporizing combustion chamber with film on flight tests with commercial aircraft cooling, determining flame temperature under A71-303 19 supersonic flight conditions Commercial vs military design criteria for STOL 871-28749 transport aircraft, noting landing and takeoff Gas turbine engine combustion chamber start-up and distances and noise levels burning performance, considering air injection [SAE PAPBR 7104653 871-30536 and propellant atomization Analysis of magnitude, growth, and carrier A71-28968 participation of passenger traffic in major Carbon deposition rates in gas turbine engine short-haul markets combustion chambers with airstream-mechanical N71-26528 propellant atomization COMEUNICATION SATELLITES 871-28970 Feasibility of VHF aeronautical satellite system Gas turbine engine combustion chamber outlet, frequency sharing band used by ATC service, noting 3as flow temperature field peripheral employing spatial separation, antenna nonuniformity directivity and frequency offset A71-28972 871-28873 Analytical model of compressor sensitivity to Survey of very high and ultrahigh frequency transient and distorted transient flows, utilization in US aeronautics for communication considering inlet duct, compressor stages and satellite frequency assignment combustor up to turbine nozzles [ NASA-TN-X-655273 N71-25920 [AIAA PAPER 71-6701 871-30734 COMPATIBILITY Nodular concept mathematical model for combustion Procedures for evaluating compatibility of and pollution formation processes in jet engine aviation materiel with related equipment combustors, including turbulent mixing and [AD-7191071 871-24457 reaction kinetics COMPONENT RELIABILITY [AIAA PAPER 71-7141 871-30766 Reduction gearbox reliability problems from Aircraft gas turbine combustion chamber design development and service experience with PT6A [ NAL-TR-208 ] N71-26298 turboprop engine COHBUSTION EFFICIEHCY [SAE PAPER 7104331 871-28318 Continuous combustion gas turbine with stepwise Fail-safe helicopter rotor control design, heat release, investigating ideal thermal discussing damage tolerant components, redundant efficiency cycle of gas overexpansion, cooling system, failure warning and maintenance and compression [AHS PREPRINT 5501 A71-31102 A71-28583 Conference on fatigue life in helicopter Olympus 593 Consorde engine combustion system, components discussing operating conditions, combustion . [DLR-MITT-70-01] N71-24385 performance criticality and altitude relighting Dynamic tests of helicopter components A71-28740 N71-24388 Gas-air mixture requirements for turbine and Structural stability tests of helicopter injection burner combustion efficiencies components [ AD-7198341 N71-25359 N71-24390 COMBUSTION PEPSICS Aluminide coatings for nickel-base superalloy Combustion generated aerodynamic noise, developed for high temperature jet engine considering sound radiation from open turbulent components flames, spectral content, power output and [ NASA-CR-72863 ] 871-25454 origin COMPOSITE MATERIALS [AIAA PAPEB 71-7351 A71-30780 Filamentary composite reinforced metal aircraft COMBUSTlON PRODUCTS structures, considering boron/epoxy in Chemical kinetic calculation of nitric oxide combination with aluminum formation in spark ignition automobile engines A71-28168 and gas turbine combustors Advanced composite vs conventional maxerial A71-30454 components in cost comparison for aircraft parts COMBUSTIOH STABILITY 871-29656 Turbopropulsion systems thrust augmentor Composite materials application to V/STOL combustion instability, discussing physical prop/rotors, determining material properties causes due to various. pressure oscillation modes parametric effect on frequencies and weight by [AIAA PAPER 71-6971 A71-30756 Southwell coefficients Turbojet and turbofan augmentors combustion [AHS PREPRINT 5541 ’ A71-31106 instability, discussing pressure oscillations COMPOUHD EELICOPTERS elimination by screech liner and flameholder Electromechanical control system synthesis for design compound hingeless rotor helicopter, using root [AIAA PAPER 71-6981 A71-30757 locus method with transfer functions from Acoustic liner design for propellant combustion airframe motion linear model instability and jet aircraft noise suppression, [AES PREPRINT 5361 871-31096 discussing cross flou and oscillatory pressure High performance UH-1 compound helicopter high effects speed flight research, considering rotor loads, [AIAA PAPER 71-7573 A71-30791 stability, control ana flying qualities COMMERCE [AHS PREPRINT 5701 A71-31111 Characteristics ana cost analysis of nuclear AH-56A compound helicopter rigid rotor stability powered air cushion vehicles for oceanic and handling qualities, using flight, whirl commercial operations tower and wind tunnel tests [ NASA-TN-X-22931 N71-25783 [AHS PREPRINT 5741 A71-31115
1-16 SUBJECT IUDEX COUTROL THEORY
COHPRESSIBILITY EFFECTS A71-29610 Army rotorcraft performance data, discussing COUDUCTIVE HEAT TRAUSPER hovering and forward flight performance out of Static strain measurements on Ti specimen ground and level flight power requirements and subjected to different conductive heating rates. drag and compressibility effects testing various gages [AHS PREPRINT 5001 A71-31076 A71-29833 COlPRESSIOU LOADS conductive heat transfer effect on temperatnre Pisa University Aeronautical Institute activities distribution in vicinity of wing leading edge in /1960-1970/. considering supersonic and subsonic hypersonic flight flow research, thin stiffened shells fatigue [ ARC-CP-112 6 ] N71-24446 under compressive or tensile loads, etc COUFEREUCES A71-30822 Technical. sales/marketing and management COMPRESSOR BLADES Conference, Coronado, California, Hay.4971 Monograph on potential flow interaction between A71-28164 blade rows in axial flow compressors covering Combustion and heat transfer in gas turbine mathematical model, numerical analysis and systems - Conference, Cranfield. England, April experiment 1969 A71-28883 A71-28739 COMPRESSORS Aerospace materials - Conference, Anaheim, Air bypass behind compressor into variable area California, April 1971 exhaust nozzle, obtaining energy losses from gas A71-29633 turbine jet engine indices Atmospheric turbulence - Conference, London, May A71-28586 1971 COMPUTER PROGRAMS A71-29749 French ATC, discussing automatic coordinator Dynamic testing - Conference. London, January 1971 systems, computer utilization and flight plan A71-30053 data processing Aviation within total transport system - A71-30382 Conference. London, Uay 1971 Computer aided design program for civil transport A71-30158 aircraft configuration, performance, propulsion, Instrumentation in aerospace industry - weight and costs to meet given specifications Conference, Las Vegas, Kay 1971 A71-30398 A71-30309 Inertial navigation systems improvements for Telemetering - IEEE Conference, Eashington, D.C., commercial air transportation, noting digital April 1971 computer program revision and increased 871-30896 functional capability Aerospace antennas - IEE Conference, London, June [SAE PAPER 7104581 871-30534 1971 Lou aerodynamic drag airfoil designing by A71-31034 Lighthill method Conference on fatigue life in helicopter [ ARC-R/M-3618] N71-24498 components COMPUTER TECEUIQUES [DLR-KITT-70-01] 871-24385 Gas turbine engine condition analysis by digital Conference on dvnamics and aeroelasticitv of soace computer and fault isolation techniques shuttle [SAE PAPER 7104483 A71-30532 [ NASA-TK-X- 22741 N71-24651 onboard computer for aircraft engine testing, Proceedinqs of conference to train personnel in monitoring and data reduction, emphasizing conducting aircraft noise certification tests automatic in-flight recording for post-flight [ HRC-TR-300-SOPPL- 11 N71-26303 displays CONGRESS [AIAA PAPER 71-6511 A71-30727 Authorization hearings on NASA space flight 'OHPUTERIZED DESIGN program - Part 4, 1972 Computer aided design program for civil transport N71-25196 aircraft configuration, performance, propulsion, CONICAL BODIES weight and costs to meet given specifications Conical body lift/drag ratio increase by wedge A71-30398 shaped nose, noting applications to space Hypersonic theoretical/experimental correlations vehicles entering atmosphere above escape of aerodynamic characteristics for space shuttle velocity design A71-29183 N71-26066 CONICAL FLOW COHPUTERIZED SIHULATIOU Elliptical cones at large angle of attack, Computerized simulation techniques for calculating three-component real gas properties investigating aircraft accidents due to effects on aerodynamic characteristics atmospheric turbulence A71-29 19 1 A71-29779 COUTROL EQUIPUENT Computerized simulation of V/STOL terminal Fluidic cabin pressure automatic control systems approach and departure paths at landing sites for military and civil aircraft, discussing [ NASA-CR-1183153 N71-24869 design, operation and performance COUCOEDE AIRCRAFT A71-30308 Olympus 593 pure jet twin shaft engine development Supersonic aircraft lateral control equipment program for Concorde, discussing engine [ AD-7207401 N71-26538 evolution, design considerations and flight COUTROL STABILITY development Turbine engine fuel control stability on CH-47C [SAE PAPER 7104221 871-28309 helicopter, using flight tests and lag damper Olympus 593 Concorde engine combustion system, simulation discussing operating conditions, combustion [AHS PREPRINT 5601 A71-31107 performance criticality and altitude relighting COUTROL SURFACES A71-28740 Hypersonic flight load bearing refractory alloy Concorde SST flight test equipment installation control surface protective coatings, emphasizing with PCM recording and visual instruments oxidation screening tests A71-30055 A71-29646 Concorde power plant fire protection system, COUTROL TEEORY describing prototype engine bay overheat controlled aircraft motion under strict kinematic detection system and additional UV optical fire constraints in terms of simple subsystems, detection system noting pilots role in Newmark theory A71-30300 A71-31024 COUDUCTIAG FLUIDS Hingeless rotor helicopter stability and control Incompressible conducting fluid plane jet characteristics, considering induced flow field. expansion in homogeneous slipstream, deriving flapwise bending modes and blade-fuselage partial differential equations for nonconduction dynamic coupling approximation [AHS PREPRINT 5411 A71-3 1098
A-17 CORTROLLABILITY SUBJECT IBIDEX
CONTBOLLaBILITY emphasizing decision making in program Helicopter handling under ASW flight conditions, management discussing sea state effect on low altitude [SAE PAPER 71011523 A71-28330 hover stability Aircraft capabilities in intraurban transportation A71-29384 for Detroit metropolitan area, considering Commercial aircraft piloting in atmospheric vehicle design. fleet size, cost and terminal turbulence, discussing aircraft characteristics, location . instrumentation, flying procedures, pilot [AIAA PAPER 71-5041 A71-29548 training and kinesthetic cues Advanced composite vs conventional material 871-29782 components in cost comparison for aircraft parts Atmospheric turbulence effects on handling A71-29656 qualities and structural loads on aircraft Air transport and travel expansion rate, 871-29787 discussing motivations and cost Handling qualities and control sensitivity of high 871-30159 performance helicopters. considering pitch and Circumstances inducing growth in different air collective control transport sectors, discussing transportation [ABS PREPRINT 542 ] A71-31099 cost. aviation capital requirement and business Handling qualities of V/STOL research vehicles and leisure air travel during steep terminal area approaches, A71-30160 discussing powered lift fan BTOL aircraft Aircraft quantitative maintenance cost limitations and instrument landing approach requirements translation into design criteria, [AHS PREPRINT 5443 A71-31101 considering airline operations influence on AH-568 compound helicopter rigid rotor stability manufacturer and handling qualities, using flight, whirl [SAE PAPER 7104371 A71-30529 tower and wind tunnel tests COST EFFECTIVEBESS [AHS PREPRINT 5741 A71-31115 cost efficient sound limit expenditures per Stability and controllability of supersonic swept parameter unit in commercial transport aircraft wing aircraft design [ AD-71 9803 ] N71-25049 871-28945 COliVECTIlTE BEAT TRLBSFEII Helicopters as cranes and external load carriers, Flow direction effect on combined forced and free considering operational costs and investment convective heat transfer from cylinders to air return A71-28985 A71-29144 COXIBEIOBS Operations research minimum cost model of aircraft Frankfurt terminal baggage conveyor system. noise abatement in airport communities describing passenger capacity and luggage [AIAA PAPER 71-5251 A71-29551 handling equipment Criteria for converting aeronautical project A71-29312 operational targets into actual requirements and COOLING SPSTEBS technical specifications, emphasizing cost Analysis of first stage turbine stator vane and effectiveness rotor blade cooling designs for application in A71-30824 highspeed aircraft COST REDUCTION [ NASA-TU-X-17821 N71-26355 Hoeing 747 aircraft integrated data system program CORIIELATION for reducing engine maintenance and operating Data correlation and effectiveness :-ediction from costs film cooling injection geometries, considering [AIAA PAPER 71-6483 A71-30725 finitely thick slot lip and boundary layers Potential feasibility of safe, practical, and A71-28751 economical air breathing nuclear propulsion CORRELATION COEFFICIENTS system for aircraft and air cushion vehicles Hypersonic theoretical/experimental correlations [ NASA-TR-X-67837 1 N71-25524 of aerodynamic characteristics for space shuttle CRACK PROPAGATIOB design structural fatigue in aircraft design, discussing N71-26066 twin engine transport tests, crack propagation CORROSIOB PREVENTION rate, residual strength, etc Soviet book on aircraft materials science and 871-29434 treatment covering steel/cast iron processing, CRANES metallography, heat/thermochemical conditioning, Helicopter design for use as crane and for surface protection and corrosion prevention carrying external loads A71-29529 A71-28489 Development and characteristics of high strength, Helicopters as cranes and external load carriers. stress corrosion resistant aluminum alloys for Considering operational costs and investment aircraft structures return [ AD-720398 3 N71-25876 871-29144 CORROSION RESISTBBCE CREEP TESTS lechanical properties of compos>tes consisting of Tests to determine short-term creep of metals and A1 matrix reinforced by boron fibers, alloys under conditions of aerodynamic heating considering high temperature creep, corrosion with high velocity air flow and thermal shock resistivity [ NASA-TT-P-13633] B7 1-25822 A7 1- 30473 CRITICAL LOADIBG CORROSION TESTS C-5A airplane Be brakes, considering critical Artificial corrosion pits effect on fatigue design weight environment for optimum load durability of smooth samples and aircraft carrying capacity duraluminum skin elements [SAE PAPER 7104271 A71-28313 A71-27819 CROSS PLOW aetal coated superalloys evaluation for gas Wing-jet interference effects in cross wind on turbine engine components, including corrosion, thrust and aerodynamic characteristics at large impact and fatigue tests distance from and near ground 871-29635 A71-29207 Fincap communication antennas design and Flowfield production by fluid injection into environmental tests for vibration, acceleration, supersonic crossflow, occurring with liquid/gas waterproofing. salt corrosion, ice formation and jet control of vehicle with combustion ramjets compass safe distance [AIAA PAPER 71-7281 A71-30775 A71-31047 Wind tunnel investigation of jet exhausting into COST ANBLYSIS cross flow - data for three jet configuration Airline operator evaluation of maintainability, [ AD-7181231 N71-24491 considering costs and investment return Wind tunnel investigation of jets exhausting into ~SAEPAPER 7104321 A71-28317 cross flow - description and data analysis Costs-reliability relationships in helicopter [ AD-7181221 N71-24492 development testing and demonstration,
A-18 SUBJECT INDEX DELTR DINGS
CURVED PANELS [ ASME PAPER 71-FE-91 A71-29450 Locating neutral layer and critical curvature Circumferential traversing probe technique for radius in aircraft components waffle panels intrastage analysis of,axial flow compressors, under elastoplastic bending considering mass flolr averaging data reduction A71-28940 technique Structural and inertial nonlinearities influence [ASME PAPER 71-FE-331 A71-29468 on flat or curved panel flutter Aircraft i6strumentation and data analysis for A71-30825 clear air turbulence, including orthogonal CYCLIC LOADS components and temperature and wind Evaluation of helicopter flight loading and distributions structural stability A71-29753 N71-24389 Hind tunnel investigation of jets exhausting into CYLIBDRICAL ANTENNAS cross flow - description and data analysis Aerospace antenna design, calculating one- [AD-7181221 N71-24492 wavelenqtb circular slot aperture radiation from DATA SYSTEBS circular cylindrical surface Integrated flight test data system combining A71-31075 digital airborne data acguisition/recording CYLINDRICAL BODIES system with telemetry/microwave link to Flona direction effect on combined forced and free computerized ground station convective heat transfer from cylinders to air A71-30318 A71-28985 Airborne integrated data system capabilities based Aerodynamic characteristics of low-aspect-ratio on flight tests with commercial aircraft winq mounted on cylindrical body, simulating by 871-30319 system of horseshoe vortices Boeing 747 aircraft integrated data system program 871-30264 for reducing engine maintenance and operatinq costs [AIAA PAPER 71-6481 A71-30725 DATA TRANSBISSION DASSAULT AIRCRAFT Sensing and communications technologies for short Dassault Mercure short range twin jet aircraft wayside headways, considering applicable capable of using powerful engine equipment for personal rapid transit systems, A71-29276 modulation, coding and data transmission DATA ACQUISITION techniques Self contained lightweight airborne data A71-30337 acquisition system for atmospheric and DC ‘10 AIRCRAFT meteorological research. using analoq recorder DC 10 specifications for airport planning, and telemetry system including ground clearances, payload-range A71-30311 characteristics and jet engine exhaust Fluctnating pressure measurements in jet engine velocities testing, using mioiature transducers with A71-30239 calibration and data acquisition equipment DC 10 flight crew individualized ground training 871-30325 program, emphasizing hands-on equipment and Automated modal data acquisition and processing instruction hardware system /MODAPS/ for real-time modal vibration [SAE PAPER 7104721 871-30538 testing of complex aerospace vehicle strr+tures. DECISION BAKING describing features, capabilities and Costs-reliability relationships in helicopter utilization development testing and demonstration, A71-30341 emphasizing decision making in program Performance and cost design tradeoff between HF management and synchronous meteorological satellite data [SAE PAPER 7104521 A71-28330 collection systems, considering platform Aviation within total transport system. discussing transmitting power and SNR decision making and management planning A71-30900 A71-30165 DBTB LINKS DEFROSTING L band aircraft antenna array consisting of Test procedures for aircraft defogger/defroster circnlarly polarized elements and static equipment electronic steering circuits for synchronous [ AD-7191091 871-24452 satellites radio links DEICIEIG A71-31074 Calculating and testing antiicing systems of DATA PROCXSSING aircraft and helicopters Normal accelerations experienced by transport [ AD-71 9922 ] N71-25622 aircraft fleet from fatigue load meter data DELTI HIIiGS analysis, discussing counting rates seasonal Air flow about low aspect ratio delta wing at sariations large angles of attack, deriving lift A71-29788 coefficient Automated modal data acquisition and processing A71-28282 system /PIODAPS/ for real-time modal vibration Hypersonic flow around delta wing at small angles testing of complex aerospace vehicle structures, of attack, using pressure sources method and describing featnres, capabilities and, Fredholm integral equation utilization 871-29189 871-30341 Hypersonic flow pattern past windward side of French ATC, discussing automatic coordinator delta wing with supersonic leading edges, systems, computer utilization and flight plan joining potential and vortex regions behind data processing shock wave 871-30382 A71-30874 Maastricht Automatic Data Processing and Display Angle of incidence effect on delta wing ATC system with digital computers for aiding leading-edge vortices with cross flow controllers in issuing instructions and making visualization in hydraulic test tunnel decisions [ ARC-R/M-36451 871-24482 A71-30383 Flow measurement of Nonweiler delta wing in DATA PROCESSING EQUIPMENT hypersonic slip flow Development and characteristics of electronic [ DLR-FB-70-461 N71-24500 equipment for digital processing of stochastic Oscillatory pitching moment derivatives signals for military aircraft avionics systems measurement on delta sings in incompressible [ AD-7198223 N71-24954 flow DIPB REDUCTION [ ARC-R/N-3628-PT- 1-4 ] N71-24569 Heat transfer within resonant cavities at subsonic Measurements of oscillatory pitchinq moments on and supersonic flow, discussing wind tunnels, round leading edged delta wing in incompressible test procedures and data reduction flow noting vortex flow development
A-19 DEMAND (ECONOEICS) SUBJECT INDEX
N71-24570 DIODES Neasurement of oscillatory pitching moment Bicrostrip p-i-n diode controlled L band digital derivatives on sharp-edged delta wing at vortex phase shifter for aircraft-satellite breakdown angle of attack communication 871 - 24 572 A71-31055 Buffet response of straight wing and delta wing DIRECTIONAL CONTROL model of space shuttle launch configuration Flight evaluations using variable stability N71-24662 aircraft to determine effects of turbulence Aerodynamic characteristics of delta wing space induced aerodynamic distnrbances and lateral shuttle configurations directional dynamics on pilot performance 871-26062 [NASA-CR-17181 N71-26170 DEMAND (ECONONICS) DISPLAP DEVICES Long term prospects of air traffic development in V/STOL aircraft instruments, deck display and competition with other modes, estimating VTOL automatic flight controls for takeoff and service demand landing operation A71-30164 A7 1-291 32 DEUSITY MEASUREHENT ATC radar display systems mapping techniques using Temperature and radical concentration measurements vectors and optical projections for high temperature flowing gas streams in rig 871-30014 simulating conditions in ramjet combustion Coucorde SST flight test equipment installation chamber and nozzle with PCH recording and visual instruments A71 -2 8758 A71-30055 DEPOSITION Naastricht Automatic Data Processing and Display Carbon deposition rates in gas turbine engine ATC system with digital computers for aiding combustion chambers with airstream-mechanical controllers in issuing instructions and making propellant atomization decisions A71-28970 A71-30383 DERIVATION Area navigation system based on radio aids by Least squares method and iteration technique for airborne receivers and sensors for aircraft obtaining aerodynamic stability derivatives movement improvement, noting advantages of pilot N71-24703 displays DESCENT [SAE PAPER 7104571 871-30533 En route aircraft flap control during descent and DO-31 AIRCRAFT holding Commercial V/STOL and jet VTOL transport, [ AR B-TN-99 ] N71-24920 discussing Do-31 test results, landing approach, DETECTORS air traffic control automation and electronic Precipitation detector and mechanism for stopping control and restarting machinery at initiation and A71-29131 cessation of rain DOPPLER NAVIGATION [ NASA-CASE-XLA-26191 N71-26334 Air naviga:ion techniques history, considering DE 121 AIRCRAFT radio, radar, loran Doppler and inertial Trident aircraft autopilot for automatic landings navigation in blind conditions, discussing operational A71-30712 problems DOPPLER RADAR A71-29261 Airborne Doppler radar receiver transmitter DIAPHRAGIS (MECHANICS) failure testing by Versatile Avionics Shop Test Altimeter-airspeed and nach number pressure computer controlled system transducer with diaphraqm free of temperature A71-28778 and vibration effects DOBNIER IIIRCRAFT A71-30322 Rotary wing structural stability of Dornier high DIFFUSION THEORY temperature gas jet helicopter Diffusion and thermal mechanism ignition theories, 871-24387 applying to altitude relighting of gas turbine DOENEASE engine combustors Numerical evaluation of dowuwash integral for wing B71-28745 loading of lifting rectangular planform DIGITAL COMPUTERS [ NPL-HA-901 871-24483 nultistage axial flow compressors on digital DRAG computer, testing gas dynamic design in final Unsteady hypersonic self similar gas flow and drag adjustment phase on circular cone accelerated according to power A71-28584 law. nsing small perturbation theory wind tunnel model trajectory simulation system A71-29205 with closed loop control by digital computer, Supercavitating flow past straight cascade with describing instrumentation, system arbitrary blade shapes, considering lift and servoamplifiers and testing procedures drag coefficients, cavitation number, cavity A71-30334 shape and exit flow conditions Naastricht Automatic Data Processing and Display [ ASBE PAPER 71-FE-61 ~71-29ua ATC system with digital computers for aiding Pressure distribution and drag prediction over controllers in issuing instructions and making slender axisymnetric fuselages and afterbodies decisions and exhaust nozzles at transonic nacb numbers 1171-30383 [AIAA PAPER 71-7201 A71-30771 Inertial navigation systems improvements for DRAG MEASUREMEUT commercial air transportation, noting digital Ballistic vind tunnel for drag measurement on computer program revision and increased models during free flight at supersonic speeds functional capability A71-29201 [SAE PAPER 7104583 A71-30534 DRAG REDUCTIOU AN/ASB-86 inertial navigation system consisting of Minimizing drag and increasing perrormance of inertial platform, digital computer and control optimum shapes at hypersonic flight indicator N 7 1- 2 4 7 0 4 [ABS PREPRINT 5331 A71-31094 DRILLING DIGITAL SYSTEMS Automated orifice drilling optimal treatment Integrated flight test data system combining routines, inclading proper timing and adequate digital airborne data acqnisition/recording total depth allowance system with telemetry/microuave link to 871-28941 computerized ground station DROP SIZE 871-30318 Optical measurement of sprays mean droplet size, Nicrostrip p-i-u diode controlled L band digital assessing operating variables effect on phase shifter for aircraft-satellite air-blast atomizer characteristics communication A71-28756 A71-31055
A-20 SUBJECT INDEX ELEVATORS (CONTROL SURFACES)
DUCTED PANS Ejection system performance in relation to Acoustic linings for attenuation of fan generated aircraft performance dependent extreme flight uoise in turbofan engines, considering conditions, examining ejection seat design interaction between analytical lining features and trajectories performance prediction and flow duct testing A71-29385 [AIAA PAPER 71-7313 A71-30778 E JECTORS DUCTED PLOW Eigh entrainment constant area multiple nozzle Friction factor for low Reynolds number turbulent ejectors with two mixing tube lengths for flow in large aspect ratio rectangular ducts, boundary layer control, estimating performance comparing Blasius and Prandtl relations with analytical model CASUE PAPER 71-PE-A] A71-29378 [ASME PAPER 71-FE-341 A71-29469 Acoustic linings for attenuation of fan generated ELECTRIC EQUIPUEHT noise in turbofan engines, considering Soviet handbook of aircraft electrical equipment interaction between analytical lining covering DC and turbine powered generators. performance prediction and flow duct testing lubrication materials, electromagnetic [AIAA PAPER 71-7313 A71-30778 interference countermeasures, etc DYNAMIC CEARACTEEISTICS A71-29530 Nonlinear mathematical model for dynamical ELECTRIC GENERATORS behavior of extensible towing cable subjected to STOL aircraft electric power variable frequency aerodynamic forces generated by uniform flow generation and high voltage DC distribution with field, discussing system stability secondary square wave AC distribution A71-31026 [SAE PAPER 7104441 A71-28325 DY NAMIC EODELS Soviet book on airplane and helicopter electrical Analytical model of compressor sensitivity to power supply systems covering storage batteries. transient and distorted transient flows, DC generators, alternators, voltage regulators, considering inlet duct, compressor stages and current and frequency control, etc combustor up to turbine nozzles A71-29525 [AIAA PAPER 71-6701 A71-30734 ELECTRIC POWER DYNAMIC RESPONSE STOL aircraft electric power variable frequency Aircraft with T tail configuration, examining generation and high voltage DC distribution with dynamic response to lateral gusts secondary square wave AC distribution A71-29786 [ SAE PAPER 7104441 871-28325 Alleviation of lateral and longitudinal gust ELECTRIC POWER l!RANS?IISSION effects on aircraft Soviet book on airplane and helicopter electrical N71-24709 power supply systems covering storage batteries, Pressure sensor network for measuring liquid DC generators, alternators, voltage regulators, dynamic response in fliqht including fuel tank current and freguency control, etc acceleration, liquid slosh amplitude, and fuel A71-29525 depth monitoring ELECTRIC RELAYS [NASA-CASE-XLA-O5541] N71-26387 Plug-in relay hazards and minimization for DYNAUIC STABILITY aircraft flight safety applications Propulsion, guidance and stability of ground A71-28841 effect vehicle with perimetric Coanda fluid ELECTRICAL PROPERTIES boundary Electrical and physical nature of microbial A7 ‘-29308 membranes implicated in aircraft fuel quantity High rotor advance ratio from multiblade general probe malfunction coordinates method in linear analysis of lifting [SAE PAPER 7104393 A71-28321 rotor dynamic stability and gust ratio ELECTROMAGNETIC ABSORPTION CARS PREPRINT 5121 871-31083 Tropospheric and ionospheric absorption at VHF for DYNAMIC TESTS North Atlantic aeronautical satellite system Dynamic testing - Conference, London, January 1971 [ NASA-TM-X-65507 1 N71-24914 A71-30053 ELECTROMAGNETIC INTERFERENCE Conference on fatigue life in helicopter Soviet handbook of aircraft electrical equipment components covering DC and turbine powered generators, [ DLB-MITT-70-011 N11-24385 lubrication materials, electromagnetic Dynamic tests of helicopter components interference countermeasures, etc N71-24388 871-29530 Structural stability tests of helicopter ELECTROMAGNETIC RADIATIOU components Hot jet aerodynamic parameters from emissions of N71-24390 electromagnetic and acoustic energies by crossed beam IR probing A71-30520 E ELECTRONIC COBTROL EARTH ATMOSPEERE Uultiple planar Luneberg lens circular array for Description of method for determining visibility airborne electronically scanned X band narrow in earth atmosphere beam antenna mounted under aircraft nose or [ AD-719502 1 N71-24375 fuselage EARTE SURFACE 871-31038 Jet aircraft sound spectrum on ground and in air, Eigh speed electronic phase and frequency scanned comparing calculation with experiment linear, static fed and mouopulse arrays element A71-30524 and angular error analysis ECONOMIC ANALYSIS A71-31049 Airport terminal building design and construction, ELECTBOUIC EQUIPMENT noting economy and expansibility coreguirements Interference prediction model for evaluating [SAE PAPER 7104181 A71-28307 expected interactions between avionics eguipmept Economic analysis of subsonic transport airplane on aircraft design, evaluation and operation [ AD-7 189 97 1 N71-24357 [SAE PAPER 7104231 871-2831 0 ELECTRONIC EQUIPMENT TESTS EcononIcs Airborne Doppler radar receiver transmitter Aircraft jet engines technological progress review failure testing by Versatile Avionics Shop Test over past 25 years, emphasizing industry computer controlled system economics considerations A71-28778 A71-30303 ELECTRONIC MODULES EJECTION SEATS Low carrier power aircraft antenna module for Tractor rocket actuated Yankee escape system, airborne UHF communications system, Considering discussing advantages of pulling action over range/field strength measurements conventional pushed ejection seat under low A71-31046 kpeed low altitude conditions ELEVATORS (CONTROL SURFACES) A71-29383 sailplane elevator induced maneuvering and
A-2 1 ELEBOBS SUBJECT INDEX
horizontal tail surface loads, discussing [ NASA-TEI-X- 17821 N71-26355 airworthiness requirements ENGIUE IBLETS A71-29256 Aircraft propulsion system testing, stressing ELEBOBTS noise reduction and inlet-engine exhaust system Elevons as longitudinal and lateral control compatibility elements on low aspect ratio wings, calculating [ SAE PAPZR 7104501 871-28328 subsonic and supersonic aerodynamic EP rake probes with high temperature integrated characteristics sensor for inflight aircraft engine intake air 871-29190 flow distortion measurements ELLIPTICITY A71-30321 Elliptical cones at large angle of attack, Engine surge pressure transients in mixed- calculating three-component real gas properties compression supersonic inlet, describing scale effects on aerodynamic characteristics wind tunnel model simulation and measurement 871-29191 techniques ElISSIOR SPECTRA [AIAA PAPER 71-6711 A71-30735 Complex noise emission spectra from superposition BBGIBE HOBIlORIHG IBS2IiU14BNTS of continuous component and peaks, calculating Gas turbine auxiliary power unit accessories, level separations due to perfectly reflecting discussing high energy igniters, cables and plane connectors, thermocouples and speed and 871-30523 temperature monitoring equipment EBERGY DISSIPATIOH A71-29262 Air bypass behind compressor into variable area Design interface requirements for optimal aircraft exhaust nozzle, obtaining energy losses from gas engine condition monitoring system, using turbine jet engine indices parameter, vibration. oil, borescope and 871-28586 radiography analysis EBERGY DISTRIBUTIOB [SAE PAPER 7104471 A71-30531 Energy state approximation and supersonic aircraft Boeing 747 aircraft integrated data system program minimum fuel fixed range trajectory for reducing engine maintenance and operating optimization, noting not convex velocity set costs A71-30609 [AIAA PAPER 71-6481 871-30725 ENERGY SOLIRCBS Engine condition monitoring systems, discussing Bot jet aerodynamic parameters from emissions of engineering design reguirements uith respect to electromagnetic and acoustic energies by crossed accessibility, accuracy, economics, beam IR probing effectiveness, reliability and maintainability A71-30520 [AIAA PAPER 71-6523 A71-30728 EHGIBTE DESIGN ENGINE BOISE VTOL propulsion, discussing gas turbine pressure Absorbent materials for sound attenuation in ratio inlet temperature and lifting and high turboreactor ducts. examining flow velocity, bypass fans absorbent structure and cladding effects A71-27838 A71-30518 Olympus 593 pure jet twin shaft engine development EUGIBE PilRTS program for Concorde. discussing engine Vacuum heat treatment of brazed and diffusion evolution, design considerations and flight bonded jet engine components near melting development tem perature [SAE PAPER 7104221 A71-28309 A71-28 145 High temperature aircraft gas turbine engine Silicide coated Nb alloys for gas turbine engine design, discussing developments in manufacturing components operating at temperatures above 2000 processes. materials, cooling techniques, F aerodynamic and mechanical design ieprovements [SAE PAPER 7104601 A71-28334 [SAE PAPER 7104621 A71-28335 netal coated superalloys evaluation for gas STOL aircraft/engine integrated systems for medium turbine engine components, including corrosion, distance air transportation, discussing tradeoff impact and fatigue tests factors involving performance, noise, weight and A71-29635 cost EUGIBE STARTERS [SAE PAPER 7104691 871-28337 Gas turbine engine startup igniter uith modified Subsonic and supersonic turbojet aircraft engines propellant atomizer enhanced by air injection development, discussing design, operation, A71-28969 reliability, weight, fuel consumption and cost notor starting techniques for 2-15 kH Brayton A71-29811 space power system Aircraft jet engines technological progress review [ NASA-TU-X-678 19 1 N71-24691 over past 25 years, emphasizing industry EBGIHE TESTS economics considerations Supersonic inlet turbojet engine compatibility A71-30303 tests in wind tunnels, using light panels and Transport aircraft JT9D high bypass ratio engine Summation Device analysis development. noting maintainability and 871-28032 stability improvements CF6 turbofan engine development. discussing [SAE PAPER 7104191 A71-30527 performance and endurance tests and design Aircraft JT9D engine development for airline changes for reliable low cost operation operation, discussing construction, condition [SAE PAPER 7104211 A71-28308 monitoring, maintenance, noise and smoke Commercial aircraft powerplant development, reduction discussing engine and components test programs rSAE PAPER 7104341 A71-30528 and techniques Design interface requirements for optimal aircraft [SAE PAPER 7104491 871-28327 engine condition monitoring system, using Aircraft propulsion system testing, stressing parameter, vibration, oil, borescope and noise reduction and inlet-engine exhaust systea radiography analysis compatibility [SAE PAPER 7104471 A71-30531 [SAE PAPER 7104501 A71-28328 Space shuttle airbreathing propulsion systems Airline engine performance testing from operator requirements and design studies, considering perspective, using automated test cell data cruise, landing, go-around and ferry acquisition system capabilities [SAE PAPER 7104511 871-28329 [AIAA PAPER 71-6621 A 71-30731 Uiniature transducers design and fabrication for Fundamentals of aircraft gas turbine engines fluctuating pressure measurements in jet engine C AD-71 991 3 1 N7 1-25808 testing, noting frequency response and power Eircraft gas turbine combustion chamber design dissipation [ NAL-TR-208 1 N71-26298 A71-30324 Analysis of first stage turbine stator vane and Fluctuating pressure measurements in jet engine rotor blade cooling designs for application in testing, using miniature transducers uith highspeed aircraft calibration and data acquisition equipment
A-22 SUBJECT IBDEX FATIGUE (KATEBIALS)
A71-30325 Optimal penetration effect on peripheral gas flow Low cost go/no-go portable aircraft engine tester temperature field at outlet of turbine connected to engine mounted sensors combustion chamber- with circular flame tubes A71-30327 A71-28971 Gas turbine engine condition analysis by digital iiigh entrainment constant area multiple nozzle computer and fault isolation techniques ejectors with two mixing tube lengths for [SAE PAPER 7104481 A71-30532 boundary layer control. estimating performance Wind tunnel force test program design for jet with analytical model aircraft configurations, including propulsion [ASME PAPER 71-FE-341 A71-29469 system simulation Airframe installation effects on underwing nacelle A71-30605 nozzle performance, using calibrated engines and ENVIROBlEETAL COBTROL load cells on F-106 for measurements Performance of aircraft environmental control [AIAA PAPER 71-6811 A71-30745 systems under simulated tactical conditions Isolated axisymmetric jet engine exhaust nozzles [ AD-719101 ] N71-24461 thrust and drag predictions in sub-, trans- and ENVIBONMENTAL TESTS supersonic flight regimes Pincap communication antennas design and [AIAA PAPER 71-7191 A71-30770 environmental tests for vibration, acceleration, Pressure distribution and drag prediction over waterproofing, salt corrosion. ice formation and slender axisymmetric fuselages and afterbodies compass safe distance and exhaust nozzles at transonic Mach numbers 871-31047 [AIAA PAPER 71-7203 871-30771 Test procedures for aircraft defogger/defroster EXHAUST SYSTEKS equipment Aircraft propulsion system testing, stressing [ AD-719109 ] N71-24452 noise reduction and inlet-engine exhaust system EQUILIBBIUE METHODS compatibility Nonlinear panel flutter analyses by perturbation [SAE PAPER 7104501 871-28328 and harmonic balance methods EXPERIMENTAL DESIGE [NASA-CR-111907] N71-25362 Wind tunnel force test program design for jet EQUIPHENT SPECIFICATIOES aircraft configurations, including propulsion Development and characteristics of scanning system simulation systems for thermal viewers and infrared A71-30605 detectors for airborne operation EXTREHUM VALUES [ AD-719854 ] N71-25053 Cumulative frequency distributions determined by ERROR ANALYSIS extreme value analysis used for fa'tique analysis Measurement errors in testing single stage air and interpretation of c.4. vertical acceleration driven axial flow compressors and turbines and gust velocity measured on transport aircraft A71-28582 [ AGARD-R-579-711 N71-25080 iiigh speed electronic phase and frequency scanned linear, static fed and mouopnlse arrays element and anqular error analysis 871-31049 F-104 AIRCRAFT ESCAPE ROCKETS Minimum time profiles for P-104 aircraft by Tractor rocket actuated Yankee escape system, Balakrishnan epsilon technique, comparing discussing advantages of pulling action over solutions with energy method conventional pnshed ejection seat under ?-u A71-28831 speed low altitude conditions FABRICATIOB A71-29383 materials and processing methods for rain erosion ESCAPE SYSTEKS resistant ceramic coated plastic structures for Tractor rocket actuated Yankee escape system, supersonic aircraft, considering fiberglass discussing advantages of pulling action over reinforced polyimide radomes with alumina conventional pushed ejection seat under lou coating speed lou altitude conditions 871-29645 A71-29383 Miniature transducers design and fabrication for Ejection system performance in relation to fluctuating pressure measurements in jet engine aircraft performance dependent extreme flight testing. noting frequency response and power conditions, examining ejection seat design dissipation features and trajectories A71-30324 A71-29385 FAIL-SAFE SYSTEMS ESBO SATELLITES Fail-safe helicopter rotor control design, Scientific results from ESRO satellites and from discussing damage tolerant components, redundant sounding rocket campaign including aeronautical system, failure warning and maintenance fields, management planning. satellite [AES PREPRINT 5501 A71-31102 development, and telecommunication - 1969 report Integral spar inspection system for making cii-46 N71-24447 rotor blade fail-safe EVALUATION [ABS PREPRINT 5511 A71-31103 Procedures for evaluating compatibility of FAILUBX AEALYSIS aviation materiel with related equipment Airborne Doppler radar receiver transmitter [ AD-71 9107 ] N71-24457 failure testing by Versatile Avionics Shop Test EVASIVE ACTIOBS computer controlled system Performance of aixcraft environmental c.ontro1 A71-28778 systems under simulated tactical conditions Structnre service life and storage failure [ AD-7191011 N71-2446 1 probability calculation with current load EXEAUST GASES measurements and laboratory fatigue testing Visible exhaust smoke trails from aircraft jet A71-29231 engines, measuring optical density by Gas turbine engine condition analysis by digita,l photographic photometry computer and fault isolation techniques [ SAE PAPER 7104281 871-283 14 [SAE PAPER 7104483 A71-30532 Chemical kinetic calculation of nitric oxide FAILURE BODES formation in spark ignition automobile engines Belicopter power transmission failure modes, and gas turbine combustors presenting field experiences correlation with 871-30454 conventional design stress analysis and bench Wind tunnel investigation of jets exhausting into test data cross flow - description and data analysis [SAE PAPER 7104541 A71-28331 [AD-7 18122 ] N71-24492 FATIGUE (KATERIALS) EXHAUST NOZZLES Cumulative frequency distributions determined by Air bypass behind compressor into variable area extreme value analysis used for fatique analysis exhaust nozzle, obtaining energy losses fron gas and interpretation of c.g. vertical acceleration turbine jet engine indices and gust velocity measured on transport aircraft 871-28586 [ AGARD-R-579-713 N71-25080
A-23 FATIGUE LIFE SUBJECT IUDEX
Fatigue and fracture mechanics of airframes and FLAPS (COUTROL SURFACES) materials including structural design and stress Direct lift control system having flaps with slots analysis techniques adjacent to their leading edge and particularly [AD-7197563 N71-25092 adapted for lightweight aircraft FATIGUE LIFE [ NASA-CASE-LAR-10249-1] N71-26110 Artificial corrosion pits effect on fatigue FLIT PLATES durability of smooth samples and aircraft Asymptotic limiting viscous flow pattern and drag duraluminum skin elements on flat plate with stationary separation zones A71-27819 at large Reynolds numbers Aircraft design and fatigue life monitoring, A71-29204 investigating effects of gust velocity frequency Skin friction drag and velocity profile distribution in patches of atmospheric measurements on flat plate in two phase circular turbulence pipe flow in subsonic wind tunnel for gas-solid A71-29789 media, using photographic technique Conference on fatigue life in helicopter [ASME PAPER 71-PE-321 A71-29467 components Turbulent skin friction and heat transfer [ DLR-MITT-70-0 1 3 N71-24385 prediction on flat plates and wind tunnel walls Fatigue life of helicopter rotary wings under at snpersonic and hypersonic Mach numbers, using vibrational stresses Van Driest theory N71-24386 A71-29868 FATIGUE TESTS Low speed wind tunnel test of four ft diameter Structure service life and storage failure circular plate model to determine surface static probability calculation with current load pressure distributions for jet decay measurements and laboratory fatigue testing characteristics of cross flow 871-29231 [AD-7202321 171-26516 Structural fatigue in aircraft design, discussing Low speed wind tunnel test of four ft diameter twin engine transport tests, crack propagation circular plate model with three exhansting jets rate, residual strength, etc [ AD-7202331 171-26517 871-29434 FLEXIBILITY Metal coated superalloys evaluation for gas Helicopter rotor stall characteristics, turbine enqine components, including corrosion, investigating blade flexibility, unsteady impact and fatigue tests aerodynamics and variable inflow effects 871-29635 [AHS PREPRINT 5201 A71-31086 Pisa university Aeronautical Institute activities FLEXIBLE BODIES /1960-1970/, considering supersonic and subsonic Random process theory method for estimating flow research, thin stiffened shells fatigue response of flexible airplanes to atmospheric under compressive or tensile loads. etc turbulence A71-30822 N71-24708 FEEDBACK CONTROL FLIGET Wind tunnel model trajectory simulation system Flow meter for measuring stagnation pressure in with closed loop control by digital computer, boundary layer around high speed flight vehicle describing instrumentation, system [ NASA-CASE-XFR-02007] N71-24692 servoamplifiers and testing procedures FLIGHT ALTITUDE A71-30334 Jet transport aircraft design for safety under air VTOL aircraft minimum climb-to-cruise tsse turbulence conditions, considering cruise transition optimal open loop and suboptimal altitude limitations and pitch and g excursion closed loop control synthesis reduction by special autopilot mode A71-30799 A71-29777 PILE COOLING FLIGET CHARACTERISTICS Annular vaporizing combustion chamber with film Aircraft flight characteristics dependence on cooling, determining flame temperature under angle of attack, roll and pitch supersonic flight conditions A71-29043 A71-28749 Flight characteristics under atmospheric Data correlation and effectiveness prediction from turbulence conditions, analyzing analog trace film cooling injection geometries, considering records of airspeed, normal acceleration, finitely thick slot lip and boundary layers altitude, air temperature, control surface and A71-28751 flight attitude parameters PIUITE DIFFEREUCE THEORY A71-29771 Finite difference method for calculating inviscid Forward flight performance of coaxial rigid rotor flow field around supersonic/hypersonic space in NASA wind tunnel, comparing to aerodynamic shuttle stability with conventional rotors N71-26056 [AHS PREPRINT 5241 A71-31090 FIRE COUTROL PLIGHT COUDITIOUS Cheyenne attack helicopter weapons system, Flight characteristics under atmospheric discussing night vision capability, armament, turbulence conditions, analyzing analog trace fire control and navigation equipment records of airspeed, normal acceleration, integration altitude, air temperature, control surface and [AAS PREPRINT 5301 A71-31091 flight attitude parameters Ueapons delivery computer for attack helicopters, 871-29771 using planar distributed function generator for PLIGHT COUTROL general closed form Instantaneous solution L-1011 aircraft flying stabilizer, aiscussing capability choice of longitudinal flight control systems [AHS PREPRINT 5311 A71-31092 [SAE PAPER 7104261 A71-28312 PIRE PREVEUTION VTOL aircraft minimum climb-to-cruise time , Concorde power plant fire protection system. transition optimal open loop and suboptimal describing prototype engine bay overheat closed loop control synthesis detection system and additional UV optical fire A71-30799 detection system Heavy lift helicopter flight control system A71-30300 design, emphasizing fly by wire electrical PxssIon PRODUCTS analog Studying aircraft accidents to determine impact [AHS PREPRINT 5031 A71-31079 angle and speed criteria for designing nuclear Jet vertical takeoff aircraft piloted cockpit airplane fission product containment vessel simulator for controlling aircraft flight [NASA-TM-X-2245] N71-25411 performance FLAEE TEEPERATURE [ARC-R/M-3647] N71-25065 Annular vaporizing combustion chamber with film FLIGHT CREWS cooling, determining flame temperature under DC 10 flight crew individualized ground training supersonic flight conditions program, emphasizing hands-on equipment and A71-28749 instruction hardware
A-24 SUBJECT IUDEX FLOW EQUATIONS
[SAE PAPER 7104721 A71-30538 STOL vehicle and systems air transportation PLIGHT HAZARDS expansion by reducing trip tine, congestion, Naterials and structural design development by noise exposures and pollution for DOT, DOD and high velocity impact testing due to transport NASA roles and subsonic military aircraft susceptibility to [SAE PAPER 7104641 A71-30535 bird collision damaoe PLIGHT TRAIBIBG A71-29642 Boeing 747 crew members training program, PLIGHr INSTRUHENTS describing ground training, classrooms, inertial Onboard area navisation svstems in ATC navigation system and cockpit trainers environment, discussing-route structure and [SAE PAPER 7104731 A71-28339 flight instrnments Commercial airlines flight training program, using [SAE PAPER 7104551 A71-28332 siaulation and improved techniques fo,r safety PLIGHT LOAD BBCOBDBRS and economy Aircraft flight load measurements in high [SAE PAPER 7104751 A71-28340 temperature environment. determining optimal DC 10 flight crew individualized ground training strain gage installation and calibration program, emphasizing hands-on equipment and A71-30681 instruction harduare FLIGHT PATHS [SAE PAPER 7104723 A71-30538 V/STOL aircraft flight path and attitude controls PLOW CHARACTERISTICS in turbulence, discussing design based on state Air flou past small aspect ratio thick-section variable methods of control theory wing at small angles of attack, investigating A71-29776 vortex system effect on flow characteristics in High intensity xeon flashtube lights for absence of lift increasing conspicuity of trainer helicopters A71-29234 during daytime and nighttime flights Relicopter rotor stall characteristics, [ AD-7186391 871-24669 investigating blade flexibility, unsteady PLIGHT PLANS aerodynamics and variable inflow effects French ATC, discnssing automatic coordinator [AHS PREPRINT 5201 871-31086 systems, computer utilization and flight plan Transonic wind tunnel investigation of flow data processing characteristics and pressure fluctuation of A71-30382 space shuttle launch and reentry configurations PLIGHT SIIULATION N71-24663 V/STOL aircraft gust effects prediction with PLOS DEFLECTION mathematical models based on nonlinear hybrid Two dimensional jet flap cascades, presenting simulation at takeoff and landing altitudes stream deflection angles as function of jet to A71-29775 mainstream momentum flux Computerized simulation techniques for [ASME PAPER 71-FE-141 A71-29453 investigating aircraft accidents due to PLOS DISTORTION atmospheric turbulence HF rake probes with high temperature integrated A71-29779 sensor for inflight aircraft engine intake air PLIGBT SINULATORS flow distortion measurements Visual flight simulation devices, considering high A71-30321 resolution photogrphic films and digital Time variant distortions in kupersonic inlet on memories J-85-GE-13 turbojet engine from wind tunnel A71-29483 test, considering instantaneous distortion PLIGBT STABILITY TESTS amplitudes and contours Evaluation of helicopter flight loading and [AIAA PAPER 71-6671 A71-30733 structural stability PLOW DISTRIBUTIOB N71-24389 Asymptotic limiting viscous flou pattern and drag Flight evaluations using variable stability on flat plate with stationary separation zones aircraft to determine effects of turbulence at large Reynolds numbers induced aerodynamic disturbances and lateral A71-29204 directional dynamics on pilot performance Stratospheric air flow patterns and CAT [ NASA-CR-17181 N71-26170 measurements onboard aircraft over and downwind PLIGHT TESTS of western U.S. mountain terrain Yak 40 aircraft flight test program, discussing A7 1-29755 airworthiness requirements, static structural, Flowfield production by fluid injection into vibration and wind tunnel tests supersonic crossflow, occurring with liguid/gas A71-29911 jet control of vehicle with combustion ramjets Concorde SST flight test equipment installation [AIAA PAPER 71-7283 871-30775 with PCM recording and visual instruments Hypersonic flow pattern past windward side of 871-30055 delta wing with supersonic leading edges, Integrated flight test data system combining joining potential and vortex regions behind digital airborne data acguisition/recording shock wave system with telemetry/microuave link to A71-30874 computerized ground station Nonlinear mathematical model for dynamical 871-30318 behavior of extensible towing cable subjected to Airborne integrated data system capabilities based aerodynamic forces generated by uniform flow on flight tests with commercial aircraft field, discussing system stability A71-30319 A71-31026 High performance UE-1 compound helicopter high Flow field velocity distribution at rotating wing speed flight research, considerinq rotor loads, devices tip vortices stability, control and flying qualities [AHS PREPRINT 5221 A71-31088 [AES PREPRINT 5701 A7 1- 31 11 1 Rind tunnel simulations of flow fields and Evaluation of fuel flowmeter instrnmentation aerothermodynamics of space shuttle orbiters conducted during flight tests 871-26053 [AD-7192803 N71-24479 Finite difference method for calculating inviscid Flight tests for controlling slope approach of flow field around supersonic/hypersonic space short takeoff aircraft shuttle [ ARC-CP-11381 N71-25050 171-26056 Comparison of pilot performance using center Flow visualization, thermocouple measurements, and stick, dual side stick, and single side stick analyses of shock interference heating effects configuration on straight wing space shuttle model [ AD-720846 3 N71-258 46 N71-26057 PLIGHT TINE PLOW EQUATIONS Binimum time profiles for F-104 aircraft by Axisymmetrical three component flow equations for Balakrishuau epsilon technique, comparing incompressible viscous fluid in cylinder with 'solutions with energy method rotating disk A71-28831 A71-30855
A-25 FLOB €IEASURE€IEBT SUBJECT INDEX
FLOB HEASUREXEBT A71 -3 1021 Eonograph on hypersonic shock tunnel supersonic FLY BY XIRE COBTROL combustion research techniques covering test Heavy lift helicopter flight control system facilities, optical and electromagnetic flow design. emphasizing fly by wire electrical measurement methods, etc analog 871-29578 [AHS PREPRINT 5031 871-31079 Supersonic mass flux probe description, discussing PLXIBG PIJiTPOBES inlet geometry, angle of attack and Reynolds and Geomagnetic components measurement from moving Kach numbers effects on performance platforms, discussing coordinate system 1171-29925 stabilization methods for errorless time Flow measurement of Nonweiler delta wing in averaging of measurements hypersonic slip flow A71-28249 [DLR-FB-70-461 N71-24500 FORCED COBVECTIOH FLOW THEORY Flow direction effect on combined forced and free Eonograph on potential flow interaction between convective heat transfer from cylinders to air blade rows in axial flow compressors covering A71-28985 mathematical model, numerical analysis and FRACTURE BECHABICS experiment Fatigue and fracture mechanics of airframes and A71-28883 materials including structural design and stress Unsteady curvilinear motion of lifting surface, analysis techniques calculating induced gas flow velocities in terms [ AD-7197561 N71-25092 of vortex densities FREDHOLK EQUATIOBS A71-29188 Hypersonic flow around delta wing at small angles Propeller vortex theory, calculating vortex of attack, using pressure sources method and streets pitch distributions and wake Fredholm integral equation configuration 811-29189 A71-30443 FREE BOUBDARIES FLOW VELOCITY Air inlet for simulation of shock wave separated Aerofoil cascades with axial velocity change in flow in supersonic diffusers, deriving pressure incompressible flow, determining turbine blade variation profile along free boundary force dependence on circulation 871-29175 A7 1-28467 FREE COBVECTIOB Unsteady curvilinear motion of lifting surface, Flow direction effect on combined forced and free calculating induced gas flow velocities in terms convective heat transfer from cylinders to air of vortex densities A7 1- 289 85 A71-29188 FREE FLIGHT Skin friction drag and velocity profile Ballistic wind tunnel for drag measurement on measurements on flat plate in tno phase circular models during free flight at supersonic speeds pipe flon in subsoric wind tunnel for gas-solid A71-29201 media, using photographic technique FREE KOLECULAR FLOW [ASEE PAPER 71-FE-321 A71-29467 Photoelectric, bolometric and photographic Plow field velocity distribution at rotating wing recording assembly for measurement of light devices tip vortices pressure and aerodynamic forces on complex shape [AHS PREPRINT 5221 871-31088 body in free molecular flow FLOB VISUALIZATIOB A71-29155 Turbulence level effects on mixing of three plane Aerodynamic characteristics similarity and parallel slipstreams with equal velocities and variation in hypersonic flow transition region temperature from smoke visualization from free molecular flow to solid medium A71-28962 A71-29172 Helicopter rotor vortex system and induced FREE RADICALS velocity field for various angles of attack. Temperature and radical concentration measurements flight conditions and unit loads, using smoke for high temperature flowing gas streams in rig visualization technique simulating conaitions in ramjet combustion A71-29235 chamber and nozzle Angle of incidence effect on delta wing A71-28758 leading-edge vortices with cross flow FREQUEBCY ASSIGHEEHT visualization in hydraulic test tunnel Survey of very high and ultrahigh frequency [ ARC-R/Ei-3645] N71-24482 utilization in US aeronautics for communication FLOWHETERS satellite frequency assignment Evaluation of fuel flonmeter instrumentation [ NASA-TH-X-65527 1 N71-25920 conducted during flight tests FREQUENCY DISTRIBUTIOB [AD-719280] N71-24479 Aircraft design and fatigue life monitoring, Flow meter for measuring stagnation pressure in investigating effects of gust velocity frequency boundary layer around high speed flight vehicle distribution in patches of atmospheric [ NASA-CASE-XFR-02007 ] N71-24692 turbulence FLUID BOUBDABIES 871-29789 Propulsion, guidance and stabili-ty of ground Cumulative frequency distributions determined by effect vehicle with perimetric Coanda fluid extreme value analysis used for fatique analysis boundary and interpretation of c.g. vertical acceleration A71-29308 and gust velocity measured on transport aircraft FLUID IBJECTION [ AGARD-R-579-711 N71-25080 Flowfield production by fluid injection into FREQUEBCY RESPONSE supersonic crossflow, occurring with liquid/gas Frequency response of five component strain, gage jet control of vehicle with combustion ramjets oscillating balance for dynamic wind tunnel [AIAA PAPER 77-7281 A71-30775 stability testing FLUIDICS 871-30333 Fluidic cabin pressure automatic control systems FREQUEHCY SCABBING for military and civil aircraft. discussing High speed electronic phase and frequency scanned design, operation and performance linear, static fed and monopulse arrays element A71-30308 and angular error analysis FLUTTER ANALYSIS A71-31049 Supersonic flutter analysis of clamped skew panels FRICTIOB DRAG with in-plane forces by Galerkin method. using Skin friction drag and velocity profile two dimensional static approximation for measurements on flat plate in two phase circular aerodynamic loading pipe flow in subsonic wind tunnel for gas-solid 871-30607 media, using photographic technique Mechanical support system role in determination of [ASEE PAPER 71-FE-321 A71-29467 aeroelastic stability of leeward cylinder FRICTIOB FACTOR immersed in wake using undamped flutter theory Friction factor for low Reynolds number turbulent
A-26 SUBJECT IBDEX GAS TURBIBB ENGIBES
flow in large aspect ratio rectangular ducts, GAS BEARINGS comparing Blasius and Praudtl relations Time dependent clearance changes effects on [ASHE PAPER 71-FE-A] A71-29378 aerodynamic characteristics of sectorially FUEL COXBUSTIOB grooved gas bearings, describing lift and drag Kerosene type fuels for aircraft gas turbine coefficients calculation engines, discussing combustion problems, smoke A71-30227 emission reduction and bacterial or fungal GAS COOLING contamination Hetal temperatures in rotating cooled gas turbine A71-28754 blades, discussing coolant flow aerodynamics FUEL CONSUBPTIOB 871-28748 Jet-supported VTOL aircraft fuel-time-optimal GAS DEBSITY landing control, using mathematical model, Hypersonic shock/density ratio effects in Pontryagin maximum principle and analog computer aerothermodynamic heating of space shuttle solution configuration A71-29281 N71-26058 Subsonic and supersonic turbojet aircraft engines GAS FLOW development, discussing design, operation, Beat shield ablation under high enthalpy reliability, weight, fuel consumption and cost chemically active turbulent gas flou in hydrojet A71-29811 engine manifolds FUEL CONTAXINATIOI A71-28589 Nicrobiological contamination of jet aircraft fuel Gas turbine engine cornbustion chamber outlet, tanks in tropical regions. considering noting gas flow temperature field peripheral maintenance nonuniformity [SAE PAPER 7104381 A71-28320 A71-28972 Kerosene type fuels for aircraft gas turbine Three dimensional steady separated liquid and gas engines, discussing combustion problems, smoke flow past low aspect ratio bodies, deriving emission reduction and bacterial or fungal similarity laws for reduction to two dimensional contamination problem A71-28754 A71-29169 FUEL CONTROL Heat transfer on spheres and sharp cones in Energy state approximation and supersonic aircraft rarefied hypersonic gas flow at zero angles of minimum fuel fixed range trajectory attack in wind tunnel vacuum optimization. noting not convex velocity set A71-29176 A71-30609 Unsteady curvilinear motion of lifting surface, Turbine engine fuel control stability on CH-47C calculating induced gas flow velocities in terms helicopter, using flight tests and lag damper of vortex densities simulation A71-29188 [AHS PREPRINT 5601 A71-31107 Unsteady hypersonic self similar gas flow and drag FUEL GAGES on circular cone accelerated according to power Electrical and physical nature of microbial law, using small perturbation theory membranes implicated in aircraft fuel quantity A71-29205 probe malfunction Soviet book on experimental aerodynamics covering [SAE PAPER 7104391 A71-28321 wind tunnels, shock tubes, liquid and gas FUEL INJECTIOB physical properties, flou parameter measurement Gas-air mixture requirements for turbine and equipment, etc injection burner combustion efficiencies A71-29524 [ AD-719834 ] N71-25359 Vortical transonic gas flow over uing profile FUEL SYSTEHS 171-257 14 Procedures for evaluating effectiveness of self GAS GEBEBATORS propelled and portable ground servicing units Afterburning turbofan engine thrust calculation by for Army aircraft gas generator method, using F-lllA for [ AD-719102 ] N71-24459 comparison tests Evaluation of fuel flowmeter instrumentation [AIAA PAPER 71-6801 871-30744 conducted during flight tests GAS IBJECTIOB [ AD-7192801 N71-24479 Gas turbine engine combustion chamber start-up and FUEL TANKS burning performance, considering air injection Hicrobioloqical contamination of jet aircraft fuel and propellant atomization tanks in tropical regions, considering 871-28968 maintenance Gas turbine engine startup igniter with modified [SAE PAPER 7104381 A71-28320 propellant atomizer enhanced by air injection Pressure sensor netuork for measuring liquid A71-28969 dynamic response in flight including fuel tank GAS PRESSURE acceleration, liquid slosh amplitude. and fuel Fluidic cabin pressure automatic control systems depth monitcring for military and civil aircraft, discussing [NASA-CASE-XLA-O5541] N71-26387 design. operation and performance FUEL TESTS 871-30308 Fuel tests to determine feasibility of gelled GAS STREAES methane for use in jet engine Temperature and radical concentration measurements [ NASA-CR-728761 N7 1-257 72 for high temperature flowing gas streams in rig FUEL-BIB RATIO simulating conditions in ramjet combustion Gas-air mixture requirements for turbine and chamber and nozzle injection burner combustion efficiencies A71-28758 [ AD-719834 3 N71-25359 GAS 'PEkiPERATURE FUSELAGES Gas temperature measurement in aircraft combustion Fuselage influence on total aircraft drag in chambers. usina calorimetric DrObe subsonic passenger aircraft, considering high A71-28757 aspect radio cylindrical fuselages GAS TURBINE EBGINES A71-30821 VTOL propulsion, discussinq qas turbine pressure ratio inlet temperature ana lifting anh high bypass fans A71-27838 GABE PEEORY Commercial aircraft powerplant development, German monograph on game theory and planning discussing engine and components test programs techniques for aircraft evaluation and techniques A71-28880 [SAE PAPER 7104491 A71-28327 GAEHii RAYS Silicide coated Nb alloys for gas turbine engine Nondestructive testing of aircraft structures components operating at temperatures above 2000 using thulium and iridium gamma sources F [JAERI-MEHO-4163] N71-24849 [SAE PAPER 7104603 A71-28334
A-27 GAS TURBINES SUBJECT INDEX
High temperature aircraft gas turbine engine Combustion and heat transfer in gas turbine design. discussing developments in manufacturing systems - Conference. Cranfield. England, April processes, materials. cooling techniques. 1969 aerodynamic and mechanical design improvements A71-28739 [SAE PAPER 7104621 A71-28335 Beta1 temperatures in rotating cooled gas turbine Air bypass behind compressor into variable area blades, discussing coolant flow aerodynamics exhaust nozzle, obtaining energy losses from gas A71-28748 turbine jet engine indices GEARS A71-28586 Reduction gearbox reliability problems from Diffuslon and thermal mechanism ignition theories, development and service experience with PT6A applying to altitude relighting of gas turbine tnrboprop engine engine combustors [SAE PAPER 7104331 A71-28318 A71-28745 GELLED PROPELLABTS Kerosene type fuels for aircraft gas turbine Fnel tests to determine feasibility of gelled engines, discussing combustion problems, smok= methane for use in jet engine emission reduction and bacterial or fungal [ NASA-CR-72876 ] 871-25772 contamination GEOCEBTRIC COORDINATES ~71-2a754 Control, navigation ana guidance review, Soviet papers on combustion processes in turbulent considering application of earth reference and laminar flows of kerosene and gasoline coordinates for aircraft, missiles and mixtures, stressing gas turbine engines problems spacecraft A71-28954 A71-30710 Gas turbine engine combustion chamber start-up and GEOEAGNETISE burning performance, considering air injection Geomagnetic components measurement from moving and propellant atomization platforms, discussing coordinate system A71-28968 stabilization methods for errorless time Gas turbine engine startup igniter with modified averaging of measurements propellant atomizer enhanced by air injection A71-28249 A71-28969 GLIDE PATES Carbon deposition rates in gas turbine engine Quasi-stationary gliding trajectories of aircraft combustion chambers with airstream-mechanical in planetary atmosphere dnring constant control propellant atomization of attack and bank angles A71-28970 171-29185 Optimal penetration effect on peripheral gas flow GLIDERS temperature field at outlet of turbine Sailplane elevator induced maneuvering and combustion chamber with circular flame tubes horizontal tail surface loads, discussing 871-28971 airworthiness requirements Gas turbine engine combustion chamber outlet, A71-29256 noting gas flow temperature field peripheral Wind tunnel tests of geometrically compatible nonuniformity airfoils for variable chord sailplane A71-28972 A71-29257 Gas turbine auxiliary power unit accessories, GREASES discussing high energy igniters, cihles and Bilitary aviation greases for subsonic commercial connectors, thermocouples and speed and airplane lubricants, discussing economic and temperature monitoring equipment technical benefits based on service experience A71-29262 and testing Eetal coated superalloys evaluation for gas [SAE PAPER 7104111 A71-28304 turbine engine components. including corrosion, GRIUDIUG IACRIUES impact and fatigue tests Helicopter component surface finish smoothness and A71-29635 residual stress requirements, using abrasive Chemical kinetic calculation of nitric oxide grinding belt machines with gear link mechanisms formation in spark ignition automobile engines A71-28943 and gas turbine combustors GROUND EFFECT A71-30454 Longitudinal stability of ground effect airplane, Aircraft JT9D engine development for airline discussing influence on aerodynamic operation, discussing construction, condition characteristics of height. ground surface monitoring, maintenance, noise and smoke roughness and wing aspect ratio reduction A71-29228 [SAE PAPER 7104341 871-30528 GROUND EFFECT IACHINES Gas turbine engine condition analysis by digital Propulsion, guidance and stability of ground computer and fault isolation techniques effect vehicle with perimetric Coanda fluid [SAE PAPER 7104481 A71-30532 bonndary Turbopropulsion systems thrust augmentor A71-29308 combnstion instability, discussing physical Air breathing nuclear propulsion, considering causes due to various pressure oscillation modes reactor safety in air cushion vehicles and [AIAA PAPER 71-6971 A71-30756 aircraft Design point characteristics of 15-80 kWe nuclear A71-29930 reactor Brayton cycle power system SK-5 air cushion vehicles evaluation inclnding [ HASA-TB-X-678 11 ] N71-24689 search/rescue, aids to navigation, law Predicted performance of 15-80 kWe reactor Brayton enforcement, safety logistics and oil pollution power system over ran'qe of operating conditions [AHS PREPRINT 5721 871-31113 [ NASA-TM-X-678333 N71-24690 Potential feasibility of safe, practical, and Hotor starting techniqnes for 2-15 kl Brayton economical air breathing nuclear propulsion space power system system for aircraft and air cushion vehicles [ NASA-TI-X-67819) 871-24691 [ NASA-TM-X-67837 ] N71-25524 Assembly methods for three types of aircraft gas Characteristics and cost analysis of nuclear turbine engines powered air cushion vehicles for oceanic [ AD-7198231 N71-25209 commercial operations Fundamentals of aircraft gas turbine engines [ N ASA-T M-X- 2293 ] N71-25783 [AD-7199131 N71-25808 GROUND EAEDLIBG aircraft gas turbine combustion chamber design Frankfurt terminal baggage conveyor system, [ BAL-TR-2081 N71-26298 describing passenger capacity and luggage GAS TURBIBES handling equipment Continuous combustion gas turbine with stepwise A71-29312 heat release, investigating ideal thermal GROUBD SUPPORT EQUIPHRBT efficiency cycle of gas overexpansion, cooling Design, development, and test of ground support and compression equipment for analyzing aircraft equipment A71-28583 condition and performance [AD-7196751 N71-2460.3
A-28 SUBJECT IBDEX BELICOPTER COBTROL
GROUBil-AIR-GROUND COIHUBICATIOBS AH-56A compound helicopter rigid rotor stability Low carrier power aircraft antenna module for and handling qualities, using flight, whirl airborne UHF communications system, considering tower and wind tunnel tests range/field strength measurements CAES PREPRINT 5741 871-31115 A71-31046 BAIL GUIDANCE (HOTIOR) Meteorological radar for detection of Control, navigation and guidance review, thunderstorms, hail, and turbulence hazardous to considering application of earth reference aviation noting echo interpretation and radar coordinates for aircraft, missiles and transmission spacecraft [ HMO-264-TP-148 3 N71-24394 A71-30710 HAllDLING EQUIPEIEBT GUIDANCE SENSORS Melbourne/Tullamarine airport, describing Sensing and communications technologies for short facilities, capacity, road system, ca*go and wayside headways, considering applicable passenger handling areas and runway layout equipment for personal rapid transit systems, A71-29310 modulation. coding and data transaission Frankfurt terminal baggage conveyor system, techniques describing passenger capacity and luggage A71-30337 handling equipment GUBS (ORDBANCE) A71-29312 Cheyenne attack helicopter weapons system, BARRIER AIRCRAFT discussing night vision capability, armament, Supersonic staggered gutter colander conbustion fire control and navigation equipment system for plenum chamber burning on high bypass integration Pegasus turbofan engine of Harrier VTOL [AHS PREPRINT 5301 A71-31091 aircraft, noting performance improvement GUST ALLEVIATORS 871-28743 Aircraft gust alleviation. considering movement HAZARDS correction based real time atmospheric Plug-in relay hazards and minimization for turbulence measurement aircraft flight safety applications 871-29785 871-28841 Alleviation of lateral and longitudinal gust HEAT RESISTABT ALLOYS effects on aircraft Metal coated superalloys evaluation for gas 871-24709 turbine engine components, including corrosion, GUST LOADS impact and fatigue tests Atmospheric turbulence effect on turbine powered A71-29635 transport aircraft, discussing gust Aluminide coatings for nickel-base superalloy accelerations, avoidance, detection, forecasting developed for high temperature jet engine and pilot control components A71-29750 [ NLSA-CR-728631 N71-25454 Aircraft structural design requirements based on HEAT SHIELDING statistical analysis of air turbulence intensity Heat shield ablation under high enthalpy and gust loads records from large number of chemically active turbulent gas flow in hydrojet research flights engine manifolds 871-29784 A71-28589 Gust transfer functions relating lift and moueuts Parameters contributing to aeroelastic problems in to upwash in single sinusoidal wave for large thermal protection of space shuttle aspect ratio rectangular wings in turbulent 871-24661 incompressible flow Comparison of space shuttle aerodynamic heating A71-30604 analyses for metallic heat shield and surface Cumulative frequency aistributions determined by insulation concepts extreme value analysis used for fatigue analysis 871-26054 and interpretation of c.4. vertical acceleration BEAT TRABSFER and gust belocity measured on transport aircraft Combustion and heat transfer in gas turbine C AGARD-R-579-711 N71-25080 systems - Conference, Cranfield, England, April GUSTS 1969 Extreme turbulence measurement during low level A71-28739 flights of Mirage A3-76 fighter aircraft, Heat transfer on spheres and sharp cones in determining true gust velocities and power rarefied hypersonic gas flow at zero angles of spectral energy distributions attack in wind tunnel vacuum A71-29756 A71-29176 V/STOL aircraft gust effects prediction with Heat transfer within resonant cavities at subsonic mathematical models based on nonlinear hybrid and supersonic flow, discussing wind tunnels, simulation at takeoff and landing altitudes test procedures and data reduction 871-29775 [ASME PAPER 71-FE-93 A71-29450 Aircraft with T tail configuration, examining HEAT TREATIEBT dynamic response to lateral gusts Vacuum heat treatment of brazed and diffusion A71-29786 bonded jet engine components near melting Aircraft design and fatigue life monitoring, temperature investigating effects of gust velocity frequency A71-28145 distribution in patches of atmospheric Soviet hook on aircraft materials science and turbulence treatment covering steel/cast iron processing, 871-29789 metallography, heat/thermochemical conditioning, High rotor advance ratio from multiblade general surface protection and corrosion prevention coordinates method in linear analysis of lifting A71-29529 rotor dynamic stability and gust ratio HEATIBG EQUIPIJEBT CAHS PREPRINT 5121 A71-31083 Procedures for evaluating effectiveness of self propelled and portable ground servicing units for Army aircraft H [ AD-7 19 1023 N71-24459 E-53 HELICOPTER BELICOPTER CONTROL Night rescue terminal navigation, considering Helicopter handling under ASR flight conditions, design, development and tests of Limited Night discussing sea state effect on low altitude Recovery System for HE-53 helicopter hover stability [AHS PREPRINT 534] A71-31095 A71-29384 E-56 BELICOPTER Rotor blade stall induced helicopter control Cheyenne attack helicopter weapons system, loads, combining unsteady aerodynamics with discussing night vision capability, armament, aeroelastic rotor analysis fire control and navigation equipment [AHS PREPRINT 5133 A71-31084 integration AN/ASR-~Ginertial naviqation system consisting of [AHS PREPRINT 5303 A71-31091 inertial platform, digital computer and control
A-29 EELICOPTER DESIGU SUBJECT IUDBX
indicator Soviet book on helicopter design covering [AHS PREPRINT 5333 A71-31094 aerodynamic properties, power plants, control Electromechanical control system synthesis for systems, fatigue minimization and strength compound hingeless rotor helicopter, using root analysis locus method with transfer fnnctions from A71-29944 airframe motion linear model EELICOPTER PBRPORIAUCE [AHS PREPRINT 5361 A71-31096 Restland RG 13 Lynx helicopter, discussing design Heavy lift helicopters IPR hover capability with featnres, performance characteristics and civil slung load, discussing sensors controls and and military applications displays A71-30301 [AHS PREPRINT 5401 A71-31097 Soviet nil V-12 heavy lift helicopter for civil Hingeless rotor helicopter stability and control and military missions, noting tnrbiue engines, characteristics, considering induced flow field, rotor configuration, cargo hold and navigation flapvise bendino modes and blade-fuselaqe system dynimic coupling A71-30420 r ABS PREPRINT 541 1 A71-31098 Noise production during aerodynamic tests on Ha6dling qualities and control sensitivity of high helicopter rotor in wind tunnel performance helicopters, considering pitch and A71-30519 collective control Army rotorcraft performance data, discussing [AHS PREPRINT 5421 A71-31099 hovering and forward flight performance out of Fail-safe helicopter rotor control design, ground and level flight power reqnirements and discussing damage tolerant components, redundant drag and compressibility effects system, failure warning and maintenance [AHS PREPRINT 5001 A71-31076 [ AHS. PBEPRINT 550 ] A71-31102 Helicopter fuselage vertical and in-plane main High performance UH-1 compound helicopter high rotor head vibratory forces isolation with speed flight research, considering rotor loads, hydropneumatic servocentered system at stability, control and flying qualities transmission/airframe interface [AHS PREPRINT 5701 A71-31111 [AHS PREPRINT 5141 A71-31085 AH-56A compound helicopter rigid rotor stability Helicopter rotor stall characteristics, and handling qualities, using flight, whirl investigating blade flexibility, nnsteady tower and wind tunnel tests aerodynamics and variable inflow effects [AHS PREPRINT 5743 A71-31115 [ AHS PREPRINT 5201 A71-31086 Helicopter gyro displacement measurements at High performance UH-1 compound helicopter high differing flying conditions speed flight research, considering rotor loads, [ FOB-2-C-2356- 49-/72/] N71-26567 stability, control and flying qualities HELICOPTEH DESIGU [AHS PREPRINT 5701 A71-31111 Costs-reliability relationships in helicopter Evaluation of helicopter flight loading and development testing and demonstration. structural stability emphasizing decision making in program N71-24389 management Aerodynamic configurations and characteristics of [SAE PAPER 7104527 1171-28330 USSR military helicopters Helicopter design for use as crane ah for [ AD-7195851 N71-25133 carrying external loads HELICOPTER PROPELLER DRIVE A71-28489 Helicopter rotor system vibratory and mechanical Helicopter component surface finish smoothness and stability characteristics, investigating residual stress requirements, using abrasive anisotropically mounted flexible swash plate and grinding belt machines with gear link mechanisms blade out of track effects A71-28943 [AHS PREPRINT 5111 A71-31082 Soviet book on helicopter design covering Optimal turbofan engine and reaction drive rotor aerodynamic properties, power plants, control combinations for helicopter design systems, fatigue minimization and strength [AHS PREPRINT 5611 A71-31108 analysis EELICOPTEH RAKES A71-29944 Hake model and computer program to compute Hestland HG 13 Lynx helicopter, discussing design geometries, flows and velocity influence features, performance characteristics and civil coefficients for helicopter blade load and mi1ita;y applications calculations A71-30301 [ABS PREPRINT 5231 A71-31089 Soviet Nil V-12 heavy lift helicopter for civil Bathematical models for lifting rotor aerodynamic and military missions, noting turbine engines, calculations, noting wake confignrations rotor configuration, cargo hold and navigation [ DLR-MI TT-7 0- 19 3 N71-24489 system HELICOPTERS A71-30420 Helicopters as cranes and external load carriers, Advancing Blade Concept helicopter lifting rotor considering operational costs and investment development, discussing full scale analysis, return design, fabrication and wind tunnel tests A71-29144 [AHS PREPRINT 5041 A71-31080 Soviet book on airplane and helicopter electrical High rotor advance ratio from multiblade general power supply systems covering storage batteries, coordinates method in linear analysis of lifting DC generators, alternators, voltage regulators, rotor dynamic stability and gust ratio current and frequency control, etc [AHS PREPRINT 5121 A71-31083 A71-29525 Optimal turbofan engine and reaction drive rotor Helicopter systems operations in, around and combinations for helicopter design between major metropolitan areas, cons A-30 SUBJECT IUDEX HYPEHSONIC PLOW Rotary wing structural stability of Doruier high angle sensitivity temperature gas jet helicopter A71-31022 N71-24387 HOVERING Dynamic tests of helicopter components Army rotorcraft performance data, discussing N71-24388 hovering and forward flight performance out of Structural stability tests of helicopter ground and level flight power requirements and components drag and compressibility effects 871-24390 [AHS PREPRINT 5001 871-31076 High intensity xeon flashtube lights for Heavy lift helicopters IPR hover capability with increasing conspicuity of trainer helicopters slung load, discussing sensors controls and during daytime and nighttime flights displays [ AD-7 18 639 3 871-24669 [AHS PREPRINT 5401 A71-31097 Calculatins and testinq antiicins-- systems of Eoverins performance tests of iet-flamed rotors aircraft-and helicopters and comparison of predicted ana act& results [AD-7199221 E171 -25622 [NAL-TR-2111 N71-25396 HIGH ALTITUDE BALLOOUS HOVERING STABILITY High altitude balloons pressurealtitude Helicopter handling under ASW flight conditions, transducer assembly, discussing electronic discussins sea state effect on low altitude circuitry. calibration and temperature and hover stability vibration effects A71-29384 871-30070 HUKAN REACTIONS HIGE ASPECT RATIO Pilot subjective evaluation of XB-70 aircraft Friction factor for low Reynolds number turbulent response to atmospheric turbulence in comparison flow in large aspect ratio rectangular ducts, with measured accelerations comparing Blasius and Prandtl relations A71-29774 [ASME PAPER 71-PE-A] A71-29378 HYDHAULIC EQUIPIEUT Gust transfer functions relating lift and moments Third Chance flight control system, discussiug to upwash in single sinusoidal wave for large aircraft control capability with backup aspect ratio rectangular wings in turbulent hydraulic system after loss of dual main incompressible Lrlow hydraulic systems due to combat damage A71-30604 A71-29382 Fuselage influence on total aircraft drag in Thrust measurement of aircraft propulsion systems, subsonic passenger aircraft, considering high considering hydraulic piston device, edge aspect radio cylindrical fuselages clearance, oil quantity and calibration A71-30821 A71-29860 HIGH PHEQUEUCIES HYDBOCABBON COIBUSTIOB Performance and cost design tradeoff between HF Soviet papers on combustion processes in turbulent and synchronous meteorological satellite data and laminar flows of kerosene and gasoline collection systems, considering platform mixtures, stressing gas turbine engines problems transmitting power and SNR A71-28954 171-30900 HIPEHBOLIC NAVIGATION HIGH BESOLUTIOB Long range hyperbolic navigation in U.S., Visual flight simulation devices, considering high discussing loran and Omega systems resolution photogrphic films and digital A71-30711 memories HYPEBSONIC BOIINDAHY LAYER A71-29483 Slender cone boundary layer transition under angle HIGH SPEED of attack at Uach 21 with promoted leeward and Flow meter for measuring stagnation pressure in fixed windward ray boundary layer around high speed flight vehicle A71-29887 [NASA-CASE-XPE-O2007] N71-24692 HYPEHSONIC PLIGHT HIGH TEIPERATURE ENVIROUlEBTS Hypersonic flight load bearing refractory alloy Aircraft flight load measurements in high control surface protective coatings, emphasizing temperature environment, determining optimal oxidation screening tests strain gage installation and calibration A71-29646 A71-30681 conductive heat transfer effect on temperature HIGH TEIPEHATUBE GASES distribution in vicinity of wing leading edge in Gas temperature measurement in aircraft combustion hypersonic flight chambers, using calorimetric probe [ ARC-CP-11263 N71-24446 A71-28757 Minimizing drag and increasing performance of Temperature and radical concentration measurements optimum shapes at hypersonic flight for high temperature flowing gas streams in rig 871-24704 simulating conditions in ramjet combustion HYPEESOliIC PLOW chamber and nozzle Aerodynamic characteristics similarity and 871-28758 variation in hypersonic flow transition region EIGHWAYS from free molecular flow to solid medium Aviation and surface transportatation safety for A71-29172 1970 with related accident investigations and Heat transfer on spheres and sharp cones in recommendations rarefied hypersonic gas flow at zero angles of [ AB-4 3 N71-24925 attack in wind tunnel vacuum EOLOGBAPHY A71-29176 Holographic techniques, optical data processing Hypersonic flow around delta wing at small angles and laser properties for aerospace of attack, using pressnre sonrces method and instrumentation Fredholm integral equation A71-30329 A71-29189 EOBIBOUTAL TAIL SURFACES unsteady hypersonic self similar gas flow and drag Sailplane elevator inawed maneuvering and on circular cone accelerated according to power horizontal tail surface loads, discussing law. using small perturbation theory airworthiness requirements A71-29205 A71-29256 wind tunnel simulation of viscous hypersonic flow- HOHU ABTEUUAS laminar boundary layer interactions, presenting High speed airborne scanning navigational radar similarity parameter effects on aerodynamic antenna with matched patterns, using offset horn characteristics fed relector and polarization modes for improved 871-29224 visual display Monograph on hypersonic shock tunnel supersonic A71-31036 combustion research techniques covering test HOT-PIRE FLOWIETEBS facilities, optical and electromaqnetic flow X-type hot-wire probe thermal turbulent wake measuremept methods, etc interference, discussing wind tunnel am-29578 investigation of vire distance effect on pitch A-31 BYPERSONIC REENTRY SUBJECT INDEX Turbulent skin friction and heat transfer numerical analysis prediction on flat plates and wind tunnel walls A71-30068 at supersonic and hypersonic Mach numbers, using Incident sonic boom shock wave reflection factors Van Driest theory off smooth surface, discussing pressure rise and 871-29868 flight near threshold Mach number Hypersonic flow pattern past windward side of 871-30610 delta wing with supersonic leading edges, INCOEPRESSIBLE FLOW joining potential and vortex regions behind Aerofoil cascades with axial velocity change in shock wave incompressible flow, determining turbine blade 871-30874 force dependence on circulation plow measurement of Nonweiler delta wing in 871-28467 hypersonic slip flow Incompressible fluid motion in laminar boundary [ DLR-FB-70-463 N71-24500 layer on blade rotating uniformly about axis HYPEBSOBIC REEBTBP perpendicular to wing span Bypersonic shock/density ratio effects in A71-30218 aerothermodynamic heating of space shuttle Oscillatory pitching moment derivatives configuration measurement on delta wings in incompressible N71-26058 flow BYPERVELOCITY FLOW [ ARC-R/U-3628-PT-1-4] N71-24569 Tests to determine short-term creep of metals and measurements of oscillatory pitching moments on alloys under conditions of aerodynamic heating round leading edged delta wing in incompressible with high velocity air flow flow noting vortex flow development [NASA-TT-F-136331 N71-25822 N71-24570 Pinite difference method for calculating inviscid IBCOHPRESSIBLE FLUIDS flow field around supersonic/hypersonic space Incompressible conducting fluid plane jet shuttle expansion in homogeneous slipstream, deriving N71-26056 partial differential equations for nonconduction BYPERVELOCITY WIND TUNNELS approximation Uind tunnel simulation of viscous hypersonic flow- A71-29610 laminar boundary layer interactions, presenting Axisymmetrical three component flow equations for similarity parameter effects on aerodynamic incompressible viscous fluid in cylinder with characteristics rotating disk A71-29224 A71-30855 Bypervelocity blowdown nitrogen wind tunnel with IBEBTIAL NAVIGATION graphite resistance beater noting nozzles, Boeing 747 crew members training program, diffuser, and calibration describing ground training. classrooms, inertial [IC-AER0-71-01] N71-24675 navigation system and cockpit trainers [SAE PAPER 7104733 871-28339 Inertial navigation systees improvements for I commercial air transportation, noting digital ICE POBUATIOA computer program revision and increased Fincap communication antennas design and functional capability environmental tests for vibration. acceleration, [SAE PAPER 7104581 A71-30534 waterproofing, salt corrosion, ice formation and Combined inertial and instrument landing aircraft compass safe distance navigation systems with reduced cross runway A71-31047 position and velocity errors, using optimal IGBITEBS linear estimation Gas turbine engine startup igniter with modified 171-30606 propellant atomizer enhanced by air injection Air navigation techniques history, considering A71-28969 radio, radar, loran Doppler and inertial Gas turbine auxiliary power unit accessories, navigation discussing high energy igniters, cables and A71-30712 connectors, thermocouples and speed and AN/ASN-86 inertial navigation system consisting of temperature monitoring equipment inertial platform, digital computer and control A71-29262 indicator IGNITIOB SYSTEUS [AHS PREPRINT 5331 A71-31094 Diffusion and thermal mechanism ignition theories, IBEBTIAL PLATFORMS applying to altitude relighting of gas turbine Ali/ASN-86 inertial navigation system consisting of engine combustors inertial platform, digital computer and control A71-28745 indicator IUPACT ACCELEBATION [ASS PREPRINT 5331 A71-31094 Studying aircraft accidents to determine impact INFLUENCE COEFFICIENT angle and speed criteria for designing nuclear Wake model and computer program to compute airplane fission product containment vessel geometries, flows and velocity influence [ NASA-TU-X-22451 N71-25411 coefficients for helicopter blade load IUPACT DAUAGE calcnlations Haterials and structural design development by [AHS PREPRINT 5231 A71-31089 high velocity impact testing aue to transport INPBABED DETECTORS and subsonic military aircraft susceptibility to Airborne equipment for CAT detection ahead of bird collision damage aircraft, considering pulsed Doppler laser and A71-29642 IR detectors IUPEDIFCS HEASUBEUEEITS A71-29765 Impedance measurements 'on modified broadband metal Development and characteristics of scanning antenna for speech communication systems for thermal viewers and infrared [ POA-3-C-3602-61] N71-26150 detectors for airborne operation IB-PLIGXT UOBITOBIBG [ AD-71985U ] N71-25053 Onboard computer for aircraft engine testing, Aircraft mounted infrared detectors for remote monitoring and data reduction, emphasizing measurements of optical cloud properties automatic in-flight recording for post-flight N71-25260 displays IBPBABED IBSTBUUEBTS [AIAA PAPER 71-6511 A71-30727 Development and characteristics of scanning Engine condition monitoring systems, discussing systems for thermal viewers and infrared engineering design requirements with respect to detectors for airborne operation accessibility, accuracy, economics, [ AD-71 98541 N71-25053 effectiveness, reliability and maintainability IBGESTIOB (ENGINES) [AIAA PAPER 71-6523 A71-30728 Exhaust gas ingestion and recirculating flow field IBCIDBBT BADIATIOB characteristics of small scale vertical take off Simply supported normal mode plate time response engine pod to traveling wave at obligue incidence, using [ NASA-CR-1774 1 N71-25397 A-32 SUBJECT IEDEX JET ENGIEE PUELS IHLET PLOW traffic growth rates Test description and results for high Mach number A71-30161 transonic fan stases to determine ranqe and IRIDIUM ISOTOPES distortion tolerance for various roto; tip nondestructive testing of aircraft structures casing treatment configurations using thulium and iridium gamma sources [ NASA-CR-828623 871-25460 [ JAERI-BEMO-41631 N71-24849 Tabulations of blade element and circumferential ITERATIVE SOLUTION distortion flow data in tests of high Mach Least squares method and iteration technique for number transonic fan stages with various rotor obtaining aerodynamic stability derivatives tip casing treatment configurations B71-24703 [ BASA-CR-828671 871-25461 IELET PRESSURE Engine surge pressure transients in mixed- J compression supersonic inlet, describing scale 3-85 EBGINE wind tunnel model simulation and measurement Time variant distortions in supersonic inlet on techniques J-85-GE-13 turbojet engine from wind tunnel [AIAA PAPER 71-6711 1171-30735 test, considering instantaneous distortion INSPECTION amplitudes and contours Airport certification and safety inspection [AIAA PAPER 71-6673 A71-30733 procedures and minimum safety standards JET AIRCRAFT [SAE PAPER 7104131 871-28305 Microbiological contamination of jet aircraft fuel IBSTALLIBG tanks in tropical regions, considering Aircraft flight load measurements in high maintenance temperature environment, determining optimal [SAE PAPER 7104381 A71-28320 strain gage installation and calibration En route turbojet aircraft flight speed control, A71-30681 assessing impact on ATC procedures IESTRUMEET ERRORS A71-28884 Aircraft barometric altimeter errors caused by Dassault Mercure short range twin jet aircraft atmospheric temperature deviations from capable of using powerful engine International Standard Atmosphere A71-29276 A71-30323 Jet-supported VTOL aircraft fuel-time-optimal Fan-produced sound pressure fluctuation in very landing control, using mathematical model, lou speed subsonic wind tunnel test stream, Pontryagin maximum principle and analog computer noting resulting anemometer calibration errors solution A71-30526 A71-29281 IESTRUMEET PLIGHT RULES Integrated short-haul interurban transportation Heavy lift helicopters IFB hover capability with system, considering combination of conventional slung load, discussing sensors controls and jet aircraft, STOL aircraft and high-speed displays ground transportation [AHS PREPRINT 5401 A71-31097 [AIAA PAPER 71-5081 A71-29550 IBSTBUIENT LANDING SYSTEMS Atmospheric turbulence effect on turbine powered Combined inertial and instrument landing aircraft transport aircraft, discussing gust navigation systems with reduced cross runway accelerations. avoidance. detection. forecastino position and velocity errors, using optimal and pilot conLrol linear estimation 871-29750 A71-30606 Jet transport aircraft stability and Handling qualities of V/STOL research vehicles controllability under atmospheric turbulence during steep terminal area approaches, conditions, discussing longitudinal and lateral- discussing powered lift fan VTOL aircraft directional characteristics with particular limitations and instrument landinq approach attention to unstable spiral mode [ AHS PREPRINT 5441 A71-31101 871-29772 IETEGBAL TBAESPOBIATIOBS Jet transport aircraft design for safety under air Numerical evaluation of dounuash integral for wing turbulence conditions, considering cruise loading of lifting rectangular planform altitude limitations and pitch and g excursion [ NPL-BA-901 N71-24483 reduction by special autopilot mode 1BTEGBU"l'D CIRCUITS 871-29777 Interface IC circuits for driving high voltage wind tunnel force test program design for jet transistor switches from low level logic inputs, aircraft configurations, including propulsion noting avionics application system simulation A71-28910 871-30605 IBTEBPEBEBCE LIFT Jet vertical takeoff aircraft piloted cockpit ling-jet interference effects in cross wind on simulator for controlling aircraft flight thrust and aerodynamic characteristics at large performahce distance from and near around [ARC-R/M-3647] N71-25065 A71-29207 Flight evaluation of lateral handling, stability, IETEBEAL COMPRESSION INLETS control, and flying qualities of jet transport Analytical model of compressor sensitivity to aircraft during up-and-auay and approach flight transient and distorted transient flows; in landing configuration considering inlet duct, compressor stages and [ NASA-TN-D-63393 N71-25537 combustor up to turbine nozzles JET AIRCRAFT BOISE [AIAA PAPER 71-670) A71-30734 Noise attenuation prediction in absorbing ducts Aind tunnel tests to determine Mach 2.5 adaptable to bypass jet engines, using rlorse performance of bicone inlet with internal theory focnsed compression and 40-vercent internal 871-30522 contraction- Jet aircraft sound spectrum on ground and in air; [ BASA-TM-X-22941 N71-25872 comparing calcnlation with experiment IETERNATIONAL COOPEBATIOE A71-30524 Air transport development trends, considering Acoustic liner design for propellant combustion increased speed and capacity, STOL aircraft, instability and jet aircraft noise suppression, urban service, and European cooperation for discussing cross flow and oscillatory pressure mauufacturina effects A71-30302 [AIAA PAPER 71-7571 871-30791 IETEBNATIOBAL LAW JET COHTROL Book on air law and civil air policy coveriuq Plowfield production by fluid injection into international regulation, ai; traffic market, supersonic crossflow, occurring with liquid/gas passenger and cargo services, etc jet control of vehicle with combustion ramjets A71-29938 [AIAA PAPER 71-7283 871-30775 INTEPNATIONAL TRADE JET ENGIBE FUELS Long haul international air transport, analyzing Airport jet fuel delivery system salt driers for A-33 JET EBGIBES SUBJECT IBDEX reducing water content below saturation, partial differential equations for nonconduction lengthening filter life and improving downstream approximation system components performance A71-29610 [SAE PAPER 7104401 A71-28322 Low thrust jet effect on base pressures on JET EBGIEES boat-tailed afterbodies in Each number 0.8-1.2 Vacuum heat treatment of brazed and diffusion flow bonded jet engine components near melting A71-29889 temperature Hot jet aerodynamic parameters from emissions of A71-28145 electromagnetic and acoustic energies by crossed Olympus 593 pure jet twin shaft engine development beam IR probing program for concorde, discussing engine A71-30520 evolution, design considerations and flight JET IMPIBGEUEET development Wing-jet interference effects in cross wind on [SAE PAPER 7104221 871-28309 thrust and aerodynamic characteristics at large Air bypass behind compressor into variable area distance from and near ground exhaust nozzle, obtaining energy losses from gas 871-29207 turbine jet engine indices JET EIXING PLOW 871-28586 Optimal penetration effect on peripheral gas flow fieat shield ablation under high enthalpy temperature field at outlet of turbine chemically active turbulent gas flow in hydrojet combustion chamber with circular flame tubes engine manifolds A71-28971 A71-28589 uind tunnel investigation of jet exhausting into Aircraft jet engines technological progress review cross flow - data for three jet Configuration over past 25 years, emphasizing industry [ AD-71 8 1231 N71-24491 economics considerations uind tunnel investigation of jets exhausting into % A71-30303 cross flow - description and data analysis Einiature transducers design and fabrication for AD-7 18 1221 871-24492 fluctuating pressure measurements in jet engine JET PHBOST testing, noting frequency response and power Wing-jet interference effects in cross wind on dissipation thrust and aerodynamic characteristics at large A71-30324 distance from and near ground Fluctuating pressure measurements in jet engine A71-29207 testing, using miniature transducers with Afterburning turbofan engine thrust calculation by calibration and data acquisition equipment gas generator method, using P-lllA for 871-30325 comparison tests modular concept mathematical model for combustion [AIAA PAPER 71-6801 A71-30744 and pollution formation processes in jet engine Rotary wing structural stability of Dornier high combustors, including turbulent mixing and temperature gas jet helicopter reaction kinetics N71-24387 [AIAA PAPER 71-7141 871-30766 Isolated axisymmetric jet engine exhaust nozzles thrust and drag predictions in sub-, traus- and K supersonic flight regimes KEROSENE [AIAA PAPER 71-7191 871-30770 Kerosene type fuels for aircraft gas turbine Exhaust gas ingestion and recirculating flow field engines, discussing combustion problems, smoke characteristics of small scale vertical take off emission reduction and bacterial or fungal engine pod contamination [ NASA-CR-17741 N71-25397 A71-28754 Alominide coatings for nickel-base superalloy KINEEATIC EQUATIONS developed for high temperature jet engine controlled aircraft motion under strict kinematic components constraints in terms of simple subsystems, [ NASA-CR-72863 3 871-25454 noting pilots role in Newmark theory Fuel tests to determine feasibility of gelled A71-31024 methane for use in jet engine [ NASA-CR-728761 N71-25772 JET EXHAUST L Visible exhaust smoke trails from aircraft jet 1-1011 AIRCRAFT engines, measuring optical density by 1-1011 aircraft flying stabilizer, discussing photographic photometry choice of longitudinal flight control systems [ SAE PAPER 7704281 A71-283 14 [SAE PAPER 7104261 A71-28312 Isolated axisymmetric jet engine exhaust nozzles Automatic landing systems independent monitor for thrust and drag predictions in sub-, trans- and 1-1011 aircraft, providing pilot confidence supersonic flight regimes under reduced visibilities [AIAA PAPER 71-7193 871-30770 [SAE PAPER 7104433 A71-28324 Wind tunnel investigation of jet exhausting into 1-1011 Tristar antenna arrangement test results, cross flow - data for three jet configuration considering weight. aerodynamic and structural [ AD-718123 ] N71-2449 1 design requirements LOW speed wind tunnel test of four ft diameter A71-31060 circular plate model with three exhausting jets LAMINAR BOUNDARY LAYER [ AD-7202331 N71-26517 Rind tunnel simulation of viscous hypersonic flow- JET FLAPS laminar boundary layer interactions, presenting Two dimensional jet flap cascades, presenting similarity parameter effects on aerodynamic stream deflection angles as function of jet to characteristics mainstream momentum flux A71-29224 [ ASEE PAPER 71-FE-141 A71-29453 Incompressible fluid motion in laminar boundary Hovering performance tests of jet-flapped rotors layer on blade rotating uniformly about axis and comparison of predicted and actual results perpendicular to wing span [ NAL-TR-2111 N71-25396 A71-30218 uind tunnel tests to determine low-speed LAUINAE PLOU aerodynamic characteristics of large-scale STOL Soviet papers on combustion processes in turbulent transport model with augmented jet flap and laminar fiows of kerosene and gasoline (NASA-TM-X-62017] N71-26183 mixtures, stressing gas turbine engines problems JET FLOW A71-28954 Aerodynamic noise produced by supercritical jets, LANDING GEAR using high speed flash photography for schlieren Powered landing gear wheel system requirements for and shadowgraph studies parking ana taxiing of commercial jet transport A71-28767 airplanes Incompressible conducting fluid plane jet [SAE PAPER 7104461 871-30530 expansion in homogeneous slipstream, deriving A-34 SUBJECT INDEX LINEAR ARRAYS LANDING LOADS Numerical evaluation of downwash integral for uing Landing load estimation methods for preliminary loading of lifting rectangular planform design weight prediction for military aircraft [NPL-MA-901 N71-24483 A71-28211 Direct lift control system having flaps with slots LASERS adjacent to their leading edge and particularly Eolographic techniques, optical data processing adapted for lightweight aircraft and laser properties for aerospace C NASA-CASE-LAR-10249-'I 1 N71-26110 instrumentation LIFT DRAG RATIO A71-30329 conical body lift/drag ratio increase by wedge LATERAL CONTROL shaped nose, noting applications to space Elevons as longituainal and lateral control vehicles entering atmosphere above escape elements on low aspect ratio wings, calculating velocity subsonic and supersonic aerodynamic A71-29183 characteristics LIPT FANS A71-29190 VTOL propulsion, discussing gas turbine pressure Supersonic aircraft lateral control equipment ratio inlet temperature and lifting and high [AD-7207401 N71-26538 bypass fans LATERAL STABILITY 871-27838 Flight evaluations using variable stability Tip turbine driven lift fan noise reduction tests, aircraft to determine effects of turbulence considering design parameters effects induced aerodynamic disturbances and lateral [AIAA PAPER 71-7433 A71-30784 directional dynamics on pilot performance Eandling qualities of V/STOL research vehicles [ NASA-CR-17181 N71-26170 during steep terminal area approaches, LAUNCH VEHICLE CONFIGURATIONS discussing powered lift fan VTOL aircraft Buffet response of straight wing and delta wing limitations and instrument landing approach model of space shuttle launch configuration CAES PREPRINT 5441 A71-31101 871-24662 LIFTING BODIES Transonic wind tunnel investigation of flou Miniature aerodynamic turbulence gage using characteristics and pressure fluctuation of axisymmetric lifting body sensor space shuttle launch and reentry configurations A71-28158 N71-24663 Trailing vortices shed by aircraft lifting LEADING EDGES surfaces, noting wake effects importance at low Eypersonic flow pattern past windward side of speeds delta wing with supersonic leading edges, A71-28 176 joining potential and vortex regions behind unsteady curvilinear motion of lifting surface, shock wave calculating induced gas flow velocities in terms A71-30874 of vortex densities Conductive heat transfer effect on temperature A71-29188 distribution in vicinity of wing leading edge in LIFTING REENTRY VEEICLES hypersonic flight Leeside aeroaynamic heating of lifting reentry [ ARC-CP-11261 N71-24446 vehicle configurations Angle of incidence effect on delta wing N71-26061 leading-edge vortices with cross flow Analysis of aerodynamic forces on DL-4 lifting visualization in hydraulic test tunnel entry vehicle and comparison with theoretical [ ARC-R/M-3 6453 N7' "4482 methods LEAST SQOARES METHOD [ NASA-TEI-X- 19943 N71-26354 Least squares method and iteration technique for LIFTING ROTORS obtaining aerodynamic stability derivatives Advancing Blade Concept helicopter lifting rotor N71-24703 development, discussing full scale analysis, LEE WAVES design, fabrication and wind tunnel tests Lee surface flow and aerodynamic heating on delta [AES PREPRINT 5041 A71-31080 wing orbiter Eelicopter rotor blade airload by applying lifting 871-26060 surface solution Leeside aerodynamic heating of lifting reentry [ABS PREPRINT 5101 A71-31081 vehicle configurations Eigh rotor advance ratio from multiblade general N71-26061 coordinates method in linear analysis of lifting LIFT rotor dynamic stability and gust ratio Air flow about low aspect ratio delta wing at [ABS PREPRINT 5121 A71-31083 large angles of attack, deriving lift Eingeless rotor helicopter stability and control coefficient characteristics, considering induced flow field, A71-28282 flapwise bending modes and blade-fuselage Minimum drag wing-fuselage combination for dynamic coupling snpersonic speeds and prescribed lifting force, [AES PREPRINT 5411 A71-31098 longitudinal moment and volume, using method of Composite materials application to V/STOL successive approximations prop/rotors, determining material properties A71-29182 parametric effect on frequencies and weight by Supercavitating flow past straight cascade with Southwell coefficients arbitrary blade shapes, considering lift and [ABS PREPRINT 5541 A71-31106 drag coefficients. cavitation number, cavity Mathematical models for lifting rotor aerodynamic shape and exit flow conditions calculations, noting wake configurations [ASME PAPEN 71-FE-61 A71-29448 [DLR-HITT-70-19] 871-24489 V/STOL propulsion units lift ratings based on LIGHT AIRCRAFT aircraft system requirements Direct lift control system having flaps with slots [SAE PAPER 7104711 A71-30537 adjacent to their leading edge and particularly Eigh lift and boundary layer separation behavior adapted for lightweight aircraft of sweptback wing airfoil profile noting [NASA-CASE-LAR-l0249-1] N71-26110 trailing and leading edge stall pattern LIGHTBILL METHOD [ ARC-R/H-3648] N71-24488 Low aerodynamic drag airfoil designing by LIFT DEVICES Lighthill method Vortex wakes behind STOL operations high lift [ ARC-R/H-3618] N71-24498 wings, discussing height above ground and LINE SPECTRA various wind tunnel dimensions effects Complex noise emission spectra from superposition A71-28033 of continuous component ana peaks, calculating Two dimensional flow research on high lift level separations due to perfectly reflecting airfoils for STOL aircraft, using vorticity plane distribution and wind tunnel wall blowing A71-30523 techniques LINEAE ARRAYS A71-29910 High speed electronic phase ana frequency scanned linear, static fed and monopnlse arrays eleaent A-35 LINING PROCESSES SUBJECT INDEX and angular error analysis A71-30712 A71-31049 LOW ASPECT RBTIO Blade antenna linear array design for aircraft- Three dimensional steady separated liquid and gas satellite communication, determining mutual flows past low aspect ratio bodies, deriving influences by array measurements in simulated similarity laws for reduction to two dimensional electrical environment problem A71-31062 A7 1-29 169 LINING PROCESSES Lon ASPECT RATIO WINGS Acoustic linings for attenuation of fan generated Air flow about low aspect ratio delta wing at noise in turbofan engines, considering large angles of attack, deriving lift interaction between analytical lining coefficient performance prediction and flow duct testing A71-28282 [AIAA PAPER 71-7311 A71-30778 Elevons as longitudinal and lateral control Flow-duct test facility data on acoustic behavior elements on low aspect ratio wings, calculating of lined ducts and duct-lining materials for subsonic and supersonic aerodynamic turbojet engine applications characteristics [NASA-CR-111887] 171-26417 A71-29 190 LINIBGS Air flow past small aspect ratio thick-section Acoustic liner design for propellant combustion wing at small angles of attack, investigating instability and jet aircraft noise snppression. vortex system effect on flow characteristics in discussing cross flow and oscillatory pressure absence of lift effects A71-29234 [AIAA PAPER 71-7571 A71-30791 Aerodynamic characteristics of low-aspect-ratio LIQUID ATOMIZBTIOB wing mounted on cylindrical body, simulating by Carbon deposition rates in gas turbine engine system of horseshoe vortices combustion chambers with airstream-mechanical A71-30264 propellant atomization LOP LEVEL TURBULENCE A71-28970 Extreme turbulence measurement during low level LIQUID PLOW flights of Mirage A3-76 fighter aircraft, Three dimensional steady separated liquid and gas determining trne'gust velocities and power flows past low aspect ratio bodies, deriving spectral energy distributions similarity laws for reduction to two dimensional A71-29756 problem LOW SPEED WIBD TUNNBLS A7 1- 29169 Wind tunnel investigation of jets exhausting into LIQUID SLOSHIBG cross flow - description and data analysis Pressure sensor network for measuring liquid [ AD-7181221 N71-24492 dynamic response in flight including fuel tank nind tunnel tests to determine low-speed acceleration, liquid slosh amplitude, and fuel aerodynamic characteristics of large-scale STOL depth monitoring transport model with augmented jet flap [NASA-CASE-XLA-O5541] N71-26387 [ NASA-T?l-X-62017] N7 1-26 183 LOAD DISTRIBUTION (FORCES) Low speed wind tunnel test of fonr ft diameter Sailplane elevator induced maneuvering and circular plate model to determine surface static horizontal tail surface loads, discussing pressure distributions for jet decay airworthiness requirements characteristics of cross flow A71-29256 [AD-7202321 N71-26516 LOADING OPERATIOBS Low speed wind tnnnel test of four ft diameter Helicopters as cranes and external load carriers, circular plate model with three exhausting jets considering operational costs and investment [ AD-7202331 N71-26517 return LOW TERUST 871-29144 Low thrust jet effect on base pressures on LOADS (FORCES) boat-tailed afterbodies in Uach number 0.8-1.2 Aerodynamic behavior of bodies in wake of two flow dimensional bluff bodies, discussing loads A71-29889 A71-29265 LOW VISIBILITY Atmospheric turbulence effects on handling Antomatic landing systems independent monitor for qualities and structural loads on aircraft 1-1011 aircraft, providing pilot confidence A71-29787 nnder rednced visibilities JGIC CIRCUITS [SAE PAPER 7104431 871-28324 Interface IC circuits for driving high voltaqe LUBRICANT TESTS transistor switches from low level logic inputs, Olympus 593 supersonic engine lubricants tests, noting avionics application defining requirements in terms of bulk thermal A71-28910 stability, resistance to hot bearing breakdown, LONGITUDIBAL CONTROL oil mist coking, etc 1-1011 aircraft flying stabilizer, discnssing A71-29826 choice of longitudinal flight control systems LUBRICATING OILS [SAE PAPER 7104261 A71-28312 Military aviation greases for subsonic commercial Elevons as longitudinal and lateral control airplane lubricants, discussing economic and elements on low aspect ratio wings, calculating technical benefits based on service experience subsonic and supersonic aerodynamic and testing characteristics [SAE PAPER 7104111 171-28304 A71-29190 Olvmpus 593 supersonic ensine lubricants tests, LONGITUDIBAL STABILITY zefining requirements in terms of bnlk thermal Longitudinal stability of ground effect airplane, stability, resistance to hot bearing breakdown, discussing influence on aerodynamic oil mist coking, etc characteristics of height, ground surface A71129826 roughness and wing aspect ratio 871-29228 Low-speed wind tunnel longitudinal stability tests M on sweptback wing model with blowing at leading 11-2 LIFTING BODY edge slats and trailing edge flaps for Buccaneer Transonic wind tunnel tests of vertical fin loads aircraft performance and rudder hinge moments on U2-F3 lifting body [ ARC-R/M-3655] N71-24565 scale model at Mach 0.50 to 1.30 LORAN [NASA-TU-X-22861 N71-24581 Long range hyperbolic navigation in U.S., nacn NUBBEE discussing loran and Omega systems Altimeter-airspeed and Each number pressure 871-30711 transdncer with diaphragm free of temperature Air navigation techniques history, considering and vibration effects radio, radar, loran Doppler and inertial 171-30322 navigation A-36 SUBJECT IBDEX MECHANICAL MEASUREMEAT MACHIISERY MBTERIALS HANDLING Precipitation detector and mechanism for stopping Melbourne/Tullamarine airport, describing and restarting machinery at initiation and facilities, capacity, road system, cargo and cessation of rain passenger handling areas and runway layout [NASA-CASE-XLA-2619] N71-26334 A71-29310 MAGNETIC MEASUREMENT MATERIALS SCIEBCE Geomagnetic components measurement from moving Soviet book on aircraft materials science and platforms, discussing coordinate system treatment covering steel/cast iron processing, stabilization methods for errorless time metallography, heat/thermochemical conditioning, averaging of measurements surface protection and corrosion prevention A71-28249 A71-29529 MAIBTAIBABILITY Aerospace materials - Conference. Anahejm, FAA aircraft design appraisal for maintainability, California, April 1971 considering maintenance concepts and adverse A71-29633 airworthiness situations Advanced composite vs conventional material [SAE PAPER 7104311 A71-28316 components in cost comparison for aircraft parts Airline operator evaluation of maintainability, A71-29656 considering costs and investment return BATERIALS TBSTS [SAE PAPER 7104321 871-28317 Materials and structural design development by MALAYA high velocity impact testing due to transport Oklahoma and Malaysia thunderstorms comparison and subsonic military aircraft susceptibility to based on weather reconnaissance aircraft bird collision damage measurements, considering turbnlence patches A71-29642 A71-29752 MATHEMATICAL MODELS EALPUIICTIOBS Monograph on potential flow interaction between LlAC malfunction detection, analysis and recording blade rows in axial flow compressors covering system applications in commercial airlines, mathematical model, numerical analysis and emphasizing real time response for maintenance experiment function 871-28883 [SAE PAPER 7104253 1171-28311 High entrainment constant area multiple nozzle Electrical and physical nature of microbial ejectors with tu0 mixing tube lengths for membranes implicated in aircraft fuel quantity boundary layer control, estimating performance probe malfunction with analytical model [SAE PAPER' 7104391 A71-28321 [ ASME PAPER 71-PE-341 871-29469 MAN MACRINE SYSTEMS V/STOL aircraft gust effects prediction with Controlled aircraft motion under strict kinematic mathematical models based on nonlinear hybrid constraints in terms of simple subsystems, simulation at takeoff and landing altitndes noting pilots role in Newmark theory A71-29775 A71-31024 Modular concept mathematical model for combustion MAUAGEMEUT PLAUBIBG and pollution formation processes in jet engine Technical, sales/marketing and management - combustors, including turbulent mixing and Conference, Coronado, California, May 1971 reaction kinetics 871-28164 [AIAA PAPER 71-7147 A71-30766 German monograph on game theory and planni& Nonlinear mathematical model for dynamical techniques for aircraft evaluation behavior of extensible towing cable subjected to 1171-28880 aerodynamic forces generated by uniform flow Aviation within total transport system, discussing field, discussing system stability decision making and management planning A71-31026 A71-30165 Wake model and computer program to compute Criteria for converting aeronautical project geometries, flows and velocity influence operational targets into actual requirements and coefficients for helicopter blade load technical specifications, emphasizing cost calculations effectiveness [AES PREPRINT 5231 A71-31089 A71-30824 Mathematical models for lifting rotor aerodynamic Scientific results from ESRO satellites and from calculations, noting wake configurations sounding rocket campaign including aeronautical [ DLR-EITT-70-193 N71-24489 fields, management planning, satellite General aviation traffic implied densities and development, and telecommunication - 1969 report interaction frequencies computed with model N71-24447 using southern California to judge difficulty MANUFACTURIBG for naval air traffic Complex structural aircraft components [ AD-7199061 N71-25621 manufacture, using group technology principle MEASURING INSTRUMENTS based on subdivision of parts classes Circumferential traversing probe technique for A71-30267 intrastage analysis of axial flow compressors, EAPPIBG considering mass flow averaging data reduction ATC radar display systems mapping techniques using technique vectors and optical projections [ASME PAPER 71-FE-331 A71-29468 A71-30014 Soviet book ou experimental aerodynamics covering MARINE PROPULSION wind tunnels, shock tubes, liguid and gas SK-5 air cushion vehicles evaluation including physical properties, flow parameter measurement search/rescue, aids to navigation, law equipment, etc enforcement, safety logistics and oil pollution 871-29524 [AES PREPRINT 5721 A71-31113 Supersonic mass flux probe description, discussing MARKETIBG inlet geometry, angle of attack and Reynolds and Technical, sales/narketing and management - Mach numbers effects on performance Conference. Coronado. California, May 1971 A71-29925 A71-28164 IECHAUICAL DRIVES MASS PLOP Reduction gearbox reliability problems from Circumferential traversing probe technique for development and service experience with PT6A intrastage analysis of axial flow compressors, turboprop engine considering mass flow averaging data reduction [SAE PAPER 7104331 A71-28318 technigue MECHANICAL MEASUREMEAT [ASME PAPER 71-FE-331 871-29468 Oscillatory pitching moment derivatives MASS PLOH RATE measurement on delta wings in incompressible supersonic mass flux probe description, discussing flow inlet geometry, angle of attack and Reynolds and [ ARC-R/M-3628-PT-1-4] N71-24569 Each numbers effects on performance Heasurements of oscillatory pitching moments on A71-29925 round leading edged delta wing in incompressible flow noting vortex flow development A-37 MECEAIIICAL PROPERTIES SUBJECT IUDEX N71-24570 A71-31074 Measurements of aerodynamic drag, interference MICBOIAVE EQUIPMEUT lift, and pitching moment on delta wings Microstrip p-i-n diode controlled L band digital A71-24573 phase shifter for aircraft-satellite HECEANICBL PROPERTIES communication Aircraft engine production components and alloys A71-31055 mechanical properties evaluation for improved Design and characteristics of continuous wave, reliability of mass produced products microwave scanning-beam aircraft landing system 871-28944 operating at C band and superhigh frequencies Composite materials application to V/STOL [AD-718972] 871-24555 prop/rotors, determining material properties EICROHAVE PRAUSIIISSIOA parametric effect on frequencies and weight by Integrated flight test data system combining Southwell coefficients digital airborne data acquisition/recording [AHS PREPRINT 5541 A71-31106 system with telemetry/microwave link to METAL COATINGS computerized ground station metal coated superalloys evaluation for gas A71-30318 turbine engine components, including corrosion, IIILITARY AIR FACILITIES impact and fatigue tests Runway concrete pavement condition at Naval A71-29635 Station, Adak, Alaska METAL MATRIX COMPOSITES [ AD-7198893 U71-25604 Mechanical properties of composites consisting of MILITARY AIRCRAFT A1 matrix reinforced by boron fibers, Landing load estimation methods for preliminary considering high temperature creep, corrosion design weight prediction for military aircraft and thermal shock resistivity A71-28211 A71-30473 Optimization of military VTOL aircraft secondary METALS pouer systems, considering alternate power Tests to determine short-term creep of metals and source for aircraft hydraulics, pneumatic alloys nnder conditions of aerodynamic heating drives, etc with high velocity air flow [SAE PAPER 7104451 A71-28326 [ NASA-TT-F-136331 N71-25822 Military/commercial STOL transport design, Impedance measurements on modified broadband metal discussing performance, payload and equipment antenna for speech communication requirements with emphasis on production cost [ FOB-3-C-3602-611 N7 1-26 150 benefits METEOROLOGICAL IUSTRUHEUTS [SAE PAPER 7104681 A71-28336 Self contained lightweight airborne data Commercial vs military design criteria for STOL acquisition system for atmospheric and transport aircraft, noting landing and takeoff meteorological research, using analog recorder distances and noise levels and telemetry system [SAE PAPER 7104651 A71-30536 A71-30311 Army aircraft automatic inspection and maintenance IETEOROLOGICAL PARAMETERS monitoring system, considering feasibility, Description of method for determining visibility technology approach and effectiveness in earth atmosphere [AIAA PAPER 71-6493 A71-30726 [ AD-719502 1 N71-24375 Multimission strategic aircraft installation METEOROLOGICAL RADAR effects testing in propulsion and aerodynamic Eeteorological radar for detection of wind tunnels, yielding flowfield definition, thunderstorms, hail, and turbulence hazardous to inlet internal performance, drag, forebody shape aviation noting echo interpretation and radar and orientation transmission [AIAA PAPER 71-7591 A71-30792 [ Wn0-264-TP-148] N71-24394 Flightworthy 25-foot diameter proprotor wind METEOROLOGY tunnel test, considering civil and military need Single anemometer wind measurement required for for VTOL transportation aircraft landing, comparing data from different [AHS PREPRINT 5011 871-31077 sampling periods Procedures for evaluating effectiveness of self A71-30395 propelled and portable ground servicing units METBAUE for Army aircraft Performance prediction of methane-fueled [AD-7191021 871-24459 supersonic transports over range of cruise IIILITARY AVIATIOU speeds up to Each 4 Military aviation greases for subsonic commercial [ NASA-TE-X-22811 N71-25384 airplane lubricants, discussing economic and Fuel tests to determine feasibility of gelled technical benefits based on service experience methane for use in jet engine and testing [ NASA-CR-72876 1 N71-25772 [SAE PAPER 7104111 871-28304 MICROBIOLOGY Army rotorcraft performance data, discussing Microbiological contamination of jet aircraft fuel hovering and forward flight performance out of tanks in tropical regions. considering ground and level flight power requirements and maintenance drag and compressibility effects [ SAE PAPER 7104381 A71-28320 [AHS PREPRINT 5001 A71-31076 IICROORGANISMS MILITARY HELICOPTERS Electrical and physical nature of microbial Soviet nil V-12 heavy lift helicopter for civil membranes implicated in aircraft fuel quantity and military missions, noting turbine engines, probe malfunction rotor configuration, cargo hold and navigation [SAE PAPER 7104391 A71-28321 system IIICROWAVE ANTEUNAS A71-30420 Flush mounted aeronautical waveguide antennas with Weapons delivery computer for attack helicopters, dielectric plug for 5GHz operation using planar distributed function generator for A71-31043 general closed form instantaneous solution Low carrier power aircraft antenna module for capability airborne UHF communications system, considering [AHS PREPRINT 531 1 A71-31092 range/field strength measurements Aerodynamic configu,ations and characteristics of 871-31046 USSR military helicopters Aircraft phased arrays for L-band ATC satellite [AD-7195851 N71-25133 system application, alleviating problems of IIILITABY TECEUOLOGY power budget and vulnerability to multipath and EAC malfunction detection, analysis and recording interference system applications in commercial airlines. A71-31054 emDhasizins real time response for maintenance L band aircraft antenna array consisting of function circularly polarized elements and static [SAE PAPER 7104251 871-28311 electronic steering circuits for synchronous Procedures for service test evaluations of Army satellites radio links aircraft automatic navigation systems A-38 SUBJECT INDEX NOSES (FOREBODIES) [ AD-7190961 871-243 6 9 [ AD-719096 ] N71-24369 IINIATURE ELECTRONIC EQUIPMENT NAVIGATION INSTRUBENTS Niniature transducers design and fabrication for High speed airborne scanning navigational radar fluctuating pressnre measurements in jet engine antenna with matched patterns, using offset horn testing, noting frequency response and power fed relector and polarization modes for improved dissipation visual display A71-30324 A71-31036 IINIATURIZATION UICKEL ALLOYS Niniature aerodynamic turbulence gage using Alnminide coatings for nickel-base snperalloy axisymmetric lifting body sensor developed for high temperature jet engine A71-28158 components MINIHUM DRAG [ NASA-CR-72863 3 N71-25454 Ninimnm drag wing-fuselage combination for NIGHT supersonic speeds and prescribed lifting force, Night rescue terminal navigation, considering longitudinal moment and volume, using method of design, development and tests of Limited Night successive approximations Recovery System for HH-53 helicopter A71-29182 [AHS PREPRINT 5341 A71-31095 MIRAGE 3 AIRCRAFT NIGBT VISION Extreme turbulence measurement during low level Cheyenne attack helicopter weapons system, flights of Mirage A3-76 fighter aircraft, discussing night vision capability, armament, determining true gust velocities and power fire control and navigation equipment spectral energy distributions integration 871-29756 [AHS PREPRINT 5301 A71-31091 MISSILE CONTROL UIOBIUU ALLOYS Control, navigation and guidance review, Silicide coated Nb alloys for gas turbine engine. considering application of earth reference components operating at temperatures above 2000 coordinates for aircraft, missiles and F spacecraft [SAE PAPER 7104601 A71-28334 A71-30710 NITRIC OXIDE UIXIUG LENGTH PLOH TEEORY Chemical kinetic calculation of nitric oxide High entrainment constant area multiple nozzle formation in spark ignition automobile engines ejectors with two mixing tube lengths for and gas turbine combustors boundary layer control, estimating performance A71-30454 with analytical model NOISE INTENSITY [ASBE PAPER 71-FE-341 A71-29469 Aircraft noise on and near airports and factors IODULATION affecting its intensity Sensing and communications technologies for short A71-29304 wayside headways, considering applicable NOISE PROPAGATIOU equipment for personal rapid transit systems, Combustion generated aerodynamic noise, modulation, coding and data transmission considering sound radiation from open turbulent techniques flames, spectral content, power output and A71-30337 origin UOIENTS OF INERTIA [AIAA PAPER 71-7353 A71-30780 Roll moment of inertia to static margin ratio BOISE REDUCTIOU effect on yaw of repose angle magnitude - Aircraft propulsion system testing, stressing ballistic match of projectiles noise reduction and inlet-engine exhaust system 871-29890 compatibility UOTIVATION [SAE PAPER 7104501 A71-28328 Air transport and travel expansion rate, Operations research minimum cost model of aircraft discussing motivations and cost noise abatement in airport communities A71-30159 [AIAA PAPER 71-5251 A71-29551 IULTIPHASE FLOH Noise attenuation prediction in absorbing ducts Turbulence level effects on mixing of three plane adaptable to bypass jet engines, using Morse parallel slipstreams with equal velocities and theory temperature from smoke visualization A71-30522 A71-28962 Tip turbine driven lift fan noise reduction tests, considering design parameters effects [AIAA PAPER 71-7431 A71-30784 N Acoustic liner design for propellant combustion NACELLES instability and jet aircraft noise suppression, Airframe installation effects on underwing nacelle discussing cross flow and oscillatory pressure nozzle performance, using calibrated engines and effects load cells on F-106 for measurements [AIAA PAPER 71-7571 871-30791 [AIAA PAPER 71-681 3 A71-30745 SST sonic boom minimization, discussiuq cross- NASA PROGRAMS country flight Authorization hearings on NASA space flight A71-30820 program - Part 4, 1972 NOISE SPECTRA N71-25196 Complex noise emission spectra from superposition UAVIGA4IOU AIDS of continuous component and peaks, calculating Optimum functional integration and performance level separations due to perfectly reflecting reguirements of navigation aids and ATC in plane terminal area A71-30523 [SAE PAPER 7104561 A71-28333 NONDESTRUCTIVE TES4S Area navigation system based on radio aids by Nondestructive testing of aircraft structures airborne receivers and sensors for aircraft using thulium and iridium gamma sources movement improvement, noting advantages of pilot [ JAERI-BEMO-4 163] N71-24849 displays Application of photochromic coatings to provide [SAE PAPER 7104571 A71-30533 nondestructive inspection for aerospace Control, navigation and guidance review, materials and structures considering application of earth reference [ AD-7202391 N71-26383 coordinates for aircraft, missiles and BORTH ATLANTIC TREATY ORGANIZATION (NATO) spacecraft Consideration by NATO of transonic wind tunnel A71-30710 requirements to support evolution of SK-5 air cushion vehicles evaluation including aeronautical and aerospace systems during next search/rescue, aids to navigation, law decade enforcement, safety logistics and oil pollution [ AGARD-AB-35-71] N71-25073 [AHS PREPRINT 5721 A71-31113 UOSES (POREBODIES) Procedures for service test evaluations of Army Conical body liftlarag ratio increase by wedge aircraft automatic navigation systems shaped nose, noting applications to space A-39 NOZZLE FLOW SUBJECT INDEX vehicles entering atmosphere above escape [ AD-7 19 854 ] 871-25053 velocity OPTICAL HEASUREIENT A71-29183 optical measurement of sprays mean droplet size, NOZZLE FLOR assessing operating variables effect on Pressure distribution and drag prediction over air-blast atomizer characteristics slender axisymmetric fuselages and afterbodies ~71-28756 and exhaust nozzles at transonic Mach numbers Photoelectric, bolometric and photographic [AIAA PAPER 71-7201 871-30771 recording assembly for measurement of light BOZZLE THRUST COEFFICIENTS pressure and aerodynamic forces on complex shape Isolated axisymmetric jet engine exhaust nozzles body in free molecular flow thrust and drag predictions in sub-, trans- and A71-29155 supersonic flight regimes OPTICAL PROPERTIES [AIAA PAPER 71-7191 871-30770 Aircraft mounted infrared detectors for remote NUCLEAR PROPELLED AIRCRAFT measurements of optical clond properties Air breathing nuclear propulsion, considering N71-25260 reactor safety in air cushion vehicles and OPTIHIZATION aircraft Optimization of military VTOL aircraft secondary A71-29930 power systems, considering alternate power Studying aircraft accidents to determine impact source for aircraft hydraulics, pneumatic angle and speed criteria for designing nuclear drives, etc airplane fission product containment vessel [ SAE PAPER 7104451 A71-28326 [ NASA-TM-X-2245 ] N71-25411 Optimal penetration effect on peripheral gas flow NUCLEAR PROPULSION temperature field at outlet of turbine Air breathing nuclear propulsion, considering combustion chamber with circular flame tubes reactor safety in air cushion vehicles and A71-28971 aircraft Ring thickness optimal distribution for minimum A71-29930 wave drag in supersonic flow at zero angle of Potential feasibility of safe, practical, and attack for given planform, using Ritz method at economical air breathing nuclear propulsion lower Mach numbers system for aircraft and air cushion vehicles A7l-29222 [NASA-TM-X-678371 N71-25524 Design interface requirements for optimal aircraft Characteristics and cost analysis of nnclear engine conaition monitoring system, using powered air cushion vehicles for oceanic parameter, vibration, oil, borescope and commercial operations radiography analysis [ NASA-TM-X-22931 N71-25783 [SAE PAPER 7104471 871-30531 NUCLEAR REACTOES ORIFICES Design point characteristics of 15-80 kUe nuclear Automated orifice drilling optimal treatment reactor Brayton cycle power system routines, including proper timing and adequate [NBSA-TM-X-67811] 171-24689 total depth allowance Predicted performance of 15-80 kUe reactor Brayton 871-28941 power system over range of operating conditions OXIDATION [ NASA-TM-X-678333 N71-24690 Hypersonic flight load bearing refractory alloy control surface protective coatings, emphasizing oxidation screening tests 0 871-29646 OB-6 HELICOPTER Rotor stability derivatives determination from instrumented OH-6A prototype helicopter wind P tunnel tests, comparing data with analytical P-I-N JUNCTIONS results obtained by digital computing technique Microstrip p-i-n diode controlled L band digital [AHS PREPRINT 5431 A71-31100 phase shifter for aircraft-satellite OKLAHOMA communication Oklahoma and Malaysia thunderstorms comparison A71-31055 based on weather reconnaissance aircraft PANEL FLUTTER measurements, considering turbulence patches Supersonic flutter analysis of clamped skew panels A71-29752 with in-plane forces by Galerkin method, using OBEGA UAVIGATION SISTEI two dimensional static approximation for Long range hyperbolic navigation in U.S., aerodynamic loading discussing loran and Omega systems 871-30607 A71-30711 Structural and inertial nonlinearities influence ONBOARD EQUIPUENT on flat or curved panel flutter Onboard aircraft refractometer design, operation A71-30825 and effectiveness Application of research in panel flutter and A71-28250 boundary layer thickness to space shuttle Onboard area navigation systems in ATC N71-24660 environment, discussing route structure and Nonlinear pauel flutter analyses by perturbation flight instruments and harmonic balance methods [SAE PAPER 7104551 A71-28332 [NASA-CR-1119071 N71-25362 Satellite aided aircraft collision avoidance PARACHUTE DESCENT system effective for large number of aircraft Development of mathematical model for opening [ NASA-CASE-ERC-10090] N71-24948 behavior of parachutes noting drag and velocity OPERATIONS EESEARCH as functions of time Operations research minimum cost model of aircraft [ AD-7196981 N71-24433 noise abatement in airport communities PARACEUTES [AIAA PAPER 71-5251 A71-29551 Brief history of parachute development including OPTICAL DATA PROCESSING devices and methods for canopy deployment Holographic techniques. optical data processing [ AD-7194801 N71-24351 and laser properties for aerospace Development of mathematical model for opening instrumentation behavior of parachutes noting drag and velocity 871-30329 as functions of time OPTICAL DEUSITI [ AD-7196981 N71-24433 Visible exhaust smoke trails from aircraft jet PASSENGEE AIRCRAFT engines, measuring optical density by Fuselage influence on total aircraft drag in photographic photometry subsonic passenger aircraft, considering high [SAE PAPER 7104281 A71-28314 aspect radio cylindrical fuselages OPTICAL EQUIPIEUT A71-30821 Development and characteristics of scanning PAVEHENTS systems for thermal viewers and infrared Airport pavement design principles, considering detectors for airborne operation imposed stresses at flight operation areas, A-40 SUBJECT IBDEX PITCE (INCLIUATION) runways, taxiways. apron and waiting position PBBSOUBBL DEVELOPMENT overrun areas, shoulders and strips Proceedings of conference to train personnel in A71-29311 conducting aircraft noise certification tests Runway concrete pavement condition at Naval [ ERC-TE-300-SUPPL- 1 ] N71-26303 Station, Adak, Alaska Familiarization of Federal Aviation Administration [ AD-7198891 171-25604 personnel in acoustic measurement techniques and PAYLOADS procedures involved in noise certification of Optimization of payload for space shuttle by aircraft reducing structural loading and weight [ HBC-TR-300 ] N71-26304 871-24664 PEBTUEBATION TEEOEY PEBPOEMANCE Nonlinear panel flutter analyses by perturbation Minimizing drag and increasing performance of and harmonic balance methods optimum shapes at hypersonic flight [NASA-CR-111907] N71-25362 N71-24704 PEASE SHIFT CIECUITS PEBFOEIANCE PREDICTIOU Bicrostrip p-i-n diode controlled L band digital Data correlation and effectiveness prediction from phase shifter for aircraft-satellite film cooling injection geometries, considering communication finitely thick slot lip and boundary layers A71-31055 A71-28751 PEASED ARRAYS German monograph on game theory and planning High speed electronic phase and frequency scanned techniques for aircraft evaluation linear, static fed and monopulse arrays element A71-28880 and angular error analysis Acoustic linings for attenuation of fan generated A7 1-3 1049 noise in turbofan engines, considering Aircraft phased arrays for L-band ATC satellite interaction between analytical lining system application, alleviating problems of performance prediction and flow duct testing power budget and vulnerability to multipath and [AIAA PAPER 71-7311 A71-30778 interference Development of mathematical model for opening A71-31054 behavior of parachutes noting drag and velocity PEOTOCBROMISI as functions of time Application of photochromic coatings to provide [ AD-7196983 N71-24433 nondestructive inspection for aerospace Predicted performance of 15-80 kWe reactor Brayton materials and structures power system over range of operating conditions [AD-7202391 N71-26383 [ NASA-TB-X-67833 ] N71-24690 PBOTOGRAPEIC PILI Performance prediction of methane-fueled Visual flight simulation devices, considering high supersonic transports over range of cruise resolution photogrphic films and digital speeds up to Nach 4 memories [ NASA-TB-X-2281] N71-25384 A71-29483 PEEFOBHAHCE TESTS PEYSICAL PROPERTIES CF6 turbofan engine development, discussing Electrical and physical nature of microbial performance and endurance tests and design membranes implicated in aircraft fuel quantity changes for reliable low cost operation probe malfunction [SAE PAPER 7104211 A71-28308 [ SAE PAPER 7104391 A71-28321 Airline engine performance testing from 0: -ator Soviet book on experimental aerodynamics covering perspective, using automated test cell data wind tunnels. shock tubes, liquid and gas acguisition system physical properties, flow parameter measurement [SAE PAPER 7104511 A71-28329 equipment, etc Measurement errors in testing single stage air 871-29524 driven axial flow compressors and turbines PILOT PEBPOBEAUCE A71-28582 Automatic landing systems independent monitor for Wind tunnel tests of geometrically compatible 1-1011 aircraft, providing pilot confidence airfoils for variable chord sailplane under reduced visibilities A71-29257 [SAE PAPER 7104431 A71-28324 High entrainment constant area multiple nozzle Commercial aircraft piloting in atmospheric ejectors with two mixing tube lengths for turbulence, discussing aircraft characteristics, boundary layer control, estimating performance instrumentation, flying procedures, pilot with analytical model training and kinesthetic cues [ ASME PAPER 71-FE-34 3 A71-29469 A71-29782 Axial flow turbines comparative performance tests Controlled aircraft motion under strict kinematic under steady and pulse flow conditions for constraints in terms of simple subsystems, turbocharger application noting pilots role in Newmark theory A71-29819 A71-31024 Airframe installation effects on underwing nacelle comparison' of pilot performance using center nozzle performance, using calibrated engines and stick, dual side stick, and single side stick load cells on F-106 for measurements configuration [AIAA PAPER 71-6811 A71-30745 [AD-720846] N71-25846 Bultimission strategic aircraft installation Flight evaluations using variable stability effects testing in propulsion and aerodynamic aircraft to determine effects of turbulence wind tunnels, yielding flowfield definition, induced aerodynamic disturbances and lateral inlet internal performance, drag, forebody shape directional dynamics on pilot performance and orientation [ NASA-CR-17181 N71-26170 [AIAA PAPER 71-7591 A71-30792 PILOT TBAIUING SK-5 air cushion vehicles evaluation including DC 10 flight crew individualized ground training search/rescue, aids to navigation, law program, emphasizing hands-on equipment and ' enforcement, safety logistics and oil pollution instruction hardware [AKS PREPRINT 5721 871-31113 [ SAE PAPER 7104721 A71-30538 Procedures for service test evaluations of Army PITCH (INCLINATIOtI) aircraft automatic navigation systems Aircraft flight characteristics dependence on I AD-7190961 N71-24369 angle of attack, roll and pitch Dynamic tests of helicopter components A71-29043 871-24388 Propeller vortex theory, calculating vortex Hovering performance tests of jet-flapped rotors streets pitch distributions and wake and comparison of predicted and actual results Configuration [ BAL-TR-2111 N71-25396 871-30443 PEBIPEEBAL JET PLOW Handling qualities and control sensitivity of high Optimal penetration effect on peripheral gas flow performance helicopters, considering pitch and .temperature field at outlet of turbine collective control combustion chamber with circular flame tubes [AHS PREPRINT 5421 A71-31099 A71-28971 A-41 PITCEIBG IOIEBTS SUBJECT IBDEI PITCEIBG IOIEBTS sound radiation and pressure fields inside Oscillatory pitching moment derivatives vibrating turbomachine blades, nsing measurement on delta wings in incompressible miniaturized nicroptones and compact capacitive flow detectors [ARC-R/I-3628-PT-1-4] N71-24569 A71-30517 Measurements of oscillatory pitching moments on Pressure distribution and drag prediction over round leading edged delta wing in incompressible slender axisymmetric fuselages and afterbodies flow noting vortex flow development and exhanst nozzles at transonic EIach numbers N71-24570 [AIAA PAPER 71-7201 A71-30771 Measurement of oscillatory pitching moment Retreating blade stall experiments on model derivatives on sharp-edged delta wing at vortex helicopter rotor, considering series of pressure breakdown angle of attack distribution and boundary layer events N71-24572 [AHS PREPRINT 5211 A71-31087 Expressions for relating pressure field to total Low speed wind tnnnel test of four ft diameter aerodynamic thrust and steady pitching and circular plate model to determine surface static rollinq moments experienced by helicopter rotor pressure distributions for jet decay N71-26583 characteristics of cross flow PITTIBG [ AD-7202321 N71-26516 Artificial corrosion pits effect on fatigue Expressions for relating pressure field to total durability of smooth samples and aircraft aerodynamic thrust and steady pitching and duraluminum skin elements rolling etoments experienced by helicopter rotor A71-27819 N71-26583 PLATE THEORY PRESSURE EFFECTS Soviet papers on three dimensional structures Incident sonic boom shock wave reflection factors covering strength and stability of componnd off smooth surface, discussing pressure rise and curvature shells, bodies of revolution and flight near threshold Mach number multilayer plates A71-30610 871-30888 PRESSURE IEASUREIEBTS PLATES (STRUCTURAL IEIBERS) Miniature transdncers design and fabrication for Simply supported normal mode plate time response fluctuating pressure measurements in jet engine to traveling wave at oblique incidence, nsing testing, noting frequency response and power numerical analysis dissipation A71-300 68 A71-30324 PLEUUI CHAMBERS Pluctnating pressure measurements in jet engine Supersonic stagqered gutter colander combustion testing, using miniature transducers with system for plenum chamber burning on high bypass calibration and data acquisition equipnent Pegasus turbofan engine of Harrier VTOL A71-30325 aircraft, noting performance improvement PRESSUBE OSCILLATIOBS 871-28743 Fan-produced sound pressnre flnctuation in very PLUGGIBG low speed subsonic vind tunnel test stream, Plug-in relay hazards and minimization for noting resulting anemometer calibration errors aircraft flight safety applications A71-30526 871-28841 Turbopropulsion systems thrust augmentor PORTABLE EQUIPMENT combnstion instability, discussing physical Low cost go/no-go portable aircraft engine tester causes due to various pressure oscillation modes connected to engine mounted sensors [AIAA PAPER 71-6971 871-30756 871-30327 Turbojet and turbofan augmentors combnstion Procedures for evaluating effectiveness of self instability, discussing pressure oscillations propelled and portable ground servicing units elimination by screech liner and flameholder for Army aircraft design [ AD-719102 3 N71-24459 [AIAA PAPER 71-6981 A71-30757 POSITION (LOCATIOB) Transonic wind tunnel investigation of flow Locating neutral layer and critical curvature characteristics and pressure fluctuation of radius in aircraft components waffle panels space shuttle launch and reentry configurations under elastoplastic bending N71-24663 A71-28940 PHESSUNE SEBSOBS POSITION EHBOHS Cam profile selection for adjnstment in computing- Combined inertial and instrument landing aircraft resolving unit of aneroid sensors of altimeters naviqation systems with reduced cross runway A71-28938 position and velocity errors, using optimal High altitude balloons pressure-altitude linear estimation transducer assembly, discussing electronic A71-30606 circuitry. calibration and temperature and POWEH SPECTRA vibration effects Extreme turbulence measurement during low level 871-30070 flights of Nirage A3-76 fighter aircraft, Altimeter-airspeed and Mach number pressure determining true gust velocities and power transducer vith diaphragm free of temperature spectral energy distributiond and vibration effects A71-29756 A71-30322 POWER THABSIISSIOB Miniature transducers design and fabrication for Helicopter power transmission failure modes, fluctuating pressure measurements in jet engine presenting field experiences correlation uith testing, noting frequency response and power conventional design stress analysis and bench dissipation test data A71-30324 [SAE PAPER 7104541 A71-28331 Fluctuating pressure measurements in jet engine Pouered landing gear wheel system requirements for testing, using miniature transducers with parking and taxiing of commercial jet transport calibration and data acquisition equipment airplanes A71-30325 [SAE PAPER 7104461 A71-30530 Pressnre sensor network for measuring liquid Strain gage torquemeter as primary power dynamic response in flight including fuel tank indicating instrument in helicopter transmission acceleration, liquid slosh amplitude, and fuel systems, providing advantages for helicopter depth monitoring designer and operator [ NASA-CASE-XLA-05541] 871-26387 [AHS PREPRINT 5631 871-31110 PRESSURIZED CABIBS PRESSURE DISTHIBUTIOB Fluidic cabin pressure automatic control systems Air inlet for simulation of shock wave separated for military and civil aircraft, discussing flow in supersonic diffusers, deriving pressure design, operation and performance variation profile along free boundary A71-30308 A71-29175 PROBES HF rake probes with high temperature integrated A-42 SUBJECT INDEX RADAR CORNER REFLECTORS sensor for inflight aircraft engine intake air performance and endurance tests and design flow distortion measurements changes for reliable low cost operation A71-30321 [SAE PAPER 7104211 A71-28308 PRODUCT DEVELOPMENT Aircraft propulsion system testing, stressing Olrmpus 593 pure iet twin shaft ensine development noise reduction and inlet-engine exhaust system program foi concorde, discussing -engine compatibility evolution, design considerations and flight [SAE PAPER 7104501 871-28328 development Thrust measurement of aircraft propulsion systems. [SAE PAPER 7104221 A71-28309 considering hydranlic piston device, edge Commercial aircraft powerplant development, clearance, oil quantity and calibration discussing engine and components test programs A71-29860 and techniques V/STOL propulsion units lift ratings based on [SAE PAPER 7104493 A71-28327 aircraft system reqairements PRODUCTION ENGINEERING [SAE PAPER 7104711 A71-30537 Complex structural aircraft components Airframe installation effects on nnderwing nacelle manufacture, nsing group technology principle nozzle performance, using calibrated engines and based on subdivision of parts classes load cells on F-106 for measurements A71-30267 [AIAA PAPER 71-6811 A71-30745 PROJECT MANAGEMENT Multimission strategic aircraft installation Costs-reliability relationships in helicopter effects testing in propulsion and aerodynamic development testing and demonstration. wind tunnels, yielding flowfield definition, emphasizing decision making in program inlet internal performance, drag, forebody shape management and orientation [SAE PAPER 7104521 A71-28330 [AIAA PAPER 71-7591 871-30792 Criteria for converting aeronautical project Aconstic measurements on prop-fan model propulsion operational targets into actual requirements and system - Vol. 2, appendices technical specifications. emphasizing cost [NASA-CB-111842-2] N71-257 84 effectiveness Acoustic measurements on prop-fan model propulsion A71-30824 system PROJECTILES [ NASA-CR-111842-13 N71-25785 Roll moment of inertia to static margin ratio Wind tunnel tests to determine Each 2.5 effect on yaw of repose angle magnitude in performance of bicone inlet with internal ballistic match of projectiles focused compression and 40-percent internal A71-29890 contraction PRoPaGaTxoN MODES [ NASA-TM-X-22941 N71-25872 Simply supported normal mode plate time response PROTECTIVE COATINGS to traveling wave at oblique incidence, using Silicide coated Nb alloys for gas turbine engine numerical analysis components operating at temperatures above 2000 A71-30068 F PROPELLANT COEBUSTION [SAE PAPER 7104603 A71-28334 Acoustic liner design for propellant combustion Materials and processing methods for rain erosion instability and jet aircraft noise suppression, resistant ceramic coated plastic structures for discussing cross flow and oscillatory pressure supersonic aircraft, considering fiberglass effects reinforced polyimide radomes with alumina [AIAA PAPER 71-7571 A71-30791 coating PROPELLANT SPRAYS A71-29645 Gas turbine engine combustion chamber start-up and Hypersonic flight load bearing refractory alloy burning performance, considering air injection control surface protective coatings, emphasizing and propellant atomization oxidation screening tests A71-28968 871-29646 Gas turbine engine startup igniter with modified Application of photochromic coatings to provide propellant atomizer enhanced by air injection nondestructive inspection for aerospace A71-28969 materials and structures PROPELLER FANS [ AD-7202391 N71-26383 Prop-fan propulsion system for V/STOL short haul PULSE CODE MODULATION transport aircraft, discussing performance, Concorde SST flight test equipment installation noise and weight characteristics with PCU recordins and visual instruments [SAE PAPER 7104701 A71-28338 A71-30055 Aconstic measurements on prop-fan model propulsion PULSED LASERS system - Vol. 2, appendices Airborne equipment for CAT detection ahead of [ NASA-CR-111842-2 ] N71-25784 aircraft, considering pulsed Doppler laser and Acoustic measurements on prop-fan model propulsion IR detectors system A71-29765 [ NA SA-CR- 11 1842-1 3 N71-25785 PROPELLER SLIPSTREAMS Propeller vortex theory, calculating vortex streets pitch distributions and wake RADAR ANTENNAS configuration High speed airborne scanning navigational radar 1171-30443 antenna with matched patterns, using offset horn PROPULSION SYSTEM COBFIGURATIOBS fed relector and polarization modes for improved Prop-fan propulsion system for V/STOL short haul visual display transport aircraft, discussing performance, 871-31036 noise and weight characteristics Structural design, mechanical stability and [SAE PAPER 7104701 A71-28338 aircraft compatibility for airborne side-lookipg Propulsion, guidance and stability of ground radar antennas, using end fed slotted waveguide effect vehicle with perimetric Coanda fluid arrays boundary A71-31041 A71-29308 RADAR BEACONS Wind tnnnel force test program design for jet Radarscope net for target azimuth and distance and aircraft configurations, including propulsion for direct altitude readout through beacon system simulation nnmerics A 7 1 - 30 6 0 5 871-28886 VTOL turboshaft engine powered propulsion system RADAR CORNER REFLECTORS development, detailing design requirements, Multiple planar Luneberg lens circular array for program planning, component research and system airborne electronically scanned X band narrow integration beam antenna mounted under aircraft.nose or [AHS PREPRINT 5621 871-31109 fuselage PROPULSION STSTEM PEEFOREANCE A71-31038 CF% turbofan engine development, discnssing A-43 RADAR DETECTION SOBJECT INDEX &IADAR DETECTION RAIL TRANSPORTATION Meteorological radar for detection of Integrated short-haul interurban transportation thunderstorms, hail, and turbulence hazardous to system, considering combination of conventional aviation noting echo interpretation and radar jet aircraft, STOL aircraft and high-speed transmission ground transportation [ HMO-264-TP-1481 N71-24394 [AIAA PAPER 71-508) A71-29550 RADAR NAVIGATION Aviation and surface transportatation safety for Air navigation techniques history, considering 1970 with related accident investigations and radio. radar, loran Doppler and inertial recommendations navigation [ AR-4 ] N71-24925 A71-30712 Investigation of aerodynhmic forces imposed on RADARSCOPES vehicles proposed for operation in improved Radarscope net for target azimuth and distance and urban transportation system for direct altitude readout through beacon N71-26129 numerics RAIN A71-28886 Precipitation detector and mechanism for stopping ATC radar display systems mapping techniques using and restarting machinery at initiation and vectors and optical projections cessation of rain A71-30014 [NASA-CASE-XLA-2619] n7i-26334 RADIATION DETECTORS RANDOH PROCESSES Sound radiation and pressure fields inside Random process theory method for estimating vibrating turbomachine blades, using response of flexible airplanes to atmospheric miniaturized microphones and compact capacitive turbulence detectors N71-24708 871-30517 RAPID TEASSIT SPSTEUS RADIATION DISTRIBUTION Sensing and communications technologies for short Jet aircraft sound spectrum on ground and in air, wayside headways, considering applicable comparing calculation with experiment equipment for personal rapid transit systems, A71-30524 modulation, coding and data transmission RADIATION PRESSURE techniques Photoelectric, bolometric and photographic A71-30337 recording assembly for measurement of light RAREFIED GAS DPNAUICS pressure and aerodynamic forces on complex shape Beat transfer on spheres and sharp cones in body in free molecular flow rarefied hypersonic gas flow at zero angles of A71-29155 attack in wind tunnel vacuum RADIO ANTENNAS 1171-29176 Airborne blade antenna tunable for 26-100 MA2 by REACTION KINETICS individual bands, using hinary related inductors Chemical kinetic calculation of nitric oxide switched by miniature high vacuum relays formation in spark ignition automobile engines 871-31044 and gas turbine combustors Light aircraft notch antenna for efficient A71-30454 radiation at HF hand lower end and minimal Modular concept mathematical model for combustion interference with aircraft structure and pollution formation processes in jet engine A71-31053 combustors, including turbulent mixing and RADIO COHIUNICATION reaction kinetics ATS 1 and 3 satellite VBP transponders for ships [AIAA PAPER 71-7141 A71-30766 and aircraft location, communication and remote REACTOR CORES sensing, discussing performance test results Studying aircraft accidents to determine impact A71-30898 angle and speed criteria for designing nuclear Helicopter aerial design problems, considering airplane fission product containment vessel antenna multiplicity use of nonmetallic [ NASA-TM-X-22451 871-25411 structures and complexity of airborne radio REACTOR SAFETY systems Air breathing nuclear propulsion, considering A71-31048 reactor safety in air cushion vehicles and RADIO FREQUENCY INTERFERENCE aircraft Interference prediction model for evaluating A71-29930 expected interactions between avionics equipment REAL GASES on aircraft Elliptical cones at large angle of attack, [ AD-71 89971 N71-24357 calculating three-component real gas properties RADIO NAVIGATION effects on aerodynamic characteristics Area navigation system based on radio aids by A71-29191 airborne receivers and sensors for aircraft REAL TIME OPERATION movement improvement, noting advantages of pilot HAC malfunction detection, analysis and recording displays system applications in commercial airlines, [SAE PAPER 7104573 A71-30533 emphasizing real time response for maintenance Air navigation techniques history. considering function radio, radar, loran Doppler and inertial [SAE PAPER 7104253 A71-28311 navisation RECORDING INSTROHENTS A71-307 12 Photoelectric, bolometric and photographic RADIO TRACKING recording assembly for measurement of light ATS 1 and 3 satellite VHF transponders for ships pressure and aerodynamic forces on complex shape and aircraft location, coamnnication and remote body in free molecular flow sensinq.-. discussins_- Performance test results A71-29155 A71-30898 Concorde SST flight test equipment installation RAWHE IATERIALS with PCM recording and visual instruments Materials and processing methods for rain erosion am-30055 resistant ceramic coated plastic structures for EECTANGOLAR PLAUFORHS supersonic aircraft, considering fiberglass Numerical evaluation of downwash integral for wing reinforced polyimide radomes with.alumina loading of lifting rectangular planform coatinq [NPL-IA-90] N71-24483 A71-29645 RECTANGULAR HINGS RADOIES Gust transfer functions relating lift and moments Materials and processing methods for rain erosion to upwash in single sinusoidal wave for large resistant ceramic coated plastic structures for aspect ratio rectangular wings in turbulent supersonic aircraft, considering fiberglass incompressible flow reinforced polyimide radomes with alumina A71-30604 coating REDUBDBdT CUMPOUENTS A71-29645 Third Chance flight control system, discussing aircraft control capability with backup SUBJECT INDEX ROTARY RINGS hydraulic system after loss of dual main at large Reynolds numbers hydraulic systems due to combat damage A71-29204 871-29382 Friction factor for low Reynolds number turbulent REEBTRY TEAJECTORIES flow in large aspect ratio rectangular ducts, Spacecraft optimal atmospheric reentry trajectory comparing Blasius and Prandtl relations for minimum flight distance, investigating angle [ASME PAPER 71-FE-A] ~71-2wa of attack control with allowance for load Supersonic mass flux probe description, discussing constraints inlet geometry, angle of attack and Reynolds aod A71-29229 Each numbers effects on performance REENTRY VEEICLES A71-29925 Transonic wind tunnel investigation of flow Reynolds number simulation requirements for characteristics and pressure fluctuation of subsonic wind tunnel tests of space shuttle space shuttle launch and reentry configurations configurations N71-24663 N71-26065 REFEREFlCE ATHOSPEERES REEOELECTRICAL SIIULATION Aircraft barometric altimeter errors caused by sonic boom induced indoor acoustical waves, using atmospheric temperature deviations from electrical analog International Standard Atmosphere A71-30200 A71-30323 Heavy lift helicopter fliqht control system RBFRACTOIETERS design, emphasizing fly by wire electrical Onboard aircraft refractometer design, operation analog and effectiveness [AHS PREPRINT 5031 871-31079 871-28250 RIGID ROTOR EELICOPTERS REPRACTOEY HETAL ALLOYS Retreating blade stall experiments on model Hypersonic flight load bearing refractory alloy helicopter rotor, considering series of pressure control surface protective coatings, emphasizing distribution and boundary layer events oxidation screening tests [AHS PREPRINT 5211 871-31087 A71-29 646 Electromechanical control system synthesis for REGULATIONS compound hingeless rotor helicopter, using root Book on air law and civil air policy covering locus method with transfer functions from international regulation, air traffic market, airframe motion linear model passenger and cargo services, etc [AHS PREPRINT 5361 A71-31096 A71-29938 AH-56A compound helicopter rigid rotor stability SAE/DOT conference on aircraft and environments and handling qualities, using flight, whirl covering noise pollution, airport noise. sonic tower and wind tunnel tests booms, regulatory/legal aspects and air [AHS PREPRINT 5741 A71-31115 pollution RIGID ROTORS [AIAA PAPER 71-7293 871-30776 Stiffened horizontal stoppable hingeless rotor BEINFORCED PLASTICS conversion from helicopter to airplane flight Materials and processing methods for rain erosion speeds resistant ceramic coated plastic structures for [AHS PREPRINT 5021 A71-31078 supersonic aircraft, considering fiberglass Forward flight performance of coaxial rigid rotor reinforced polyimide radomes Kith alumina in NASA wind tunnel, compating to aerodynamic coating stability with conventional rotors A71-29645 [AHS PREPRINT 5241 A71-31090 REINFORCING FIBERS ROADS Filamentary composite reinforced metal aircraft Analysis of adequacy of access routes to Dulles structures, considering boron/epoxy in International Airport and need for additional combination with aluminum facilities to accommodate future expansion A71-28168 [ PB-1940943 N71-26301 Mechanical properties of composites consisting of ROLL A1 matrix reinforced by boron fibers, Aircraft flight characteristics dependence on considering high temperature creep, corrosion angle of attack, roll and pitch and thermal shock resistivity A71-29043 A71-30473 Roll moment of inertia to static margin ratio REMOTE SENSORS effect on yaw of repose angle magnitude in Aircraft mounted infrared detectors for remote ballistic match of projectiles measurements of optical cloud properties 871-29890 N71-25260 ROLLING IOIEUTS RESCUE OPERATIONS Expressions for relating pressure field to total Night rescue terminal navigation, corsidering aerodynamic thrust and steady pitching and design, development and tests of Limited Night rolling moments experienced by helicopter rotor Recovery System for 88-53 helicopter 871-26583 [AHS PREPRIBT 5341 A7 1-31 0 9 5 ROTARY GYROSCOPES SIC-5 air cushion vehicles evaluation including Helicopter gyro displacement measurements at search/rescue, aids to navigation, law differing flying conditions enforcement, safety logistics and oil pollution [ FOA-2-C-2356-49-/72/] N71-26567 [BAS PREPRINT 5721 A7 1- 31 113 ROTARY STABILITY Test procedures to evaluate aircraft borne Helicopter rotor system vibratory and mechanical equipment for use in crash rescue operations stability characteristics, investigating [ AD-7205631 N71-26195 anisotropically mounted flexible swash plate and 3ESIDUAL STRESS blade out of track effects Helicopter component surface finish smoothness and [AHS PREPRINT 5111 A71-31082 residual stress requirements. using abrasive AH-56A compound helicopter rigid rotor stability' qrinding belt machines with gear link mechanisms and handling qualities, using flight, whirl 871-28943 tower and wind tunnel tests 1ESISTAICE HEATING [AHS PREPRINT 5741 8'1-31115 Hypervelocity blowdown nitrogen wind tunnel with ROTARY UIUG AIRCRAFT graphite resistance heater noting nozzles, Army rotorcraft performance data, discussin9 diffuser, and calibration hovering and forward flight performance out of [IC-AEE0-71-01 ] N71-24675 ground and level flight power requirements and RESOU AUT VIBRATIOP drag and compressibility effects Eechanical support system role in determination of [AHS PREPRINT 5001 A71-31076 aeroelastic stability of leeward cylinder ROTARY PINGS immersed in wake using undamped flutter theory Structure and shape of vortex wake associated with A71-31021 oblique flow past multiblade hinged rotor, using REYNQLDS BUBBER cavitation method Asymptotic limiting viscous flow pattern and drag A71-29217 on flat plate with stationary separation zones A-45 ROTATING BODIES SUBJECT INDEX Helicopter rotor vortex system and induced Advancing Blade concept helicopter lifting roqor velocity field for various angles of attack, development, discussing full scale analysis, fliqht conditions and unit loads, using smoke design. fabrication and wind tunnel tests visualization technique [AHS PREPRINT 5041 A71-i ,080 871-29235 Rotor blade stall induced helicopter control Noise production during aerodynamic tests on loads, combining unsteady aerodynamics with helicopter rotor in wind tunnel aeroelastic rotor analysis A71-30519 [AHS PREPRINT 5131 A71-3 1084 Stiffened horizontal stoppable hingeless rotor Retreating blade stall experiments on model conversion from helicopter to airplane flight helicopter rotor, considering series of pres-ure speeds distribution and boundary layer events [AHS PREPRINT 5021 A71-31078 [ABS PREPRINT 521 1 A7 1-3 1087 Helicopter rotor blade airload by applying lifting Integral spar inspection system for making CH-46 surface solution rotor blade fail-safe [AHS PREPRINT 5101 A71-31081 [ AHS PREPRINT 551 3 A71-31103 Helicopter rotor system vibratory and mechanical Size effects on large rotor systems design, stability characteristics, investigating considering weight, blade loading, tip speeq. anisotropically mounted flexible swash plate and etc blade out of track effects [AHS PREPRINT 5523 A71-41104 [AHS PREPRINT 5111 A71-31082 BUNHAI COBDITIONS Helicopter fuselage vertical and in-plane main Airport pavement design principles, cousideriqg rotor head vibratory forces isolation with imposed stresses at flight operation areas, hydropneumatic servoceutered system at runways, taxisays, apron and waiting positign transmission/airframe interface overrun areas, shoulders and strips [AHS PREPRINT 5141 A7 1- 3 1085 A7l-29311 Helicopter rotor stall characteristics, Uneven runway taxiing vibration effects on investigating blade flexibility, unsteady supersonic transport aircraft, comparing aerodynamics and variable inflow effects calculation with measurement [ AHS PREPRINT 5201 A71-31086 A71-30305 Flow field velocity distribution at rotating wing Runway concrete pavement condition at Naval devices tip vortices Station, Adak, Alaska [AHS PREPRINT 5221 871-31088 [ AD-7198891 871-45604 Wake model and computer program to compute BUNHAYS geometries, flows and velocity influence Roissy-en-France airpiort, describing construction, coefficients for helicopter blade load passenger handliug,'terminal facilities, traffic calculations volume and runway system [AHS PREPRINT 5231 A71-31089 A71-'-9309 Rotor stability derivatives determination from Melbourneflullamarine airport, describing instrumented OH-6A prototype helicopter wind facilities, capacity, road system, cargo anb tunnel tests, comparing data with analytical passenger handling areas and runway layout results obtained by digital computing technique 871-13310 [AHS PREPRINT 5431 A71-31100 Fail-safe helicopter rotor control des.lqu, discussing damage tolerant components, redundant s system, failure waruing and maintenance SAFETY DEVICES [ AHS PREPRINT 550 ] B71-31102 Concorde power plant fire protection system, Size effects on large rotor systems design, describing prototype engine bay overheat considering weight, blade loading, tip speed, detection system and additional UV optical fire etc detection system [AHS PREPRINT 5521 871-31 104 A71-30300 Optimal turbofan engine and reaction drive rotor SAFETY FACTORS combinations for helicopter design Plug-in relay hazards and minimization for [AHS PREPRINT 5613 A7 1-31 108 aircraft flight safety applications High performance UH-1 compound helicopter high B71-28841 speed flight research, considering rotor loads, SALTS stability, control and flying qualities Airport jet fuel delivery system salt driers for [AHS PREPRINT 5701 A71-31111 reducing water content below saturation. Fatigue life of helicopter rotary wings under lengthening filter life and improving downstream vibrational stresses system Components performance N71-24386 [SAE PAPER 710440] A71-28322 Rotary wing structural stability of Dornier high SATELLITE BEWORKS temperature gas jet helicopter Aircraft phased arrays for I-baud ATC satelli+e ~71-24387 system application, alleviating problems of Hoverinq performance tests of jet-flapped rotors power budget and vulnerability to multipath snd and comparison of predicted and actual results interference [ NAL-TR-2113 N71-25396 A71-;rl054 Expressions for relating pressdre field to total SATELLITE TRACKING aerodynamic thrust and steady pitching and Satellite aided aircraft collision avoidance rolling moments experienced by helicopter rotor system effective for large number of aircrart N71-26583 [ NASA-CASE-ERC-10090 3 N71-24948 ROTATING BODIES SATELLITE THANSHISSION Metal temperatures in rotating cooled gas turbine ATS 1 and 3 satellite VHF transponders for ships blades, discussing coolant flow aerodynamics and aircraft location, communication and cenote A71-28748 sensing, discussing performance test results ROTATING DISKS A71-30898 Axisymmetrical three component flow equations for Performance and cost design tradeoff between HF incompressible viscous fluid in cylinder with and synchronous meteorological satellite data rotating disk collection systems, considering platform 871-30855 transmitting power and SNR ROTOR AERODYNAIIICS 871-30900 Mathematical models for lifting rotor aerodynamic SCALE EFFECT calculations, noting wake configurations Size effects on large rotor systems design, [ DLR-MITT-70-191 N71-24489 considering weight, blade loading, tip speed, ROTOR BLADES etc Incompressible fluid motion in laminar boundary CARS PREPRINT 5521 A71-31104 layer on blade rotating uniformly about axis SCALE MODELS perpendicular to uinq span Buffet response of straight wing and delta wing A7 1-3021 8 model of space shuttle launch configuration 871-2 4 662 A-46 SUBJECT IUDEX SEORT TAKEOFF AIRCRAFT Acoustic measurements on prop-fan model propulsion SHOCK WAVES system - Vol. 2, appendices Air inlet for simulation of shock wave separated [NASA-CR-111842-2] N71-25784 flow in supersonic diffusers, deriving pressure Acoustic measurements on DroD-fan.~ model DroDulsion-~ variation profile along free boundary system 871-29175 [NASA-CR-111842-1] N7 1-25785 Incident sonic boom shock vave reflection factors Remolds number simulation requirements for off smooth surface, discussing pressnre rise and subsonic wind tunnel tests of space shuttle flight near threshold Mach number configurations A71-30610 N71-26065 Hypersonic flow pattern past windward side of Static tests of augmentor-wing flap system for delta wing with supersonic leading edges, modified C-8A jet STOL research airplane using joining potential and vortex regions behind 0.7 scale model shock wave [ NASA-CR-l14315] 871-26416 A71-30874 SELP BAUEUVERING UNITS SHORT EAUL AIRCRAFT Procedures for evaluating effectiveness of self Prop-fan propulsion system for V/STOL short haul propelled and portable ground servicing units transport aircraft, discussing performance, for Army aircraft noise and weight characteristics [ AD-7 19102 3 871-24459 [SAE PAPER 7104701 A71-28338 SEESORS Dassault Nercnre short range twin jet aircraft Miniature aerodynamic turbuleqce gage nsing capable of using powerful engine axisymmetric lifting body sensor A71-29276 A71-28158 Aircraft capabilities in intraurban transportation SEPARATED FLOW for Detroit metropolitan area, considering Three dimensional steady separated liquid and gas vehicle desian._. fleet size. cost and terminal flows past low aspect ratio bodies, deriving location similarity laws for reduction to two dimensional [AIAA PAPER 71-5041 A71-29548 problem Intearated short-haul interurban transportation A71-29169 system, considering combination of conventional Air inlet for simulation of shock wave separated jet aircraft, STOL aircraft and high-speed flow in supersonic diffusers, deriving pressure gronnd transportation variation profile along free boundary [AIAA PAPER 71-5081 871-29550 871-29175 SEORT TAKEOFF AIRCRAFT Asymptotic limiting viscous flow pattern and drag Vortex wakes behind STOL operations high lift on flat plate with stationary separation zones wings, discussing height above ground and at large Reynolds numbers various wind tunnel dimensions effects A71-29204 A71-28033 Separation control of two dimensional air flow STOL aircraft electric power variable frequency with turbulent boundary layer along circular generation and high voltage DC distribution with cylindrical wall by jets or suction secondary square wave AC distribution A7 1-29433 [SAE PAPER 7104441 A71-28325 SERVICE LIFE Nilitary/commercial STOL transport design, Structure service life and storage failure discussing performance, payload and equipment probability calculation with current load requirements with emphasis on production cost measurements and laboratory fatigue testing benefits A71-29231 [SAE PAPER 7104681 A71-28336 SERVOAEPLIFIERS STOL aircraft/engine integrated systems for medium Wind tunnel model trajectory simulation system distance air transportation, discussing tradeoff with closed loop control by digital computer, factors involving performance, noise, weight and describing instrumentation, system cost servoamplifiers and testing procednres [SAE PAPER 7104691 A71-28337 A71-30334 Integrated short-haul interurban transportation SEBVOIECRAUISIS system, considering combination of conventional Eelicopter fuselage vertical and in-plane main jet aircraft, STOL aircraft and high-speed rotor head vibratory forces isolation with ground transportation hydropneumatic servocentered system at [AIAA PAPER 71-5083 A71-29550 transmission/airframe interface TWO dimensional flow research on high lift [AaS PREPRINT 5141 871-31085 airfoils for STOL aircraft, nsinq vorticity SEARP LEADING EDGES distribution and wind tunnel wall blowing Aspect ratio effect on oscillatory pitching moment techniqnes derivatives of slender sharp-edged delta wing in A71-29910 incompressible flow civil aviation customer /operator, passenger and N71-24571 community/ needs, describing STOL and V/STOL Beasurement of oscillatory,pitching moment aircrafts derivatives on sharp-edged delta wing at vortex A71-30162 breakdown angle of attack VTOL and STOL aircraft comparative study covering 871-24572 site area, cost and noise and toxic gas SEELL STABILITY production soviet papers on three dimensional structures A71-30163 covering strength and stability of compound Air transport development trends, considering cnrvature shells, bodies of revolution and increasea speed and capacity, STOL aircraft, multilayer plates urban service, and European cooperation for A71-30888 manufacturing SHOCK BEATING A71-30302 Aerothermodynamic shock heating of space shuttle STOL vehicle and systems air transportation booster surface during atmospheric ascent expansion by reducing trip time, congestion, N71-26059 noise exposures and pollution for DOT, DOD and SHOCK TUBES NASA roles Soviet book on experimental aerodynamics covering [SAE PAPER 7104641 A71-30535 wind tunnels, shock tubes, liquid and gas Commercial vs military design criteria for STOL physical properties, flow parameter measurement transport aircraft, noting landing and takeoff equipment, etc distances and noise levels A71-29524 [SAE PAPER 7104651 am-30536 SHOCK TUUBELS Low wing loading STOL transport ride smoothing Nonograph on hypersonic shock tunnel supersonic using Boeing aircraft combustion research techniques covering test [ NASA-CR-111819 3 N71-24586 facilities, optical and electromagnetic flow Stability, control, and handling quality aeasurenent methods. etc characteristics of STOL and V/STOL airplanes A71-29578 N71-24702 a-47 SIDE-LOOKING RADAR SUBJECT INDEX Flight tests for controlling slope approach of SLOTS short takeoff aircraft Direct lift control system having flaps yith slots [ ARC-CP-11381 N71-25050 adjacent to their leading edge and particularly Rind tunnel tests to determine low-speed adapted for lightueight aircraft aerodynamic characteristics of large-scale STOL [ NASA-CASE-LAR-10249-11 N71-26110 transport model with augmented jet flap SMOKE TRAILS [ NASA-TE-X- 620 173 N71-26183 Visible exhaust smoke trails from aircraft jet Static tests of augmentor-wing flap system for engines, measuring optical density by modified C-8A jet STOL research airplane using photographic photometry 0.7 scale model [SAE PAPER 7104283 A71-28314 f NASA-CR- 1143 15 3 N71-26416 Kerosene type fuels for aircraft gas turbine SIDE-LOOKING RADAR engines, discussing combustion problems, smoke Structural design, mechanical stability and emission reduction and bacterial or fungal aircraft compatibility for airborne side-looking contamination radar antennas, using end fed slotted Waveguide A71-28754 arrays SONIC BOOMS A71-31041 Sonic boom induced indoor acoustical waves, using SIGUAL ENCODING electrical analog Sensing and communications technologies for short 871-30200 wayside headways, considering applicable Incident sonic boom shock wave reflection factors equipment for personal rapid transit systems, off smooth surface, discussing pressure rise and modulation, coding and data transmission flight near threshold Mach number techniques A71-30610 A71-30337 SST sonic boom minimization, discussing cross- SILICIDES country flight Silicide coated Nb alloys for gas turbine engine 871-30820 components operatinq at temperatures above 2000 SOUBD FIELDS P Cost efficient sound limit expenditures per [SAE PAPER 7104601 A71-28334 parameter unit in commercial transport aircraft SIMULATION design Performance of aircraft environmental control A71-28945 systems under simulated tactical condikions Sound fields of flying aircraft from noise [AD-719101 3 N71-24461 measurements, discussinq enqine operating SKIN (STRUCTURAL MEMBER) conditions, speed and attitude Artificial corrosion pits effect on fatigue 871-30521 durability of smooth samples and aircraft Jet aircraft sound spectrum on ground and in air, duraluminum skin elements comparing calculation with experiment A71-27819 A71-30524 SKIN FRICTION SOUND GENERATORS Skin friction drag and velocity profile Combination tone noise generation from turbofans measurements on flat plate in two phase circular with supersonic fan blade tip speed, determining pipe flow in subsonic wind tunnel for gas-solid sound power distrihution among engine rotation media, using photographic technique frequency harmonics [ASEE PAPER 71-PE-323 A71-29467 [ AIAA PAPER 71-7301 A71-30777 Turbulent skin friction and heat transfer Combustion generated aerodynamic noise. prediction on flat plates and wind t'unnel walls considering sound radiation from open turbulent at supersonic and hypersonic llach numbers, using flames, spectral content, power output and Van Driest theory origin A71-2986 8 [AIAA PAPER 71-7351 A71-30780 SLENDER BODIES SOUND INTENSITY Pressure distribution and drag prediction over Combination tone noise generation from turbofans slender axisymmetric fuselages and afterbodies with Supersonic fan blade tip speed, determining and exhaust nozzles at transonic Mach numbers sound power distribution among engine rotation [LIAA PAPER 71-7201 A71-30771 frequency harmonics SLENDER CONES [AIAA PAPER 71-7303 A71-30777 Slender cone boundary layer transition under angle SOUBD PRESSURE of attack at Iiach 21 with promoted leeward and Fan-produced sound pressure fluctuation in very fixed windward ray low speed subsonic wind tunnel test stream, 871-29887 noting resulting anemometer calibration errors SLEUDER WINGS A71-30526 Aspect ratio effect on oscillatory pitching moment Interior sound pressure measurements in C-SA derivatives of slender sharp-edged delta wing in aircraft incompressible flow [AD-7197463 N71-25060 N71-24571 Techniques and procedures for measuring effective SLIP FLOW perceived noise level during aircraft noise type Plow measurement of Nonweiler delta wing in certifications hypersonic slip flow [ HRC-TR-300-SUPPL-2 3 2171-26305 [ DLR-FB-70-461 N71-2450C SOUND WAVES SLIPSTREAMS sonic boom induced indoor acoustical waves, using Turbulence level effects on mixing of three plane electrical analog parallel slipstreams with equal velocities and A71-30200 temperature from smoke visualization Sound radiation and pressure fields inside 871-28962 vibrating tnrbomachine blades, using , Incompressible condncting fluid plane jet miniaturized microphones and compact capacitive expansion in homogeneous slipstream, deriving detectors partial differential equations for nonconduction A71 -305 17 approximation Hot jet aerodynamic parameters from emissions of A71-29610 electromagnetic and acoustic energies by crossed SLOT ANTENNAS beam IR probing Structural design, mechanical stability and A71-30520 aircraft compatibility for airborne side-looking SOUNDING ROCKETS radar antennas, using end fed slotted waveguide Scientific results from ESRO satellites and from arrays sounding rocket campaign including aeronautical A71-31041 fields, management planning, satellite Aerospace antenna design, calculating one- development, and telecommunication - 1969 report vavelength circular slot aperture radiation from 871-24447 circular cylindrical surface SPACE MISSIONS A71-31075 Authorization hearings on NASA space flight program - Part 4, 1972 A-48 SUBJECT IBDEX STATE VECTORS N71-25196 Viability of L band communication system oetween IPACE POWER UNIT REACTORS geostationary satellites and aircraft terminals Motor starting techniques for 2-15 kH Brayton [ NASA-TM-X-65508] N71-24913 space pover system SPACECRAFT COBFIGURATIOBS [ NASA-TM-X-678 191 N71-24691 Transonic wind tunnel investigation of flov PACE SRUTTLES characteristics and pressure fluctuation of I Space shuttle airbreathing piopulsion systems space shuttle launch and reentry Configurations requirements and design studies, considering N71-24663 cruise, landing, go-around and ferry Cost estimates, performance prediction, technology capabilities assessment, and configurations for space shuttle [AIAA PAPER 71-6621 A71-30731 871-26052 Conference on dynamics and aeroelasticity of space SPACECRAFT COBSTRUCTIOB MATERIALS shuttle Application of photochromic coatings to provide [ NASA-TN-X-22741 N71-24651 nondestructive inspection for aerospgcce Transonic flutter and buffeting for elastic wind materials and strnctures tunnel models of straight wing proposed for [AD-7202391 N71-26383 space shuttles SPACECRAFT CONTROL N71-24659 Spacecraft optimal atmospheric reentry trajectory Application of research in panel flntter and for minimum flight distance, investigating angle boundary layer thickness to space shuttle of attack control vith allowance for load N71-24660 constraints Parameters contributing to aeroelastic problems in A71-29229 thermal protection of space shuttle Control, navigation and guidance review, N71-24661 considering application of earth reference Buffet response of straight wing and delta wing coordinates for aircraft, missiles and model of space shuttle launch configuration spacecraft N71-24662 171-30710 Transonic wind tunnel investigation of flow SPACECRAFT INSTRUHEBTS characteristics and pressure fluctuation of Instrumentation in aerospace indnstry - space shuttle launch and reentry confignrations Conference. Las Vegas, May 1971 871-24663 A71-30309 Optimization of payload for space shuttle by Holographic techniques, optical data processing reducing structural loadinq and weight and laser properties for aerospace N71-24664 instrumentation Cost estimates, performance prediction, technology A71-30329 assessment, and configurations for space shuttle SPACECRAFT PERFORIABCE N71-26052 Analysis of aerodynamic forces on DL-4 lifting wind tunnel simulations of flow fields and entry vehicle and comparison with theoretical aerothermodynamics of space shuttle orbiters methods N71-26053 [ NASA-TI-X- 19943 N71-26354 Comparison of space shuttle aerodynamic heating SPACECRAFT PROPULSION analyses for metallic heat shield and surface Space shuttle airbreathing propulsion systems insnlation concepts requirements and design studies, considering N71-26054 cruise, landing, go-around and ferry Finite difference method for calculating inviscid capabilities flov field around supersonic/hypersonic space [AIAA PAPER 71-6621 A71-30731 shuttle SPACECRAFT REElTRY N71-26056 Spacecraft optimal atmospheric reentry trajectory Flov visualization, thermocouple measurements, and for minimum flight distance, investigating angle analyses of shock interference heating effects of attack control with allowance for load on straight ving space shuttle model constraints N71-26057 A71-29229 Hypersonic shock/density ratio effects in SPECIFICATIONS aerothermodynamic heating of space shuttle Criteria for converting aeronautical project conf iguration operational targets into actual requirements and N71-26058 technical specifications, emphasizing cost Aerothermodynamic shock heating of space shuttle effectiveness booster surface during atmospheric ascent 871-30824 N71-26059 SPECTRAL ENERGT DISTRIBUTIOB Lee surface flow and aerodynamic heating on delta Extreme turbulence Beasurement during low level ving orbiter flights of Nirage 83-76 fighter aircraft, N71-26060 determining true gust velocities and power Aerodynamic characteristics of delta ving space spectraJ energy distributions shuttle configurations 871-29756 N71-26062 SPEED CONTROL Reynolds number simulation requirements for En route tnrbojet aircraft flight speed control, subsonic vind tunnel tests of space shuttle assessing impact on ATC procedures conf ignrations A 7 1- 2 8 8 8 4 N71-26065 STABILITY DERIVATIVES Hypersonic theoretical/experimental correlations Rotor stability derivatives determination from of aerodynamic characteristics for space shuttle instrumented OR-6A prototype helicopter wind design tunnel tests, comparing data with analytical N71-26066 results obtained by digital computing technique SPACECRAFT ANTEBBAS [ABS PREPRINT 5431 871-31 1bO Aerospace antenna design, calculating one- Effects of aeroelasticity on static longitudinal vavelength circular slot aperture radiation from aerodynamic derivatives circular cylindrical surface 1171-24707 A71-31075 STAGUATION PRESSURE SPACECRAFT COIIUBICATIOB Flov meter for measuring stagnation pressure in Microstrip p-i-n diode controlled I. baud digital boundary layer around high speed flight vehicle phase shifter for aircraft-satellite [NASA-CASE-XPR-02007] 871-24692 com m un ica t ion STA NDA BDS A71-31055 Airport certification and safety inspection Blade antenna linear array design for aircraft- procedures and minimum safety standards satellite communication, determining mutual [SAE PAPER 7104131 A71-28305 influences by array measurements in simulated STATE VECTORS electrical environment V/STOL aircraft flight path and attitude controls A7 1-31 062 in turbulence, discussing design based on state variable methods of control theory A-49 STATIC PRESSURE SUBJBCT IEDEX A71-29776 stratospheric Scorer paraaeter STATIC PRESSURE A71-29763 Low speed wind tunnel test of four ft diameter Stratospheric turbulence correlation to mesoscale circular plate model to determine surface static horizontal temperature gradient at altitudes pressure distributions for jet decay flown by SST from Coldscan program characteristics of cross flow A71-29767 [AD-7202321 N71-26516 Clear air turbulence in stratosphere and effects STATIC TESTS on weather formation, atmospheric physics, and Yak 40 aircraft flight test program, discussing supersonic flights airuorthiness requirements, static structural, [ JPRS-531331 N71-25746 vibration and wind tunnel tests STRATUS CLOUDS A71-29971 Aircraft hazards due to frequent low clona Effects of aeroelasticity on static longitudinal occnrrences at Kenya airport, forecasting aerodynamic derivatjves weather with statistical analysis and 871-24707 radiosounding Static tests of augmentor-wing flap system for A71-29106 modified C-8A jet STOL research airplane using STRESS AHALYSIS 0.7 scale model Eelicopter power transmission failnre modes, [ NAS A-CR- 11437 5 ] N71-26416 presenting field experiences correlation with STATISTICAL AEALTSIS conventional design stress analysis and bench Atmospheric turbulence statistical models test data assessment for aircraft design and operation, [SAE PAPER 7104541 A77-28331 considering CAT and thunderstorm turbulence data Fatigue and fracture mechanics of airframes and 871-29751 materials including structural design and stress STATOR BLADES analysis techniques Test description and results for high Uach number [AD-7197561 N71-25092 transonic fan stages to determine range and STRESS IEASUBEMEBT distortion tolerance for various rotor tip Static strain measurements on Ti specimen casing treatment confignrations subjected to different conductive heating rates, [NASA-CR-82&62] N77-25460 testing various gages Tabulations of blade element and circumferential B71-29833 distortion flow data in tests of high nach STRUCTURAL AEALTSIS number transonic fan stages with various rotor Optimization of payload for space shuttle by tip casing treatment configurations reducing structural loading and weight [ NASA-CR-82867 ] N71-25461 871-24664 STEADY PLOW Nonlinear panel flutter analyses by perturbation Three dimensional steady separated liquid and gas and harmonic balance methods flows past low aspect ratio bodies, deriving [ NASA-CR- 11 7 907 ] N71-25362 similarity laws for reduction to two dimensional STRUCTURAL DESIGE problem Materials and structural design development by A71-29169 high velocity impact testing due to transport STEEBABLE AETEBBAS and subsonic military aircraft susceptibility to L band aircraft antenna array consisting of bird collision damage circularly polarized elements and static A71-29642 electronic steering circuits for synchronous Aircraft structural design requirements based on satellites radio links statistical analysis of air turbulence intensity 871-31074 and gust loads records from large number of STOCHASTIC PROCESSES research flights Development and characteristics of electronic 871-29784 equipment for digital processing of stochastic 1-1011 Tristar antenna arrangement test results, signals for military aircraft avionics systems considering weight, aerodynamic and structural [ AD-7 19822 ] N77-24954 design requirements STORAGE BATTERIES A71-31060 Soviet book on airplane and helicopter electrical Fatigue and fracture mechanics of airframes and power supply systems covering storage batteries, materials including structural design and stress DC generators, alternators, voltage regulators, analysis technigues current and frequency control, etc [ AD-7 197561 871-25092 A71-29525 STRUCTUBAL FAILURE .TORAGE STABILITY Structure service life and storage failure Test procedures to determine ability of aircraft probability calculation uith current load egnipment and armament to withstand storage and measurements and laboratory fatigue testing operate effectively in tropic environment A71-29231 [ AD-7205701 N71-26194 Structural fatigue in aircraft design, discussing STBAIB GAGE BALANCES twin engine transport tests, crack propagation Frequency response of five component strain gage rate, residual strength, etc oscillating balance for dynamic wind tunnel A71-29434 stability testing STRUCTURAL STABILITY 871-30333 Conference on fatigue life in helicopter STRAIB GAGES components Static strain measurements on Ti specimen [DLR-UITT-70-01] N71-24385 subjected to different conductive heating rates, Rotary wing structural stability of Dornier high testing various gages temuerature aas-- iet helicovter A71-29833 N71724387 Aircraft flight load measurements in high Evaluation of helicopter flight loading and temperature environment, determining optimal strnctural stability strain gage installation and calibration B71-24389 871-30681 Structural stability tests of helicopter Strain gage torquemeter as primary power components indicating instrument in helicopter transmission B71-24390 systems, providing advantages for helicopter STRUCTURAL VIBRATIOE designer and operator Automated modal data acquisition and processing [AHS PREPRINT 5631 871-31110 system /nODAPS/ for real-time modal vibration STRATOSPHERE testing of complex aerospace vehicle structures, Stratospheric air flow patterns and CAT describing features, capabilities and measurements onboard aircraft over and downwind utilization of Yestern U.S. mountain terrain A71-30341 A77-29755 SUBSONIC AIBCRAPT Atmospheric models of partially trapped waves nilitary aviation greases for*subsonic commercial propagation in layer above tropopause with large airplane lubricants, discussing economic and A-50 SUBJECT INDEX SUPERSONIC UIBD TUNNELS technical benefits based on service experience SUPERSONIC DIFFUSERS and testing Air inlet for simulation of shock wave separated [SAE PAPER 7104111 A71-28304 flow in supersonic diffusers, deriving pressure Economic analysis of subsonic transport airplane variation profile along free boundary design. evaluation and operation 871-29175 [SAE PAPER 7104231 871-28310 SUPEESONIC FLIGHT Fuselage influence on total aircraft drag in Annular vaporizing combustion chamber with film subsonic passenger aircraft, considering high cooling, determining flame temperature under aspect radio cylindrical fuselages supersonic flight conditions A71-30821 A71-28749 SUBSONIC FLOW clear air turbulence in stratosphere and effects Heat transfer within resonant cavities at subsonic on weather formation, atmospheric physics, and and supersonic flow, discussing wind tunnels, supersonic flights test procedures and data reduction EJPRS-531333 N71-25746 [ASEE PAPER 71-FE-91 A71-29450 SUPERSONIC FLOU Pisa University Aeronautical Institnte activities ling thickness optimal distribntion for minimum /1960-1970/. considering supersonic and snbsonic wave drag in supersonic flow at zero angle of flow research, thin stiffened shells fatigne attack for given planform, using Ritz method at under compressive or tensile loads, etc lower Each numbers A71-30822 871-29222 SUBSONIC aInD Tunnms Heat transfer within resonant cavities at subsonic Skin friction drag and velocity profile and supersonic flow, discussing wind tunnels, measurements on flat plate in two phase circular test procedures and data reduction pipe flow in subsonic wind tunnel for gas-solid [ASEE PAPER 71-PE-91 A71-29450 media, nsing photographic technique Turbulent skin friction and heat transfer [ASEE PAPER 71-FE-321 A71-29467 prediction on flat plates and wind tunnel walls Fan-produced sound pressure fluctuation in very at supersonic and hypersonic Mach numbers, using low speed subsonic wind tunnel test stream, Van Driest theory noting resulting anemometer calibration errors A71-29868 1171-30526 Supersonic mass flux probe description, discussing SUPERCAVITATING FLOU inlet geometry, angle of attack and Reynolds and Snpercavitating flow past straight cascade with Hach numbers effects on performance arbitrary blade shapes, considering lift and A71-29925 drag coefficients. cavitation number, cavity Flowfield prodnction by fluid injection into shape and exit flow conditions supersonic crossflow, occurring with liquid/gas [ASEE PAPER 71-FE-61 A71-29448 jet control of vehicle with combustion ramjets SUPERCHARGERS [AIAA PAPER 71-7281 A71-30775 Axial flow turbines comparative performance tests Pisa University Aeronautical Institute activities under steady and pulse flow conditions for /1960-1970/. considering snpersonic and subsonic turbocharger application flow research, thin stiffened shells fatigne A71-29819 under compressive or tensile loads. etc SUPERCRITICAL moa A71-30822 Aerodynamic noise produced by supercritical jets, Finite difference method for calculating inviscid using high speed flash photography for schlieren flow field around supersonic/hypersonic space and shadowgraph studies shuttle A71-28767 871-26056 SUPERHIGH FREQUENCIES SUPERSONIC FLUTTER Enltiple planar Luneberg lens circular array for Supersonic flutter analysis of clamped skew panels airborne electronically scanned x band narrow with in-plane forces by Galerkin method, nsing beam antenna mounted under aircraft nose or two dimensional static approximation for fuselage aerodynamic loading A71-31038 871-30607 SUPERSOUIC AIRCRAFT SUPERSONIC INLETS minimum drag wing-fuselage combination for Supersonic inlet turbojet engine compatibility supersonic speeds and prescribed lifting force, tests in wind tunnels, using light panels and longitudinal moment and volnme. using method of Summation Device analysis snccessive approximations A71-28032 A71-29182 Engine snrge pressure transients in mixed- Energy state approximation and supersonic aircraft compression supersonic inlet, describing scale minimum fuel fixed range trajectory wind tunnel model simulation and measurement optimization, noting not convex velocity set techniques A71-30609 [AIAA PAPER 71-6711 A71-30735 Investigation of stability and controllability Uind tunnel tests to determine Each 2.5 parameters for supersonic aircraft nnder varying performance of bicone inlet with internal aerodynamic load conditions focused compression and 40-percent internal [AD-719804 ] N71-25032 contraction Stability and controllability of supersonic swept [ NASA-TE-X-22941 N71-25872 wing aircraft SUPERSONIC TRANSPORTS [ AD-7198031 N71-25049 SST in relation to U.S. world leadership in air Supersonic aircra'ft lateral control eqwipment transportation, discussing federal funding needs [ AD-720740 ] N71-26538 for technological capability ensurance SUPERSOUIC COlBUSTION A71-29387 Supersonic staggered gutter colander combustion Stratospheric turbulence correlation to mesoscale system for plenum chamber burning on high bypass horizontal temperature gradient at altitudes , Pegasus turbofan engine of Harrier VTOL flown by SST from Coldscan program aircraft, noting performance improvement A71-29767 A71-28743 Uneven rnnway taxiing vibration effects on Monograph on hypersonic shock tnnnel supersonic supersonic transport aircraft, comparing combustion research techniques covering test calculation with measurement facilities, optical and electromagnetic flow A71-30305 measurement methods, etc SST sonic boom minimization, discussing cross- A71-29578 Gountry flight SllPERSOllIC COMPRESSORS 871-30820 Analytical model of compressor sensitivity to Performance prediction of methane-fueled transient and distorted transient flows, supersonic transports over range of cruise considerins inlet duct. compressor staaes and speeds up to Each 4 combustor up to turbine nozzles [ NASA-TE-X-'228 1 3 871-25384 [AIAA PAPER 71-6703 A71-30734 SUPERSOBIC HIND TUNNELS Ballistic wind tunnel for drag measurement on a-si SUPPORT INTERFERENCE SUBJECT INDEX models during free flight at supersonic speeds A71-31074 A71-2920 1 SYSTEMS ANALYSIS Time variant distortions in supersonic inlet on Bigh rotor advance ratio from multiblade general J-85-GE-13 turbojet engine from wind tunnel coordinates method in linear analysis of lifting test, considering instantaneous distortion rotor dynamic stability and gust ratio amplitudes and contours [AHS PREPRINT 5121 A71-31083 [AIAA PAPER 71-6671 A71-30733 SYSTEMS ENGINEERING Wind tunnel tests to determine Each 2.5 Onboard aircraft refractometer design, operation performance of bicone inlet with internal and effectiveness focused compression and 40-percent internal A71-28250 contraction Engine condition monitoring systems, discussing [ NASA-TN-X-2294] N71-25872 engineering design requirements uith respect to SUPPORT INTERFERENCE accessibility, accuracy, economics, Nechanical support system role in determination of effectiveness, reliability and maintainability aeroelastic stability of leeward cylinder [AIAA PAPER 71-6521 A 71- 3 0728 immersed in wake using undamped flutter theory Performance and cost design tradeoff between HP 871-31021 and synchronous meteorological satellite data SURFACE FINISHING collection systems. considering platform Helicopter component surface finish smoothness and transmitting power and SNR residual stress requirements, using abrasive A71-30900 grinding belt machines with gear link mechanisms Heavy lift helicopter flight control system A71-28943 design, emphasizing fly by wire electrical SURFACE GEOMETRY analog Photoelectric, bolometric and photographic CARS PREPRINT 5031 871-31079 recording assembly for measurement of light Electromechanical control system synthesis for pressure and aerodynamic forces on complex shape compound hingeless rotor helicopter, using root body in free molecular flow locus method with transfer functions from A7 1-29 155 airframe motion linear model SURFACE ROUGHNESS EFFECTS [AHS PREPRINT 5361 A71-31096 Uneven runway taxiing vibration effects on Calculating and testing antiicing systems of supersonic transport aircraft, comparing aircraft and helicopters calculation with measurement [ AD-7 199221 N71-25622 A71-30305 SURFACE TEMPERATURE Lee surface flow and aerodynamic heating on delta T wing orbiter T TAIL SURFACES N71-26060 Aircraft with T tail configuration, examining Leeside aerodynamic heating of lifting reentry dynamic response to lateral gusts vehicle configurations A71-29786 N71-26061 Analysis of empennage loads and aeroelastic SUHPACE VEEICLES response of T-tail transport aircraft in Investigation of aerodynamic forces imposed on continuous atmospheric turbulence vehicles proposed for operation in improved N71-24996 urban transportation system TABLES (uPfA) 871-26129 Tabulations of blade element and circumferential Analysis of road traffic problems at Washington distortion flow data in tests of high Mach National Airport and recommendations to improve number transonic fan stages with various rotor airport access tip casing treatment configurations [ REPT-31 N71-26526 [ NASA-CR-828671 N71-25461 SURGES TAKEOFF Analytical model of compressor sensitivity to Aircraft accident at Miami. Florida involving transient and distorted transient flows, Republic of &cuador C-54D during climb following considering inlet duct, compressor stages and instrument takeoff combustor up to turbine nozzles I: NTSB-AAR-71-21 N71-26032 [AIAA PAPER 71-6701 A71-30734 TARGET ACQUISITION SWEPT UINGS Radarscope net for target azimuth and distance and Stability and controllability of supersonic swept for direct altitude readout through beacon wing aircraft numerics [AD-7198031 N71-25049 1171-28886 SPEPTBACK SIXGS TAXIING High lift and boundary layer separation behavior Uneven runway taxiing vibration effects on of sweptback wing airfoil profile noting snpersonic transport aircraft, comparing trailing and leading edge stall pattern calculation with measurement [ ARC-R/N-3648] N71-24488 A71-30305 Low-speed wind tunnel longitudinal stability tests Powered landing gear wheel system requirements for on sweptback wing model with blowing at leading parking and taxiing of commercial jet transport edge slats and trailing edge flaps for Buccaneer airplanes aircraft performance [SAE PAPER 7104461 A71-30530 [ARC-R/B-3655] N71-24565 TECHNOLOGY ASSESSIIEBT SUITCEIEG CIRCUITS Cost estinates, performance prediction, technology Interface IC circuits for driving high voltage assessment, and configurations for space shuttle transistor switches from low level logic inputs, 871-26052 noting avionics application TECHNOLOGY UTILIZATION A71-28910 Technical, sales/marketing and management -, SYMIIETRICAL BODIES Conference, Coronado, California, lay 1971 Minimizing drag and increasing performance of A71-28164 optimum shapes at hypersonic flight BAC malfunction detection, analysis and recording N71-24704 system applications in commercial airlines, SYECHROEOUS IETEOROLOGICAL SATELLITE emphasizing real time response for maintenance Performance and cost design tradeoff between HF function and synchronous meteorological satellite data [SAE PAPER 7104251 A71-28311 collection systems, considering platform TELECOMIUXICATIOX transmitting power and SNR Sensing and communications technologies for short A71-30900 wayside headways, consiaering applicable SYNCHRONOUS SATELLITES equipment for personal rapid transit systems, L band aircraft antenna array consisting of modulation, coding and data transmission circularly polarized elements and static techniques electronic steering circuits for synchronous A71-30337 satellites radio links A-52 SUBJECT INDEX THEBBAL IBSULATIOB~ Scientific results from ESRO satellites and from Roissy-en-France airport, describing construction, sounding rocket campaign including aeronautical passenger handling. terminal facilities, traffic fields, management planning, satellite volume and runway systeia development, and telecommunication - 1969 report A71-29309 N71-24447 Kelbourne/Tullamarine airport, describing Viability of L band communication system between facilities, capacity, road system, cargo and geostationary satellites and aircGaft terminals passenger handling areas and runway layout [NASA-TB-X-65508] N7 1-249 13 A71-29310 Tropospheric and ionospheric absorption at VHF for Frankfurt terminal baggage conveyor system, North Atlantic aeronautical satellite system describing passenger capacity and luggage [ NASA-T8-X-655077 N71-24914 handling equipment TELEMETRY A71-29312 Self contained lightweight airborne data Ultra Compact Airport Terminal, describing acquisition system for atmospheric and landside. terminal and airside elements meteorological research, using analog recorder A71-29313 and telemetry system Survey of civil airports to determine status of A71-30311 crash fire and rescue equipment available for Integrated flight test data system combining use following accidents involving scheduled or digital airborne data acquisition/recording local service air carrier aircraft system with telemetry/microwave link to N71-26466 cosputerized ground station Analysis of road traffic problems at Uashington A71-30318 National Airport and recommendations to improve Telemetering - IEEE Conference, Washington, D.C., airport access April 1971 [ BEPT-3 3 N71-26526 A71-30896 TEBHINAL GUIDANCE TEHPEEATUBE DISlJIIBUTIOB Night rescue terminal navigation, considering Gas turbine engine combustion chamber outlet, design, development and tests of Limited Night noting gas flow temperature field peripheral Recovery System for AH-53 helicopter nonuniformity [AHS PREPRINT 5341 A71-31095 A71-28972 TEST EQUIPHENT Conductive heat transfer effect on temperature Concorde SST flight test equipment installation distribution in vicinity of wing leading edge in with PCK recording and visual instruments hypersonic flight A71-30055 [ ARC-CP-11261 171-24446 Low cost go/no-go portable aircraft engine tester TEHPEEATUBE EFFECTS connected to engine mounted sensors Static strain measurements on Ti specimen A71-30327 subjected to different conductive heating rates, Automated modal data acquisition and processing testing various gages system /BODAPS/ for real-time modal vibration A71-29833 testing of complex aerospace vehicle structures, X-type hot-wire probe thermal turbulent wake describing features, capabilities and interference, discussing wind tunnel utilization investigation of uire distance effect on pitch 871-30341 angle sensitivity Design, development, and test of ground support A71-31022 equipment for analyzing aircraft equipment Design point characteristics of 15-80 kWe nuclear condition and performance reactor Brayton cycle power system [ AD-7196751 B71-24603 [NASA-TK-X.-67811] N71-24689 TEST FACILITIES Predicted performance of 15-80 kRe reactor Brayton Airline engine performance testing from operator power system over range of operating conditions perspective, using automated test cell data [NASA-TM-X-67833] 171-24690 acquisition system Notor starting techniques for 2-15 kH Brayton [SAE PAPER 7104511 A71-28329 space power system Terminal air traffic control facility for approach [NASA-TM-X-67819] N71-2469 1 systems tests TEMPEBATURE GRADIEUTS [ AD-719 1041 N71-24451 Stratospheric turbulence correlation to mesoscale Test description and results for high Each nuaber horizontal temperature gradient at altitudes transonic fan stages to determine range and flown by SST from Coldscau program distortion tolerance for various rotor tip A71-29767 casing treatment configurations TEHPEBATUBE HEASUBEHENT [ NASA-CR-828621 N71-25460 Metal temperatures in rotating cooled gas turbine Tabulations of blade element and circumferential blades, discussing coolant flow aerodynamics distortion flow data in tests of high aach 871-28748 number transonic fan stages with various rotor Gas temperature measurement in aircraft combustion tip cashg treatment configurations chambers, using calorimetric probe [ NASA-CR-82867 ] N71-25461 871-28757 Test procedures to determine ability of aircraft Temperature and radical concentration measurements equipment and armament to withstand storage and for high temperature flowing gas streams in rig operate effectively in tropic environment simulating conditions in ramjet combustion [AD-720570] N71-26194 chamber and nozzle Test procedures to evaluate aircraft borne 871-28758 equipment for use in crash rescue operations Aircraft instrumentation and data analysis for [ AD-7205631 N7 1- 26 195 clear air turbulence, including orthogonal Flow-duct test facility data on acoustic behavior components and temperature and wind of lined ducts and duct-lining materials for distributions turbojet engine applications A71-29753 [NASA-CR-111887] 171-26917 TENSILE TESTS TESTS Pisa University Aeronautical Institute activities Procedures for evaluating coapatibility of /1960-1970/. considering supersonic and subsonic aviation materiel with related equipment flow research, thin stiffened shells fatigue [AD-7191073 N71-24457 under compressive or tensile loads, etc THERMAL DIFFUSION A71-30822 Diffusion and thermal mechanism ignition theories, TERMINAL FACILITIES applying to altitude relighting of gas turbine Airport terminal building design and construction, engine combustors noting economy and expansibility corequirements 871-28745 [SAE PAPER 7104181 A71-28307 THERMAL INSULATION Optimum functional integration and performance Comparison of space shuttle aerodynamic heating requirements of navigation aids and ATC in analyses for metallic heat shield and surface *terminal area insulation concepts [SAE PAPER 7104561 A71-28333 N71-26054 A-53 TEERMAL PBOTECTIOU SUBJECT IUDEX THERMAL PROTECTION TILTED PROPELLERS Parameters contributing to aeroelastic problems in Flightworthy 25-foot diameter proprotor wind thermal protection of space shuttle tunnel test, considering civil and military need N71-24661 for VTOL transportation TEERMAL SEOCK [AHS PREPBIHT 5011 A71-31077 Beckanical properties of composites consisting of TILTIUG ROTORS A1 matrix reinforced by boron fibers. Flightworthy 25-fOOt diameter proprotor wind considering high temperature creep, corrosion tunnel test, considering civil and milit.ary need and thermal shock resistivity for VTOL transportation A71-30473 [AHS PREPRINT 5011 A71-31077 TEEBMAL STABILITY TIME DEPEUDEUCE Olympus 593 supersonic engine lubricants tests, Time dependent clearance changes effects on defining requirements in terms of bulk thermal aerodynamic characteristics of sectorially stability, resistance to hot bearing breakdown, grooved gas bearings, describing lift and drag oil mist coking, etc coefficients calculation A71-29826 A71-30227 TEERMOCEEMISTBY TIME OPTIMAL CONTROL Soviet book on aircraft materials science and Minimum time profiles for P-104 aircraft by treatment covering steel/cast iron processing, Balakrishnan epsilon technique, comparing metallography, heat/thermochemical conditioning, solutions with energy method surface protection and corrosion prevention A71-28831 A71-29529 Jet-supported VTOL aircraft fuel-time-optimal TEEBUODYNABIC EPPICIEUCY landing control, using mathematical model, Continuous combustion gas turbine with stepwise Pontryagin maximum principle and analog computer heat release, investigating ideal thermal solution efficiency cycle of gas overexpansion, cooling A71-29281 and compression VTOL aircraft minimum climb-to-cruise time A71-28583 transition optimal open loop and suboptimal THICKNESS RATIO closed loop control synthesis Wing thicknars optimal distribution for minimum A71-30799 wave drag j%supersonic flow at zero angle of TIME RESPONSE attack for given planform, using Ritz method at Simply supported normal mode plate time response lower Mach numbers to traveling wave at obliqne incidence, using A71-29222 numerical analysis TEIN WALLED SEELLS A71-30068 Pisa University Aeronautical Institute activities TIMIUG DEVICES /1960-1970/, considering supersonic and subsonic Brief history of parachute development including flow research, thin stiffened shells fatigue devices and methods for canopy deployment under compressive or tensile loads, etc [AD-7194801 N71-24351 A71-30822 TIP SPEED TBREE DIMEHSIOUAL PLOW Plow field velocity distribution at rotating wing Three dimensional steady separated liquid and gas devices tip vortices flows past low aspect ratio bodies, deriving [AHS PREPRINT 5221 A71-31088 similarity laws for reduction to two dimensional size effects on large rotor systems design, problem considering weight, blade loading, tip speed, A7 1-291 69 etc TEBUST [BAS PREPRINT 5521 A71-31104 Expressions for relating pressure field to total TITANIUM aerodynamic thrust and steady pitching and Static strain measurements on Ti specimen rolling moments experienced by helicopter rotor subjected to different conductive beating rates. N71-26583 testing various gages TEBUST AUGMENTATION A71-29833 Turbopropulsion systems thrust augmentor TOOLS combustion instability, discussing physical Evaluating adequacy of tool sets for aircraft causes due to various pressure oscillation modes maintenance [AIAA PAPER 71-6973 A71-30756 [ AD-7191 031 N71-24379 Turbojet and turbofan augmentors combustion TORQUEMETEES instability. discussing pressure oscillations strain gage torquemeter as primary power elimination by screech liner and flameholder indicating instrument in helicopter transmission design systems, providing advantages for helicopter [AIAA PAPER 71-6981 A71-30757 designer and operator Static tests of augmentor-wing flap system for [AHS PREPRINT 5631 1171-31 110 modified C-8A jet STOL research airplane using TOWIHG 0.7 scale model Nonlinear mathematical model for dynamical [NASA-CR-114315] N71-26416 behavior of extensible towing cable subjected to TERUST MEASUBEMEBT aerodynamic forces generated by uniform flow Thrust measurement of aircraft propulsion systems, field, discussing system stability considering hydraulic piston'device. edge A71-31026 clearance, oil quantity and calibration TEADEOPPS 871-29860 Performance and cost design tradeoff between HP THULIUM ISOTOPES and synchronous meteorological satellite data Nondestructive testing of aircraft structures collection systems, considering platform using thulium and iridium gamma sources transmitting power and SNR [ JAERI-MEMO-4163] N71-24849 A71;30900 THUBDEBSTOBBS TRAPPIC CONTROL Oklahoma and Malaysia thunderstorms comparison Analysis of road traffic problems at Washington based on weather reconnaissance aircraft National Airport and recommendations to improve measnrements, considering turbulence patches airport access A71-29752 [ REPT-3 3 N71-26526 Thunderstorm, CAT, weather and mountain uave TBAIUIUG DEVICES induced turbulence forecasting and analysis for DC 10 flight crew individualized ground training transport aircraft program, emphasizing hands-on equipment and A71-29764 instruction hardware Beteorological radar for detection of [SAE PAPER 7104721 A71-30538 thunderstorms, hail, and turbulence hazardous to TRAJECTORY AUALPSIS aviation noting echo interpretation and radar Quasi-stationary gliding trajectories of aircraft transmission in planetary atmosphere during constant control [ WMO-264-TP- 148 3 N71-24394 of attack and bank angles A71-29185 A-54 SUBJECT IUDEX TRANSPORT AIRCRAPT Rind tunnel model trajectory simulation system A71-30898 with closed loop control by digital computer, Evaluation of dual input transponder with upper describing instrumentation, system and lower aircraft antennas as resolution for servoamplifiers and testing procedures problems with air traffic control radar beacon A71-30334 system limitations TBAJECTORI CONTSOL [ FAA-NA-71-39] N71-24882 Propulsion, guidance and stability of ground TBAUSPORT AIRCRAFT effect vehicle with perimetric Coanda fluid Economic analysis of subsonic transport airplane boundary design, evaluation and operation A71-29308 [SAE PAPER 7104231 871-28310 TBAJECTORT OPTIMIZATIOU Transport aircraft all weather automatic landing Spacecraft optimal atmospheric reentry trajectory operation, examining guidance system and for minimum flight distance, investigating angle independent monitors of attack control with allowance for load [SAE PAPER 7104413 871-28323 constraints Military/commercial STOL transport design, A71-29229 discussing performance, payload and equipment Energy state approximation and supersonic aircraft requirements with emphasis on production cost minimum fuel fixed range trajectory benefits A71-28336 optimization, noting not convex velocity set [SAE PAPER 7104681 A71-30609 Cost efficient sound limit expenditures per TBAUSFEB FUUCTIOUS parameter unit in commercial transport aircraft Gust transfer functions relating lift and moments design to upwash in single sinusoidal vave for large A71-28945 aspect ratio rectangular wings in tnrbulent Commercial V/STOL and jet VTOL transport, incompressible flow discussing Do-31 test results, landing approach, A71-30604 air traffic control antomation and electronic . TBANSIEUT PRESSURES control Engine surge pressure transients in mixed- A71-29131 compression supersonic inlet, describing scale structural fatigue in aircraft design, discussing wind tunnel mo6el simulation and measurement twin engine transport tests, crack propagation techniques rate, residual strength, etc [AIAA PAPER 71-6711 A71-30735 A71-29434 TRAUSIEUT BESPOESE Atmospheric turbulence effect on turbine powered Analytical model of compressor sensitivity to transport aircraft, discussing gust transient and distorted transient flows, accelerations, avoidance, detection, forecasting considering inlet duct, compressor stages and and pilot control combustor up to turbine nozzles A71-29750 [ AIAA PAPER 71-6701 A71-30734 Thunderstorm, CAT, weather and mountain wave TBAUSISTOB CIRCUITS induced turbulence forecasting and analysis for Interface IC circuits for driving high voltage transport aircraft transistor switches from low level logic inputs, A71-29764 noting avionics application Jet transport aircraft stability and A71-28910 controllability under atmospheric turbulence TRAESITIOU FtOU conditions, discussing longitudinal acd lateral- Aerodynamic characteristics similarity and directional characteristics with particular variation in hypersonic flow transition region attention to unstable spiral mode from free molecular flow to solid medium A7l-29772 A7 1- 29 172 Jet transport aircraft design for safety under air TBAUSONIC COBPRESSORS turbulence conditions, considering cruise Test description and results for high Each number altitude limitations and pitch and g excursion transonic fan stages to determine range and reduction by special autopilot mode distortion tolerance for various rotor tip A71-29777 casing treatment configurations Normal accelerations experienced by transport [ NASA-CR-82862 1 871-25460 aircraft fleet from fatigue load meter data Tabulations of blade element and circumferential analysis, discussing counting rates seasonal distortion flow data in tests of high Each variations number transonic fan stages with various rotor A71-29788 tip casing treatment configurations Computer aided design program for civil transport [ NASA-CR-82 867 1 N71-25461 aircraft configuration, performance, propulsion, TBAUSOUIC FLOU weight and costs to meet given specifications Low thrust jet effect on base pressures on A71-30398 boat-tailed afterbodies in Each number 0.8-1.2 Transport aircraft JT9D high bypass ratio engine flow development, noting maintainability and A71-29889 stability improvements Pressure distribution and drag prediction over [ SAE PAPER 7104191 A71-30527 slender axisymmetric fuselages and afterbodies Powered landing gear wheel system requirements for and exhaust nozzles at transonic Nach numbers parking and taxiing of commercial jet transport [AIAA PAPER 71-7201 A71-30771 airplanes Vortical transonic gas flow over wing profile [SAE PAPER 7104461 A71-30530 N71-257 14 Commercial vs military design criteria for STOL TBAUSONIC FLUTTER transport aircraft, noting landing and takeoff Transonic flutter and buffeting for elastic wind distances and noise levels tunnel models of straiqht wing proposed for [SAE PAPER 7104651 871-30536 space shuttles Analysis of empennage loads and aeroelastic 871-24659 response of T-tail transport aircraft in TBAUSONIC UIUD TUUEELS continuous atmospheric turbulence Transonic wind tunnel investigation of flow N71-24996 characteristics and pressure flnctuation of Cumulative frequency distributions determined by space shuttle launch and reentry Configurations extreme value analysis used for fatique analysis N71-24663 and interpretation ef c.g. vertical acceleration Consideration by BAT0 of transonic wind tunnel and gust velocity measured on transport aircraft requirements to support evolution of [ AGARD-E-579-713 N71-25080 aeronautical and aerospace systems during next Plight evaluation of lateral handling, stability, decade control, and flying qualities of jet transport [ AGARD-AR-35-71] N7 1-25073 aircraft during up-and-away and approach flight TBAUSPOUDEBS in landing configuration ATS 1 and 3 satellite VAP transponders for ships [ NASA-TN-D-6339 3 871-25537 and aircraft location, communication and remote rind tunnel tests to determine low-speed sensing, discussing performance test results aerodynamic characteristics of large-scale STOL A-5S TBABSPOBTATION SUBJECT IBDEX transport model with augmented jet flap [SAE PAPER 7104213 871-28308 TNASA-TU-X-620171 N71-26183 Supersonic staggered gutter colander combustion TBABSPOBTATION system for plenum chamber burning on high bypass Analysis of adequacy of access routes to Dnlles Pegasns turbofan engine of Harrier VTOL International Airport and need for additional aircraft, noting performance improvement facilities to accommodate future expansion A71-28743 [ PB-1940941 N71-26301 Afterburning turbofan engine thrust calculation by TRAVELING WAVES gas generator method, using P-1118 for Simply supported normal mode plate time response comparison tests to traveling wave at oblique incidence, using [AIAA PAPER 71-6801 A71-30744 numerical analysis Turbojet and turbofan augmentors combustion 871-30068 instability. discussing pressure oscillationa TROPICAL REGIOBS elimination by screech liner and flameholder Nicrobiological contamination of jet aircraft fuel design tanks in tropical regions, considering [AIAA PAPER 71-6981 A71-30757 maintenance Combination tone noise generation from turbofans [SAE PAPER 7104381 A71-28320 with supersonic fan blade tip speed, determining Test procedures to determine ability of aircraft sound power distribution among engine rotation equipment and armament to withstand storage ana frequency harmonics operate effectively in tropic environment [AIAA PAPER 71-7301 A71-30777 [AD-7205701 N71-26194 Acoustic linings for attenuation of fan generated TROPOPAUSE noise in turbofan engines, considering Atmospheric models of partially trapped waves interaction between analytical lining propagation in layer above tropopause with large performance prediction and flow duct testing stratospheric Scorer parameter [AIAA PAPER 71-7311 A71-30778 A71-29763 Optimal turbofan engine and reaction drive rotor TROPOSPEEBE combinations for helicopter design Tropospheric and ionospheric absorption at VHP for [AHS PREPRINT 5611 A71-31108 North Atlantic aeronautical satellite system TURBOPANS [ BASA-TM-X-655071 N71-24914 Tip turbine driven lift fan noise reduction tests, TUBBIBE BLADE5 considering design parameters effects Aerofoil cascades with axial velocity change in [AIAA PAPER 71-7431 A71-30784 incompressible flow, determining turbine blade TUBBOGEBEBATOBS force dependence on circulation Soviet handbook of aircraft electrical equipment A71-28467 covering DC and turbine powered generators, Beta1 temperatures in rotating cooled gas turbine lubrication materials, electromagnetic blades, discussing coolant flow aerodynamics interference countermeasnres, etc A71-28748 871-29530 Aerodynamic forces produced in tnrbine stage by TURBOJET EBGIEES vane cascade of cascade series Supersonic inlet turbojet engine compatibility [NASA-TT-P-136311 N71-25998 tests in wind tunnels, using light panels and Analysis of first stage turbine stator vane and Summation Device analysis rotor blade cooling designs for application in A71-28032 highspeed aircraft RB 162 turbojet engine combustors for VTOL [ NASA-TM-X-17823 N71-26355 aircraft, achieving ignition by two pressure jet TURBIEE EBGIBES atomizers operative during starting cycle Turbine engine fuel control stability on CH-47C A71-28742 helicopter, using flight tests and lag damper Subsonic and supersonic turbojet aircraft engines simulation development, discussing design, operation, [AHS PREPRINT 5601 A71-31107 reliability, weight, fuel consumption and cost VTOL turboshaft engine powered propulsion system A71-29811 development, detailing design requirements, Absorbent materials for sound attenuation in program planning, component research and system tnrboreactor ducts. examining flow velocity, integration absorbent structure and cladding effects [AHS PREPRINT 5621 A71-31109 871-30518 Analysis of first stage turbine stator vane and Turbojet and turbofan augmentors combustion rotor blade cooling designs for application in instability, discussing pressure oscillations highspeed aircraft elimination by screech liner and flameholder [ NASA-TB-X-17821 N71-26355 design TUBBOCOIPRESSOBS [AIAA PAPER 71-6981 A71-30757 Beasurement errors in testing single stage air Gas-air mixture requirements for turbine and driven axial flow compressors and turbines injection burner combustion efficiencies A 7 1- 2 85 8 2 [ AD-7198341 N71-25359 lultistage axial flow compressors on digital Flow-duct test facility data on acoustic behavior computer, testing gas dynamic design in final of lined ducts and duct-lining materials for adjustment phase turbojet engine applications A71-28584 [NASA-CR-1118871 A7 1-2641 7 Monograph on potential flow interaction between TURBOIACRIBE BLADES blade rows in axial flow compressors covering Snpercavitating flow past straight cascade with mathematical model, numerical analysis and arbitrary blade shapes, considering lift and experiment drag coefficients, cavitation number, cavity A71-28883 shape and exit flow conditions Circumferential traversing probe technique for [ASUE PAPER 71-PE-61 A71-29448 intrastage analysis of axial flow compressors, Sound radiation and pressure fields inside ' considering mass flow averaging data reduction vibrating turbomachine blades, using technigue miniaturized microphones and compact capacitive [ASBE PAPER 71-PE-331 871-29468 detectors Axial flow turbines comparative p'erformance tests A71-30517 under steady and pulse flow conditions for TURBOPROP EEGIBES turbocharger application Reduction gearbox reliability problems from A7 1-29819 development and service experience with PT6A TURBOPAB AIRCRAFT turboprop engine Climbout and landing approach noise measurements [SAE PAPER 7104331 A71-28318 for three engine turbofan transport aircraft TURBOSEAPTS [ NAS A-TN-D-6 137 3 N71-24582 VTOL tnrboshaft engine powered propulsion system TUBBOPAB EBGIBES development, detailing design requirements, CP6 turbofan engine development. discussing program planning, component research and system performance and endurance tests and design integration changes for reliable low cost operation [ AES PREPBIBT 5621 A71-31109 A-56 SUBJECT IUDEX V/STOL AIRCRAFT TURBULENCE EFFECTS 871-29610 Turbulence level effects on mixing of three plane Two dimensional flow research on high lift parallel slipstreams with equal velocities and airfoils for STOL aircraft, using vorticity temperature from smoke visualization distribution and wind tunnel wall blowing ~71-28962 techniques Atmospheric turbulence effect on turbine powered A71-29910 transport aircraft, discussing gust TWO PHASE FLOW accelerations, avoidance, detection, forecasting Skin friction drag and velocity profile and pilot control measurements on flat plate in two phase circular A71-29750 pipe flow in subsonic wind tunnel for gas-solid Air turbulence primary and secondary effects on media. using photographic technique aircraft flight and avoidance criteria [ASME PAPER 71-FE-321 A71-29467 considerations 871-29768 Flight characteristics under atmospheric u turbulence conditions, analyzing analog trace U.S.S.R. records of airspeed, normal acceleration, Aerodynamic configurations and characteristics of altitude, air temperatnre, control surface and USSR military helicopters flight attitude parameters [AD-719585] N71-25133 A71-29771 UH-1 EELICOPTER Automatic aircraft landing system modification for High performance 118-1 compound helicopter high improvement of response to air turbulence speed flight research, considering rotor loads, effects stability, control and flying qualities A71-29773 [AES PREPRINT 5701 A71-31111 TURBULEUCE HETERS ULTRAEIGB FREQUENCIES Miniature aerodynamic turbulence gage using Low carrier power aircraft antenna module for axisymmetric lifting body sensor airborne UHF communications system, considering ~71-28158 range/field strength measurements TURBULENT BOUNDARY LAYER A71-31046 Separation control of two dimensional air flow Viability of L band communication system between with tnrbulent boundary layer along circular geostationary satellites and aircraft terminals cylindrical wall by jets or suction [ NASA-TM-X-655081 N71-24913 A7 1-29433 Survey of very high and ultrahigh frequency TURBULEUT PLOW utilization in US aeronautics for communication Heat shield ablation under high enthalpy satellite frequency assignment chemically active turbulent gas flow in hydrojet [ NASA-TN-X-65527] N71-25920 engine manifolds UUITED STATES OF AMERICA ~71-28589 Survey of very high and ultrahigh frequency Soviet papers ou combustion processes in turbulent utilization in US aeronautics for communication and laminar flows of kerosene and gasoline satellite frequency assignment mixtures, stressing gas turbine engines problems [ N ASA-TN- X- 65527 1 N71-25920 871-28954 UNLOADING Friction factor for low Reynolds number turbulent Army/Navy operational evaluation of offshore flow in large aspect ratio rectangular due-*?, coutainershhips discharge by CH-54 helicopters comparing Blasius and Prandtl relations [ABS PREPRINT 5731 A71-31114 [ASME PAPER 71-FE-A] ~71-2937a UUSTEADY FLOW TURBULENT BEAT TRANSFER Unsteady curvilinear motion of lifting surface, Turbulent skin friction and heat transfer calculating induced gas flow velocities in terms prediction on flat plates and wind tunnel walls of vortex densities at supersonic and hypersonic Mach numbers, using ~71-29188 Van Driest theory Unsteady hypersonic self similar gas flow and drag ~71-29868 on circular cone accelerated according to power TURBULENT MIXING law, using small perturbation theory Modular concept mathematical model for combustion A71-29205 and pollution formation processes in jet engine Aeroelasticity and unsteady flow problems of combustors, including turbulent mixinq and aircraft reaction kinetics N71-24706 [AIAA PAPER 71-7141 A71-30766 URBAN TRANSPORTATION TUHBULEUT WAKES Aircraft capabilities in intraurban transportation Structure and shape of vortex wake associated with for Detroit metropolitan area, considering oblique flow past multiblade hinged rotor, using vehicle design, fleet size, cost and terminal cavitation method location A71-29548 A71-29217 [AIAA PAPER 71-5041 X-type hot-wiue probe thermal turbulent wake Helicopter systems operations in, around and interference, discussing wind tunnel betveen major metropolitan areas, considering investigation of wire distance effect on pitch performance of New York Airways angle sensitivity [AIAA PAPER 71-5073 871-29549 A71-31022 Integrated short-haul interurban transportation TWO DIIEUSIONAL BODIES system, considering combination of conventional Aerodynamic behavior of bodies in wake of two jet aircraft, STOL aircraft and high-speed dimensional bluff bodies, discussing loads ground transportation A71-29265 [AIAA PAPER 71-5081 A71-29550 High lift and boundary layer separation behavior Investigation of aerodynamic forces imposed on of sweptback wing airfoil profile noting vehicles proposed for operation in improved I trailing and leading edge stall pattern urban transportation system [ ARC-R/N-3648] NW-244ea N71-26129 TU0 DIUENSIONAL PLOW Separation control of two dimensional air flow with turbulent boundary layer along circular V cylindrical wall by jets or suction V/STOL AIRCRAFT 871-29433 Prop-fan propulsion system for V/STOL short haul Two dimensional jet flap cascades, presenting transport aircraft, discussing performance, stream deflection angles as function of jet to noise and weight characteristics mainstream momentum flux [SAE PAPER 7104701 8-11-28338 [ASNE PAPER 71-FE-141 A71-29453 Commercial V/STOL and jet VTOL transport, Incompressible conducting fluid plane jet discussing Do-31 test results, landing approach, expansion in homogeneous slipstream. deriving air traffic control automation and electronic partial differential equations for nonconduction control approximation 271-29131 A-57 IACUUI FURNACES ‘BDEX V/STOL aircraft instruments, deck display and rvice demand automatic flight controls for takeoff and A71-30164 landing operation VTOL turboshaft engine powered propulsion system A71-29132 development, detailing design requirements, V/STOL aircraft gust effects prediction with program planning, componeut research and system mathematical models based on nonlinear hybrid integration simulation at takeoff and landing altitudes [AHS PREPRINT 5621 A71-31109 A71-29775 VERZICAL TAKEOFF V/STOL aircraft flight path and attitude controls VTOL and STOL aircraft comparative study covering in turbulence, discussing design based on state site area, cost and noise and toxic gas variable methods of control theory production A71-29776 A71-30163 Civil aviation customer /operator. passenger and Long term prospects of air traffic development in community/ needs. describing STOL and V/STOL competition with other modes, estimating VTOL aircraf ts service denand A71-30162 871-30164 V/STOL propulsion units lift ratings based on Exhaust gas ingestion and recirculating flow field aircraft system requirements characteristics of small scale vertical take off [SAE PAPER 7104711 A71-30537 engine pod Handling qualities of V/STOL research vehicles [NASA-CR-17741 N71-25397 during steep terminal area approaches, VERTICAL TAKEOFF AIRCRAFT discussing powered lift fan VTOL aircraft VTOL propnlsion. discussing gas turbine pressnre limitations and instrument landing approach ratio inlet temperature and lifting and high [AKS PREPRINT 5441 A71-3110 1 bypass fans Composite materials application to V/STOL A71-27838 prop/rotors. determining material properties Optimization of military VTOL aircraft secondary parametric effect on frequencies and weight by power systems. considering alternate power Southwell coefficients source for aircraft hydraulics, pneumatic [AKS PREPRINT 5541 A71-31106 drives, etc Stability, control, and handling quality [SAE PAPER 7104451 A71-28326 characteristics of STOL and V/STOL airplanes RB 162 turbojet engine combustors for VTOL N71-24702 aircraft, achieving ignition by two pressure jet Computerized simulation of V/STOL terminal atomizers operative during starting cycle approach and departure paths at landing sites A71-28742 [ NASA-CR- 1183151 N71-24869 Supersonic staggered gutter colander combustion VACUUU FURNACES system for plenum chamber burning on high bypass Vacuum heat treatment of brazed and diffusion Pegasus turbofan engine of Harrier VTOL bonded jet engine components near melting aircraft, noting performance improvement temperature ~71-2a743 A71-28145 Commercial V/STOL and jet VTOL transport, VANES discussing Do-31 test results, landing approach, Aerodynamic forces produced in turbine stage by air traffic control automation and electronic vane cascade of cascade series control [NASA-TT-F-13631] N71-25998 A71-29131 VARIABLE GEOUETRY STRUCTURES Jet-supported VTOL aircraft fuel-time-optimal Wind tunnel tests of geometrically compatible landing control, using mathematical model, airfoils for variable chord sailplane Pontryagin maximum principle and analog computer A71-29257 solution VARIANCE 871-29281 Time variant distortions in supersonic inlet on Helicopter systems operations in, around and J-85-GE-13 turbojet engine from wind tunnel between major metropolitan areas, considering test, considering instantaneous distortion performance of New York Airways amplitudes and contours [AIAA PAPER 71-5071 A71-29549 [AIAA PAPER 71-6671 871-30733 VTOL aircraft minimum climb-to-cruise time YBEICLE WHEELS transition optimal open loop and suboptimal Powered landing gear wheel system requirements for closed loop control synthesis parking and taxiing of commercial jet transport A71-30799 airplanes Flightworthy 25-foot diameter proprotor wind [SAE PAPER 7104463 871-30530 tunnel test, considering civil and military need VELOCITY DISTRIBOTION for VTOL transportation Kelicopter rotor vortex system and induced [ ABS PREPRINT 501 ] 871-31077 velocity field for various angles of attack, Handling qualities of V/STOL research vehicles flight conditions and unit loads, using smoke during steep terminal area approaches, visualization technique discussing powered lift fan VTOL aircraft A71-29235 limitations and instrument landing approach Flow field velocity distribution at rotating wing [AHS PREPRINT 5441 A71-31101 devices tip vortices VTOL turboshaft engine powered propulsion system CARS PREPRINT 5221 A71-31088 development, detailing design requirements, VELOCITY ERRORS program planning, component research and system Combined inertial and instrument landing aircraft integration navigation systems with reduced cross runway [AHS PREPRINT 5621 871-3’1109 position and velocity errors, using optimal Wind tunnel investigation of jet exhausting into linear estimation cross flow - data for three jet configuration A71-30606 [ AD-7181231 N71-24491 VERBAL COUIUNICATIOB Jet vertical takeoff aircraft piloted cockpit Impedance measurements on modified broadband metal simulator for controlling aircraft flight antenna for speech communication performance [ FO A-3-C-3602- 6 1 ] N71-26150 [ ARC-R/M-3647] N71-25065 VEHTICAL LANDING VERY HIGE FREQUENCIES V/STOL aircraft instruments, deck display and Feasibility of VHF aeronautical satellite system automatic flight controls for takeoff and freguency sharing band used by ATC service, landing operation employing spatial separation, antenna A71-29132 directivity and frequency offset VTOL and STOL aircraft comparative study covering ~71-ma73 site area, cost and noise and toxic gas ATS 1 and 3 satellite VHP transponders for ships production and aircraft location, communication and remote 871-30163 sensing, discussing performance test results Lonq term prospects of air traffic development in A71-30898 competition with other modes. estimating VTOL A-58 SUBJECT INDEX WAVE REFLECTION Tropospheric and ionospheric absorption at VRF for VORTEX BREAKDOWN North Atlantic aeronautical satellite system Measurement of oscillatory pitching moment [ NASA-TN-X-655077 N7 1-2491 4 derivatives on sharp-edged delta wing at vortex Survey of very high and ultrahigh frequency breakdown angle of attack utilization in US aeronautics for communication N71-24572 satellite frequency assignment VORTEX SHEETS [ NASA-TN-X-655271 N71-25920 Vortex wakes behind STOL operations high lift VIBRATION EFFECTS wings, discussing height above qrounct and Uneven runway taxiing vibration effects on various wind tunnel dimensions effects supersonic transport aircraft, comparing A71-28033 calculation with measurement VORTEX STREETS A71-30305 Propeller vortex theory, calculating vortex VIBRATION ISOLATORS streets pitch distributions and wake Helicopter fuselage vertical and in-plane main configuration rotor head vibratory forces isolation with A71-30443 hydropneumatic servocentered system at VORTICES transmission/airframe interface Trailing vortices shed by aircraft lifting CARS PREPRINT 5141 A71-31085 surfaces, noting wake effects importance at low VIBRATIOU MODE speeds Automated modal data acqnisition and processing A71-28176 system /MODAPS/ for real-time modal vibration Structure and shape of vortex wake associated with testing of complex aerospace vehicle structures, oblique flow past multiblade hinged rotor, usin#- describing features, capabilities and cavitation method utilization A71-29217 A71-30341 Air flow past small aspect ratio thick-section VIBRATION SIMULATORS wing at small angles of attack, investigating Boeing 347 helicopter program consisting of vortex system effect on flow characteristics in. analysis, vibration simulation, wind tunnel, absence of lift whirl tower and bench tests 871-29234 [AHS PREPRINT 5711 A71-31112 Helicopter rotor vortex system and induced VIBRATION TESTS velocity field for various angles of attack, Yak 40 aircraft flight test program, discussing flight conditions and unit loads, using smoke airworthiness reqnirements, static structural, visualization technique vibration and wind tunnel tests A71-29235 A71-29911 Flow field velocity distribution at rotating wing Automated modal data acquisition and processing devices tip vortices system /MODAPS/ for real-time modal vibration [AHS PREPRINT 5221 871-31088 testing of complex aerospace vehicle structures, Angle of incidence effect on delta wing describing features, capabilities and leading-edge vortices with cross flow utilization visnalization in hydraulic test tunnel A71-30341 [ ARC-R/N-3645] N71-24482 Pincap communication antennas design and Vortical transonic gas flow over wing profile environmental tests for vibration, acceler-+.ion, N71-25714 waterproofing, salt corrosion, ice formation and compass safe distance A71-31047 W VIBRATIORAL STRESS WAKES Fatigue life of helicopter rotary wings under Aerodynamic behavior of bodies in wake of two vibrational stresses dimensional bluff bodies, discussing loads 871-24386 A71-29265 VISCOUS DRAG Mechanical support system role in determination of Asymptotic limiting viscous flow pattern and drag aeroelastic stability of leeward cylinder on flat plate with stationary separation zones immersed in wake using undamped flutter theory at large Reynolds numbers A71-31021 A71-29204 WALL FLOW VISCOUS PLOW Separation control of two dimensional air flow Asymptotic limiting viscous flow pattern and drag with turbulent bonndary layer along circular on flat plate with stationary separation zones cylindrical wall by jets or suction at large Reynolds numbers 871-29433 A71-29204 WARNING SYSTEMS Wind tuunel simulation of viscous hypersonic flow- concorde power plant fire protection system, laminar boundary layer interactions, presenting describing prototype engine bay overheat similarity parameter effects on aerodynamic detection system and additional UV optical fire characteristics detection system A71-2 ~24 A71-30300 VISCOUS FLUIDS WATER EROSIOU Axisymmetrical three component flow equations for Materials and processing methods for rain erosion incompressible viscous flnid in cylinder with resistant ceramic coated plastic structures for rotating disk supersonic aircraft, considering fiberglass A71-30855 reinforced polyimide radomes with alumina VISIBILITY coating Description of method for determining visibility 871-29645 in earth atmosphere UAVE DRAG [ AD-7195021 N71-24375 Uing thickness optimal distribution for minimum High intensity xeon flashtube lights for wave drag in supersonic flow at zero anqle of increasing conspicuity of trainer helicopters attack for given planform, using Ritz method at during daytime and nighttime flights lower Mach numbers [ AD-718639 3 N71-24 669 871-29222 VISUAL FLIGHT PAVE PROPAGATION Visual flight simulation devices, considering high Atmospheric models of partially trapped waves resolution photogrphic films and digital propagation in layer above tropopause with large memories stratospheric Scorer parameter A71-29483 A71-29763 VOLTAGE REGULATORS WAVE REFLECTION Soviet book on airplane and helicopter electrical Incident sonic boom shock wave reflection factors power supply systems covering storage batteries. off smooth snrface, discussing pressure rise and DC generators, alternators, voltage regulators, flight near threshold Mach number current and frequency control, etc A71-30610 A71-29525 A-59 WAVEGUIDE ANTENNAS SUBJECT INDEX RAVEGUIDE ANTENNAS sampling periods Flush mounted aeronautical vaveguide antennas with A71-30395 dielectric plug for 5GHz operation WIND TUNBEL MODELS A7l-31043 Ballistic wind tunnel for drag measurement on WEAPON SPSTENS models during free flight at supersonic speeds Cheyenne attack helicopter weapons system, A7 1-29 20 1 discussing night vision capability. armament. Wind tunnel model trajectory simulation system fire control and navigation equipment vith closed loop control by digital computer, integration describing instrumentation, system [AHS PREPRINT 5301 A71-31091 servoamplifiers and testing procedures weapons delivery computer for attack helicopters, A71-30334 using planar distributed function generator for wind tunnel investigation of jet exhausting into general closed form instantaneous solution cross flow - data for three jet configuration capability [ AD-7181231 171-24491 [AHS PREPRINT 5311 A71-31092 Transonic flutter and buffeting for elastic wind WEAPONS tunnel models of straight wing proposed for Test procedures to determine ability of aircraft space shuttles equipment and armament to withstand storage and 171-24659 operate effectively in tropic environment wind tunnel simulations of flow fields and [AD-7205701 N71-26194 aerothermodynamics of space shuttle orbiters WEATHER FORECASTING 871-26053 Aircraft hazards due to frequent low cloud Aerodynamic characteristics of delta wing space occurrences at Kenya airport, forecasting shuttle configurations weather with statistical analysis and N71-26062 radiosound ing BIND TUNNEL STABILITY TESTS A71-29106 Yak 40 aircraft flight test program, discussing Thunderstorm, CAT, weather and mountain wave airworthiness requirements, static structural, induced turbulence forecasting and analysis for vibration and wind tunnel tests transport aircraft A71-29911 871-29764 Frequency response of five component strain gage Clear air turbulence in stratosphere and effects oscillating balance for dynamic wind tunnel on weather formation, atmospheric physics, and stability testing supersonic flights A71-30333 [ JPRS-531331 N71-25746 wind tunnel force test program design for jet WEATHER RECONNAISSANCE AIRCRAFT aircraft configurations, including propulsion Oklahoma and llalaysia thunderstorms comparison system simulation based on weather reconnaissance aircraft A71-30605 measurements. considering turbulence patches Nultimission strategic aircraft installation B71-29752 effects testing in propulsion and aerodynamic WEIGHT ANALYSIS wind tunnels,-yielding flowfield definition, Landing load estimation methods for preliminary inlet internal performance, drag, forebody shape design weight prediction for military aircraft and orientation A71-28211 [AIAA PAPER 71-7591 A71-30792 1-1011 Tristar antenna arrangement test results, Flightworthy 25-fOOt diameter proprctor wind considering weight, aerodynamic and structural tunnel test, considering civil and military need design requirements for VTOL transportation A71-31060 [AHS PREPRINT 5011 871-31077 Size effects on large rotor systems design, Forward flight performance of coaxial rigid rotor considering weight, blade loading, tip speed, in NASA wind tunnel, comparing to aerodynamic etc stability with conventional rotors [BAS PREPRINT 5521 A71-31104 [AHS PREPRINT 5241 A71-31090 Composite materials application to V/STOL Rotor stability derivatives determination from prop/rotors, determining material properties instrumented OB-6A prototype helicopter wind parametric effect on frequencies and weight by tunnel tests, comparing data with analytical Southvell coefficients results obtained by digital computing technique [AAS PREPRINT 5541 A71-31106 [AHS PREPRINT 5431 A71-31100 HEIGET MEASUREMENT Boeing 347 helicopter program consisting of Onboard weighing system for gross weight analysis, vibration simulation, wind tunnel, determination and center of gravity location of whirl tower and bench tests Alouette helicopter, using load sensors, [AES PREPRINT 5711 A71-31112 electrical circuits and visual indicators Low-speed wind tunnel longitndinal stability tests A71-30320 on sweptback wing model with blowing at leading WESTLAND AIRCRAFT edge slats and trailing edge flaps for Buccaneer Westland UG 13 Lynx helicopter, discussing design aircraft performance features, performance characteristics and civil [ ARC-R/K-3655] 871-24565 and military applications Transonic wind tunnel tests of vertical fin loads A71-30301 and rudder hin'ge moments on N2-F3 lifting body HIND EFFECTS scale model at Nach 0.50 to 1.30 Extreme turbulence measurement during low level [ NASA-TN-X-22861 N71-24581 flights of lirage 83-76 fighter aircraft, Aircraft development facility vith wind tnnnel determining true gust velocities and power testing capability suectral enerav-- distributions [AD-7198021 N71-25048 A71-29756 Reynolds number simulation requirements for, Aircraft with T tail configuration, examining subsonic wind tunnel tests of space shuttle dynamic response to lateral gusts configurations A7 1- 2978 6 N71-26065 Aircraft design and fatigue life monitoring, WIND TUNNEL WaLLS investigating effects of gust velocity frequency Turbulent skin friction and heat transfer distribution in patches of atmospheric prediction on flat plates and wind tunnel walls turbulence at supersonic and hypersonic Nach numbers, using 871-29789 Van Driest theory WIND MEASUREMENT A71-29868 Aircraft instrumentation and data analysis for WIHD TUNNELS clear air turbulence, including orthogoral Supersonic inlet turbojet engine compatibility components and temperature and wind tests in wind tunnels, using light panels and distributions Summation Device analysis 871-29753 A71-28032 Single anemometer wind measurement required for Wind tunnel tests of geometrically compatible aircraft landing, comparing data from different airfoils for variable chord sailplane A-60 SUBJECT INDEX ZERO ANGLE OF ATTACK A71-29257 Heat transfer within resonant cavities at subsonic and supersonic flow, discussing uind tunnels, Y test procedures and data reduction YAK 40 AIRCRAFT [ASUE PAPER 71-FE-91 A71-29450 Yak 40 aircraft flight test program, discussing Noise prodnction during aerodynamic tests on airworthiness requirements, static structural, helicopter rotor in wind tunnel vibration and wind tunnel tests A71-30519 A71-29911 RIND VELOCITY YAR Anemometer measurement optimum aqeraging time of Roll moment of inertia to static margin ratio wind speed for conventional aircraft landings effect on yaw of repose angle magnitude in A71-30394 ballistic match of projectiles Single anemometer wind measurement required for A71-29890 aircraft landing, comparing data from different sampling periods A71-30395 Z RING FLAPS ZERO ANGLE OF ATTACK Noise measurement data on various types of blown Heat transfer on spheres and sharp cones in flap configurations for STOL aircraft, rarefied hypersonic gas flow at zero angles of discussing integration effects betueen jet and attack in wind tunnel vacuum flap assembly A71-29176 [AIAA PAPER 71-7451 871-30785 Wing thickness optimal distribution for minimum En route aircraft flap control during descent and wave drag in supersonic flow at zero angle of holding attack for given planform, using Bit2 method at [ARB-l'N-99 3 N71-24920 lower Mach numbers Static tests of augmentor-wing flap system for 171-29222 modified C-8A jet STOL research airplane using 0.7 scale model [ NASA-CB- 11 431 5 1 N71-26416 RING LOADING Wing-jet interference effects in cross uind on thrust and aerodynamic characteristics at large distance from and near ground A71-29207 Gust transfer functions relating lift and moments to upwash in single sinusoidal wave for large aspect ratio rectangular wings in turbulent incompressible flow A71-30604 Helicopter rotor blade airload by applying lifting surface solution [AHS PREPRINT 5101 A71-31081 Size effects on large rotor systems design, considering weight, blade loading, tip speed, etc [AHS PEEPRINT 5521 871-31104 Numerical evaluation of downwash integral for wing loading of lifting rectangular planform I FIPL-RA-90 3 N71-24483 Low wing loading STOL transport ride smoothing using Boeing aircraft [ NASA-CR-111819 1 N71-24586 RING OSCILLA2IONS Measurement of oscillatory pitching moment derivatives on sharp-edged delta wing at vortex breakdown angle of attack N71-24572 RING PANELS Structural and inertial nonlinearities influence on flat or curved panel flutter A71-30825 RING PROFILES Wing thickness optimal distribution for minimum wave drag in supersonic flow at zero angle of attack for given planform, using Ritz method at lower Mach numbers 871-29222 WING SPAN Incompressible fluid motion in laminar boundary layer on blade rotating uniformly about axis perpendicular to wing span A71-30218 RINGS Transonic flutter and buffeting for elastic uind tunnel models of straight wing proposed for space shuttles N71-24659 Vortical transonic gas flow over wing profile N71-257 14 X XENON LAMPS High intensity xeon flashtube lights for increasing conspicuity of trainer helicopters during daytime and nighttime flights r AD-71 86391 N71-24669 A-61 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 8) AUGUST 1971 Typical Personal Author Index Listing PERSONAL AUTHOR A71-29779 for improvinq the ARESTBONG, D. cras5wortnines.s OF inteqral fuel tanks Final Theoretical and experimental analysis of acoustic rwort, 1967 - IS70 linings for ducts with flow [?Al-YA-7n-46] , ,N71-;101q [AIAA PAPER 71-7311 A71-30778 ABUOLDOV. V. U. Interference between a wing and a jet in cross wind A71-29207 ABOUSOU, B. E. The costs/reliability relationships of development testing and demonstration Listings in this index are arranged alphabetically by personal author. The [SAE PAPER 7104521 A71-28330 title of the document provides the user with a brief description of the ASEPOETE, E. E. subject matter. The report number helps to indicate the type of document The operational proving of automatic flight cited 1e.g.. NASA report, translation. NASA contractor report). The accession control systems in the approach and landing number is located beneath and to the right of the title. e.g.. N71-11019. phase Under any one author's name the accession numbers are arranged in se- A71-29261 quence with the IAA accession numbers appearing first. ATUIP, F. R. An analysis of gust velocities for application to aircraft design A71-29789 ATVABS. J. A Parametric studies of the acoustic behavior of ADAESOU, G. P. lined ducts and duct lining materials for Development progress - New transport engines- JT9D turbofan engine applications [SAE PAPER 7104191 A71-30527 [NASA-CR-l11887] N71-26417 ADIUSKOV, €3. P. AUSTIEI, U. E., JB. The work of turbine and injection burners on a gas The effects of atmospheric turbulence on handling variable composition qualities and structural loads [ AD-71983111 N71-25359 A71-29787 AGGABWAL. S. E. AXELSOU, J. A. The role of heat conduction in leading edge static and dynamic aerodynamics of space shuttle heating theory and experiment vehicles ' [ARC-CP-11261 N71-24446 171-26062 AELERS, E. E. Operations research analysis of aircraft noise abatement B [AIAA PAPER 71-5251 871-29551 BACON, E. P. AIKEU. T. U. The National Airport system Plan - Its history and Low speed aerodynamic characteristics of a large its potential scale STOL transport model with an augmented jet [SAE PAPER 7104141 871-28306 flap BAEEBD, E. [ NASA-TU-X-620 171 871-26 183 Use of miniaturized microphones in the study of AREEEBOV, A. P. the sound radiation of vibrating modes in Selection of a cam profile for the computing- rotating machines resolvins unit of an altimeter 171-30517 A71-28938 BAGLEY, G. ALECSANDRIESCIJ. C. An aerial module for the uhf band Propulsion guidance and stability of the ground A71-310116 effect vehicle with perimetric Coanda fluid BAILEY. R. U. boundary The use of high intensity xenon lighting to A71-29308 enhance US Army aircraft day/night conspicuity ALEKSEEV, S. A. [ AD-7186391 N71-24669 Calculation of three-dimensional structures. BALL, W. E. Number 13 Experimental correlation of installation effects A71-30888 for inlet/airplane integration AtLINIKOv, S. [AIAA PAPER 71-7591 A71-30792 Application of photochromic coatings for BARNES. J. P. nondestructive inspection Final technical cooled gas tnrbine blades report, Jan. 1969 - Jnl. 1970 871-28748 [ AD-720239 3 N71-26383 BABBETT, 1. D. AUDEBSON, E. C. Evaluation of rotor controls designed for Salt driers assure really dry fuel to aircraft increased safety [SAE PAPER 7104403 A71-28322 [AHS PREPRINT 5501 A71-31102 ANDEBSOU, E. U. BASKIU, V. E. Air navigation techiiques Theory for the unsteady curvilinear motion of a 871-30712 lifting surface in a gas ANDERSON. E. E. A71-29188 Results of an experiment to locate and read data BAXTEB, E. G. from unmanned transponders using satellites Dulles International Airport access A71-30898 [ PB-194094) N71-26301 AUDERSON, S. E. BAYER. R. Simulation techniques used in investigating New developments in product support aircraft accidents [ SAE PAPER 7104371 A71-30529 B- 1 BAZZEIN. A. P. PERSONAL AUTEOB IBDEX BAZZEIN. A. P. A71-29530 Influence of the real properties of air on flow BOGACEEV, I. 8. parameters around an elliptical cone - Short term creep of metals and alloys under Aerodynamic characteristics of elliptical cones conditions of aerodynamic heating at large angles of attack [ NASA-TT-P- 13633] ~71-25a22 A71-29191 BOGDANOVA. V. V. BEABLANR. 1. E. Universal equations of the laminar boundary layer Olympus 593 for Concorde updating of development on a rotating wing position ~71-3ozia [SAE PAPER 7104221 A71-28309 BOEON, E. L. BEABDEB. C. 1. Application of recent panel flutter research to INS projections and improvements - Capabilities in the space shuttle. Part 2 - Influence of edge the future clips and flow angularity [SAE PAPER 71045ai A71-30534 N71-24661 BEAUMONT. G. E. BONBELL, J. I. flap presentations for future ATC displays Combustion instability in turbojet and turbofan A71-30014 augmentors BEAVERS, G. S. [AIAA PAPER 71-6981 A71-30757 Low Reynolds number tnrbulent flow in large aspect BOBG, C. ratio rectangular ducts fleasurement of a helicopter's gyro displacements [ASME PAPER 71-FE-A] 871-29378 in some different flying conditions BECKHAN. H. E. [ FOA-Z-C-2356-49-/72/] N71-26567 Area navigation systems and displays BOBISOVICE. V. G. [SAE PAPER 7104571 A71-30533 Problem of gear link design for grinding-belt BECKHITE, 8. E. machines Operational forecasting and analysis of turbulence A71-289113 A71-29764 BOR1OTOV. V. N. Use of weather radar for aviation Aircraft refractometer [ 180-2 64-TP- 148] N71-24394 A71-28250 BEKIBBAEV, K. E. BOULADOB, G. The Yak-40 aircraft flight test procedures The total transport demand A71-29911 A71-30159 BELLIBGEB. E. D. BOHEB, C. V. Analytical investigation of the effects of blade Analysis of transmission failure modes flexibility, unsteady aerodynamics, and variable [SAE PAPER 7104541 A71-28331 inflow on helicopter rotor stall characteristics BOPCE, 1. P. [AES PREPRINT 5201 A71-31086 skin friction drag and velocity profile BEBSOB, V. L. measurement techniques in two-phase flow Accessories for gas turbine APU's [ASME PAPER 71-PE-321 A71-29467 871-29262 BRADLEY. E. F. BEBZAKEIN. 1. J. coated columbium for gas turbine engine Some experimental results on lift fan noise application reduction [SAE PAPER 7104501 ~71-2a334 [AIAA PAPER 71-7433 A71-30784 BBABDEHIE, D. 1. BERKSHIRE. F. E. Requirements, perforinance and integration of Partially trapped waves modern navigation aids 871-29763 [SAE PAPER 7104563 A71-28333 BEBBABD. J.-P. BEAT, E. S. Experimental stndies on absorbent materials used Simulation techniques used in investigating in turboreactor ducts aircraft accidents A71-30518 A7T-29779 BEET, J. A. BBENBEB, 1. Salt driers assure really dry fuel to aircraft structural stability of the rotor system of the [SAE PAPER 7104401 ~71-2a322 hot-gas reaction helicopter DO 132 BETIAEV, S. K. N71-24387 Hypersonic self-similar flow past a cone moving BBENBEB, W. according to a power law On-board checkout approach to engine diagnostics - A71-29205 It can work BETZ. E. [AIAA PAPER 71-6571 A71-30727 Study of visible exhaust smoke from aircraft jet BBESLAVEIIS, V. 6. engines Aircraft technician's handbook of electrical CSAE PAPER 7104za1 A71-28314 equipment BIGGEBS, J. C. A71-29530 Eorizontal stoppable rotor conversion BBEVIG. 0. [AHS PREPRINT 5021 A71-31078 Shock interference heating on the space shuttle BIGLEB, S. G. booster during ascent Use of weather radar for aviation N71-26059 [ 110-264-TP- 148] N71-24394 BBOLL, C. BISAGA, J. J. Noise measnrements in the large Modane wind tunnel Radio frequency utilization in the bands of A 71 -305 19 principal interest for aeronautical satellites EROSE, A. [ NASA-TI-X- 65527 ] N71-25920 High frequency rake probes for inflight intake BLACLBUBB. A. H. airflow distortion measurements The SST A71-30321 871-29387 BBOHNE, J. 1. BLaZEJ, J. E. VTOL propulsion system development Technical evaluation of dual input transponder [AES PBEPBIUT 5621 A71-31109 Final report, Jul. 1969 - Hay 1970 BBOWBIE. E. E. [ FAA-NA-71-39] N71-24882 Airfield pavement condition survey, USNS Adak, BLEBKIBOB. T. F. Alaska Testing of lubricants for the Olympus 593 .[ AD-719889 3 N 7 1-25604 871-29826 BBOHBSOB. J. J. BLICK, E. F. Static and dynamic aerodynamics of space shuttle Skin friction drag and velocity profile vehicles measurement techniques in two-phase flow N71-26062 [ASME PAPER 71-FE-321 A71-29467 BBUBSTEIA, A. I. BLIOGEB. 1. F. Lessons to be learned from accidents attribnted to Aircraft technician's handbook of electrical turbulence equipment A71-29770 B-2 PEBSONBL AUTEOB INDEX COOPER, C. E. BRYAN. E. A71-28841 Some observations of the atomizing characteristics CABTEII. A- S., JB. of air-blast atomizers Development of airborne remote clear air A71-28756 tnrbnlence, CAT, detection equipment BBYEB, D. I; A71-29765 The behaviour of the leading-edge vortices over a CABY. E. E. 3. delta wing following a sudaen change of A high speed airborne scanning aerial with matched incidence patterns [ ARC-R/B-3645] N71-24482 A71-31036 BUDD. E. W. An airborne electronically scanned X band narrow MODBPS- Advanced instrumentation for automated beam circular antenna array modal vibration testing A71-31038 A71-3034 1 Antennas for sideways looking airborne radar BULLEN. A. I. 851-31041 The analysis of normal accelerations experienced CASPABI, 1. by fleets of transport aircraft Helicopters as cranes, and carrying external A71-29788 loads. 11 - The planning and the constructive BURAKOV. r. I. design of 'crane helicopters' Optimal distribution of wing thickness in A71-28489 supersonic flov Belicopters as cranes, and carrying external A71-29222 loads. 111 BUBBEBBY. E. A. A71-29144 A review of helicopter aerial problems CEAIBEBS, J. E. A71-31048 Stability and control characteristics of STOL and Ef notch aerials for small aircraft V/STOL airplanes A71-31053 N71-24702 BUBCHAI. F. W., JB. CHELYSHEVA, I. F. Use of the gas generator method to calculate the Influence of the real properties of air on flow thrust of an afterburning turbofan engine parameters around an elliptical cone - [AIAA PAPER 71-6801 A71-30744 Aerodynamic characteristics of elliptical cones BURGESS, E. K. at large angles of attack Developmeni. of the ABC rotor A71-29191 ram PREPRINT 5041 A71-31080 CHERBIKOVA, L. G. BURKE; E. J. Experimental study of heat transfer on spheres and 'Third Chance' flight control system sharp cones in a rarefied hypersonic gas flow A71-29382 A71-29176 BUBROUS, 3. ii. CHIGIBB, 11. A. Combined inertisl - ILS aircraft navigation Tip vortices - Velocity distributions systems [AHS PREPRINT 5221 871-31088 A71-30606 CHOBY. D. A* BUBSTADP, P. L. Uach 2.5 performance oZ a bicone inlet with Instantaneous and dynamic analysis of snpersonic internal focused compression and 40 percent inlet-engine compatibility internal contraction [AIAA PAPER 71-6673 A71-'0733 [ NASA-TI-X-2294] 871-25872 BUBSTEIN. 8. E. CEBISTIAIISOB, 1. Air passenger traffic in short-haul markets Circumferential traversing technique for intra- N71-26528 stage analysis of axial flow compressors BUTLER. S. F. J. [ASME PAPER 71-PE-331 A71-29468 ' Low-speed wind-tunnel tests on a sweptback wing cIFFonE, D. L. model /Buccaneer Nark 1/ witb blowing at the Static and dynamic aerodynamics of space shuttle wing leading edge and blowing over the flaps and vehicles drooped ailerons N71-26062 [ ARC-R/M-3655] N71-24565 CLARK. 1. E. BUIBAUI. 0. Noise measurements for a three engine turbofan Extreme value analysis and its application to c.g. transport airplane during climbont and landing vertical accelerations measured on transport approach operations airplanes of type C-130 [NASA-TN-D-6137] N71-24582 [ AGARD-R-579-7 1 ] N71-25080 CLEABY. J. U. Static and dynamic aerodynamics of space shuttle vehicles C N71-26062 CAGGIANI. S. COCKSHUTT, E. P. Trends in the development of aeronautical turbojet VTOL propulsion - 1970 perspective engines A71-27838 A7 1-2981 1 COB, C. F, CaLoGEBas. J. E. Preliminary measnrements and flov visualization Instantaneous and dynamic analysis of supersonic studies of pressure flnctuations on space inlet-engine compatibility shuttle configurations [AIAA PAPER 71-6673 A71-30733 N71-24663 CAIN, S. E. COLLIBGBOUBNE, J. R. Aircraft vortex wake Prospects for the developnent of air traffic in A71-28176 competition uith other moaes CANTOBI, D. A. 871-30164 Motor starting techniques for the 2 to 15 kii COLTRIB, E. E. Brayton space power system Instantaneous and dynamic analysis of supersonic ' [ NASA-TI-X-67819] N71-24691 inlet-engine com pa tibility CABETTO, 1. S. [AIAA PAPER 71-6671 A71-30733 The role of kinetics in engine emission of nitric COOK, a. H. oxide Low speed aerodynamic characteristics of a large 871-30454 scale STOL transport model with an augmented jet CAREY. J. E. flap High entrainment ejector desig7 [ NASA-T8-X-62017] 871-26183 [ASME PAPER 71-PE-341 A71-29469 COOK, J. E. CABLSOB. A. U. AH-568 vehicle development Compressor sensitivity to transient and distorted [AHS PREPRINT 5741 A71-31115 transient flows COOPBE, C. EI r AIAA PAPER 71-650 1 A71-30734 An airborne blade antenna for 26-100 MHz CAROL; I. 871-31044 Plug in relay - Panacea or Pandora's BOX E- 3 COOPER. 0. 1. PERSONAL AUTEOB INDEX COOPER, 0. 1. DAWSON. C. Pressure-altitude assembly for high-altitude A high efficiency dassegrain aerial design balloons 871-31056 A71-30070 DAWSOB, C. E. COPELAND. U. 1. Simulation and measurement of pressure transients Noise measurements for a three engine turbofan in a mixed-compression supersonic intake during transport airplane during climbout and landing engine surge approach operations [AIAA PAPER 71-6711 A71-30735 [ NASA-TI-D-61371 W71-24582 DE BELLEVAL. J.-F. COBBELEETI S. Preliminary results in a study of the infrared On the uncertainty limit of high speed electronic emission of a hot jet scanning A71-30520 A71-31049 DE GALABD, J. COBSIGLIA, V. E. The 'Uercure' - The first aircraft of t new Tip vortices - Velocity distributions generation [ABS PREPRINT 5221 A71-31088 A71-29276 COTTOB, D. E. DE GEEB, I. D. The measurement of temperatures and radical Traversing probe Patent concentrations in high-temperature, flowing-gas f NASA-CASE-XFR-02007 1 N71-24692~ ~~ streams DE BAkO, D. A- A71-28750 An airspace utilization model for V/STOL terminal COUCH, A. 1. operations ALPA - A survey of airport fire and rescue [ NASA-CR-1183151 B71-24869 facilities, 1971, North America DE ROSE. C. N71-26466 Flow- fields and aerodynamic heating of space COUPBY. G. shuttle orbiters Some results on gust alleviation 871-26053 A71-29785 DEITS, G. E. CBAGGSI A. Salt driers assure really dry fuel to aircraft The response of a simply supported plate to IN' [SAE PAPER 7104401 A71-28322 uaves at oblique incidence DIAL, D. D. A71-30068 Advanced composite cost comparison CREED. E. W, A71-29656 A8/ASN-86 Inertial Navigation Set DIATLOV, I. 1. [ABS PREPRINT 5331 A71-31094 Comparative estimation of start-up and breakdown CREEL, r. E., JB. characteristics of gas-turbine engine combustion Shock interference heating and density ratio chambers with mechanical and air- stream effects. Part 2 - Bypersonic density ratio mechanical propellant atomization effects A71-28968 N71-26058 Investigation of a gas turbine engine start-up CBOIPTON, D. D. igniter Airborne Integrated Data system A71-28969 A71-30319 Effect of airstream-mechanical propellant CBONBUBG, J. E. atomization on the carbon deposition rates in a A comparison of pilot performance using a center gas-turbine engine combustion chamber stick vs side arm control configuration A71-28970 Technical report, May - Oct. 1968 DIKUSAB. V. V. [ AD-720846 ] N71-25846 Irregular optimal trajectories of a spacecraft CBOSLEP, J. K. during flight in the atmosphere The use of high intensity xenon lighting to A71-29229 enhance US Army aircraft day/night conspicuity DIVITA,'J. S. [ AD-7186391 N71-24669 Analytical and experimental evaluation of CBOWLEY. 1. D. performance prediction methods applicable to Realtime graphic flight test becomes a reality exhaust nozzles A71-30318 [AIAA PAPER 71-7193 871-30770 CULLEX. F. P. DODD. 8. 1.. JB. Design tradeoffs for EF and synchronous satellite Empennage loads on T-tail transports in continuous data collection systems atmospheric turbulence A71-30900 ii71-24996 CURBEBI, J. S. DODS. J. B., JB. Motor starting techniques for the 2 to 15 RW Preliminary measurements and flow visualization Brayton space power system studies of pressure fluctuations on space [NASA-TU-X-678193 N71-24691 shuttle.configurations CURTIS, G. C. 871-24663 The UAC MADAR System - An AIDS model for DOBELY, P. commercial airlines AtmosDheric turbulence and the air transDortation [ SAE PAPER 7104251 A71-28311 system CUBTISS, E. C.. JB. A71-29750 A stability and control theory for hingeless DOBLAN. C. J. rotors Current shuttle status [ABS PREPRINT 5411 A71-31098 171-26052 DOBIEB. B. The L band aircraft antenna of the 'Dioscures D System' - Electronic scanning for satellite- DALIN,.V. N. aided navigation system Eelicopter designs A71-31074 971-29944 DOBSCE, E. G. DANESHYAB. E. Blown flap noise research A comparison of the performance of three model [AIAA PAPER 71-7451 871-30785 axial flow turbines tested under both steady and DOUGAL, A. A. pulse flow conditions Bolography and optical data processing in A 11-29819 aerospace instrumentation DABCHINOV. E. N. A71-30329 Evaluation of the mechanical properties of alloys DOUGBEBTY, J. E. and components in aircraft engine production FAA appraisal of aircraft design for 871-28944 maintainability DAVIS, E. A. [SAE PAPER 7104311 A71-28316 concorde pouer plant fire protection system DOUNEY. J. D. 871-30300 Expansibility and economy of terminal structures B- 4 PERSONAL AUTEOB IBDBX PBICKE, 1. B. [SAE PAPER 7104183 A71-28307 chemically active gas in the manifolds of a DRAPEI, C. S. hydro-jet engine Guidance is forever A71-28589 A71-30710 PEDIAEVSKII, K. K, DUDKIII. V. T. Influence of the vortex system of a uing in the Influence of bypass of air behind the compressor absence of lift on the flou past the wing at into a variable-area exhaust nozzle on the small anales of attack indices gas turbine jet engine A71-29234 A71-28586 DUGUBDJI, J. 3-D-radar is here Perturbation and harmonic balance methods for A71-28886 nonlinear panel flutter Technical report, 11 FEBBI, A. Dec. 1969 - 15 Mar. 1971 Practical aspects of sonic boom problems [NASA-CR-l11907] N71-25362 A71-30820 DUKE. F. E. FILOTAS. 1. T. The Boeing Eodel 347 advanced technology Approximate transfer functions for large aspect helicopter program ratio wings in tnrbnlent flow CARS PREPRINT 5711 A71-31112 1171-30604 DUBVASULA. 5. FIBBEGAB. P. 1. Flutte; of clamped skew panels in supersonic flow Preliminary impact speed and angle criteria for A71-30607 design of a nuclear airplane fission product containment vessel [ NASA-TM-X-22451 N71-25411 E PISCEEB. J. E. EAEES. J. I. Fluctuating pressure measurements from DC to over The new Ilelbourne/T.ullamarine airport 100 KHz in jet engine testing A71-29310 1171-30325 ECOBOMOS, C. FISCHBB. U. C- A mathematical model for jet engine combustor Effect of angle of attack on boundary-layer pollutant emissions transition at Each 21 [AIAh PAPER 71-7141 A71-30766 A71-29887 EDELIAN. E. FISHER, E. K., JR. A mathematical model for jet engine combustor Detailed aerodynamic measurements on a model rotor pollutant emissions in the blade stall regime [AIAA PAPER 71-7143 A71-30766 [AHS PREPRINT 5211 A71-31087 EDEBBOBOUGB, E. K. FITZPATRICK. C. 6. Full-scale proprotor development Bf notch aerials for small aircraft CARS PREPRINT 5011 A71-31077 A71-31053 EDWARDS. J. P. PITZSIHUOES. 8. D. Cooled gas turbine blades The future of STOL A71-28748 [SAE PAPER 7104641 A71-30535 EDUABDS, K. J. PLOWER. S. A comparison of the performance of three model Commercial aircraft flvinq.. in turbulence - Some axial flow turbines tested under both steady and considerations pulse flow conditions A71-29782 A71-29819 POIIBA. ti. B. EHEBUBEBGEB. 1. J. Influence of the vortex system of a wing in the Analysis of subjective ratings for the XB-70 absence of lift on the flow past the wing at airplane response to atmospheric turbulence and small angles of attack controlled inputs A 7 1-2 9234 A71-29774 POBBEP. J. A. ELGIB. C. F. An analysis of predicted space shuttle The IAC EADAR System - An AIDS model for temperatures and their impact on thermal commercial airlines protection systems [ SAE PAPER 7104251 A71-28311 871-26054 EBGEL, 1. B. PBAGASSI. J. P. Electrical and physical nature of microbial High-speed flash photography of jets and study of membranes implicated in aircraft fuel quantity noises of aerodynamic origin probe malfunction A71-28767 [SAE PAPER 7104391 A71-28321 PBABKLIB. J. A. EBICKSOU, 1. 1. Turbulence and lateral-directional flying Thick high aspect ratio wing, part 2 qualities N71-24659 [NASA-CR- 17181 N71-26170 ESMEB, G. P. FEASER. W. E. Sensing and communications technologies for \n airborne phased array for use in an ATC wayside headway control systems satellite system in L-band A71-30337 A71-31054 EVAES, 1. R. FBEDBICKSON, C. Vortex wakes behind high-lift wings Factors affecting fuel control stability of a A71-28033 turbine engine and helicopter rotor drive system EVERLIBG, P. C. [AHS PREPRINT 5601 871-31107 Analytical and experimental evaluation of PBEBUAI?, E. B. performance prediction methods applicable to Preliminary design methods of V/STOL prop- rotors exhaust nozzles [AHS PREPRINT 5541 A71-31106 [AIAA PAPER 71-7193 B71-30770 FRICKE, I.. B. EVERSMAN, r. A wind tunnel investigation of jets exhausting Theoretical and experimental analysis of acoustic into a crossflou. Volume 4 - Additional data linings for ducts with flow for the three jet configuration CAIAA PAPER 71-7311 A71-30778 [ AD-7 181231 N71-24491 A wind tunnel investigation of jets exhausting into a crossflow. Volune 1 - Test description F and data analysis FADEEV. 1. V. [AD-7181223 N71-24492 Influence of bypass of air behind the compressor A wind tunnel investigation of jets exhausting into a variable-area exhaust nozzle on the into a crossflow. Volume 2 - Additional data indices gas turbine jet engine for the one jet configuration A71-28586 [ AD-7202321 N71-26516 FAFURIB. A* V. A wind tunnel investigation of jets exhausting Heat and mass transfer in the turbulent flow of a into a crossflow. Volume 3 - Additional data B-5 FBIEBEBG. I]. PERSONAL AUTHOR IADEX for two-jet configurations GEBLACH, C. E. [AD-7202333 N71-26517 Design principles for airport pavements FBIEBERG, U. 871-29311 Ejection seat system performance, versus aircraft GEYEB, 8. II. performance Evaluation of coated alloys for turbine components 871-29385 of advanced gas turbine engines FBIEDBICH. 0. 1.. JB. A71-29635 Holography and optical data processing in GILBERT. 6. B. aerospace instrumentation High entrainment ejector design 871-30329 [ASBE PAPER 71-FE-341 A71-29469 FBOGEB, C. GILBERT, 1. J. Fluctuation of sound pressures created by a fan in Motor starting techniques for the 2 to 15 kl a very low speed snbsonic wind tunnel test Braytou space power system stream /0.10 less than V less than 20 m/sec/ [NASA-TH-X- 678 19 3 N71-24691 A71-30526 GILBERT, H. P. FBUBOESE. J. Control considerations in severe turbulence Thrust measurement of great accuracy of aircraft A71-29772 propulsion systems giving particular attention GILSOB, E. D. to a hydranlic force measurement device. I1 Beryllium brake experience on the C-5A airplane A71-29860 [SAE PAPER 7104271 A71-28313 FUBLOBG, 0. D. GILPABD, G. B. Fluidic cabin pressure control systems for In-flight evaluation of the lateral handling of a military and civil aircraft four-engine jet transport during approach and A71-30308 landing [NASA-TN-D-63391 N71-25537 GIOBGIEBI, 1. G Conceptual lines for the definition of an GAABDEB. 8. T. aeronautical project The theory of digital processing of stochastic A71-30824 signals for use in avionic systems on-board Air GLANZ. E. E. Force aircraft Final scientific report, 1 Jan. Area navigation in the ATC environment 1967 - 31 Dec. 1970 [SAE PAPER 7104553 A71-28332 [ AD-7 19822] N71-24954 GLASGOH, E. E. GABEIELLI. 6. Analytical and experimental evalnation of Shape of the fnselage of modern passenger performance prediction methods applicable to transports exhaust nozzles A71-30821 [AIAA PAPER 71-7191 A71-30770 GALKIB. V. SA GLASS. E. E. Wind-tunnel simulations of viscous hypersonic Aircraft noise type certification orientation flows session Final report A71-29224’ [ HRC-TR-300 ] N71-26304 GAIIBUCCI. E. J. Aircraft noise type certification orientation Thick high aspect ratio wing, part 2 session - Lecture notes, supplement 2 Final N71-24659 report GABGEB. T. G. [BBC-TR-300-SUPPL-2] N71-26305 Results of initial prop-fan model acoustic GLASSIIAB, A- J. testing. Volume 2 - Appendices B thru F Shuttle airbreathing propulsion [ NASA-CR-111842-2 3 N71-25784 [AIAA PAPER 71-6621 A71-30731 Results of initial prop-fen model acoustic GLAHE. 6. E. testing. Volume 1 - Discussion A review of the mass-flux probe [NASA-CR-111842-1] 871-25785 A71-29925 GABNIEB, 1. GODBOLE. P. S. The progress and economics of the aero-engine Some observations of the atomizing characteristics 871-30303 of air-blast atomizers GABBISOB, J. B. A71-28756 An assessment of atmospheric turbulence data for GODSTOB. J. aeronautical applications STOL engine systems and sensitivity factprs A71-29751 [SAE PAPER 7104691 A71-28337 GASPEBS, P. A.. JB. GONOB. A. 1. Application of recent panel flutter research to Hypersonic flow past a delta wing the space shuttle. Part 1 - Boundary layer and A71-30874 hypersonic effects GOBTAB, I. D. N71-24660 Aircraft refractometer GAUDBOB. J. A71-28250 Determination of sound fields of aircraft in GORDON, G. fliqht by treatment of noise measurements Interference between a wing and a jet in cross A71-30521 wind GAULT, J. A71-29207 An analysis of gust velocities for application to GOBHAM, J. A. aircraft design Development testing of the 1-1011 independent A71-29789 landing monitor GAVBILOV! V- A. [SAE PAPER 7104431 A71-28324 Visibility in the atmosphere GOELIB, S. Ma [ AD-7195021 N71-24375 Experimental aeromechanics GEISELEABT, .E. A71-29524 A comparison of pilot performance using a center GEAIVOBOBSKII, V. A. stick vs side arm control configuration Approximate method of calculating the aerodynamic Technical report, Play - Oct. 1968 characteristics of a wing in the presence of a [AD-720846 ] N71-25846 cylindrical body GEBIB, J. A71-30264 The dynamical behaviour of a flexible cable in a GBABTHAM, W. D. uniform flow field Control considerations in severe turbulence A71-31026 871-29772 GEBDES, E. E. GBEEB, E. G. Factors affecting handling qualities of a lift- Traversing probe Patent fan aircraft during steep terminal area [NASA-CASE-XFR-O2007] N71-24692 approaches GBIFFITH. C. D. [AHS PREPRINT 544) A71-31101 Synthesis of an electromechanical control system for a compound hingeless rotor helicopter PERSONAL AUTHOR INDEX HOLLEMAN. E. C. [AHS PREPRINT 5361 A71-31096 HABKONEN, D. L. GRIGORZV. E. S. Static tests of a 0.7 scale augmentor wing flap Motion of a viscous gas in sectorial gas bearings for the modified C-8A airplane - Test results A71-30227 and analysis GBOSSIAN. E. [ NASA-CR-1143153 N71-26416 A numerical procedure to calculate the inviscid HARBSE, D. T. flow field about a space shuttle orbiter Acoustic liner design from a fluid mechanics traveling at a supersonic/hypersonic velocity approach N71-26056 [AIAA PAPER 71-7571 871-30791 GBOTH. H. W. HBBT-SKITH. 1. J. Nozzle performanceaeasnrement on underwing Filamentary composite reillforcement of metal nacelles on an F-106 utilizing calibrated structures engines and load cells A71-28168 TAIAA PAPER 71-6811 871-30745 HABTWIG, L. W. GRUND; E. Results of high-speea flight research with the Predicting airframe/exhaust nozzle interactions at high performance UH-1 compound helicopter transonic Each numbers [AES PREPRINT 5701 A71-31111 [AIAA PAPER 71-7201 A71-30771 HARVEY, D. W. GBUNNET. J. 1. The combustion system for the Olympns 593 Concorde Designing jet aircraft wind-tunnel test programs engine with propulsion system simulation A71-28740 A71-30605 HARVEY, J. K. GBUZDEV. V. N. The Imperial College graphite heated hypersonic Role of turbulence intensity during the mixing of wind tnnnel plane isothermal slipstreams in an enclosed flow [ IC-AERO-71-01 ] N71-24675 A71-28962 HAUPT. C. G. GUBAIDULLIN, A. U. The measurement of temperatures and radical Problem of gear link design for grinding-belt concentrations in hiah-temperature. flowina-aas__ machines streams A71-28943 A71-28758 GUENTEBT. D. C. EAUSEB. E. A. Predicted performance of a 15-80 kUe reactor coated columbium for gas turbine engine Brayton power system over a range of operating application conditions [ SAE PAPER 7104601 A71-28334 [NASA-Tfl-X-678331 N71-24690 BEFEB. 6. GUITTON. D. E. An investigation of a wave-rider at low Reynolds Experimental study of the thermal wake numbers interference between closely spaced wires of an [DLB-PB-70-46] 871-24500 X-type hot-wire probe BEPEEB, 3. 8. A71-31022 Lee side heating investigations. Part 1 - GURIASHKIN. 1. P. Experimental lee side heating studies on a delta Ballistic wind tnnnel for drag measurements on wing orbiter models during free flight at snpersonic speeds N71-26060 A71-29201 HEIIBOLD, E. I. GUSEV. V. N. Synthesis of an electromechanical control system Similarity and variation of the aerodynamical for a compound hingeless rotor helicopter characteristics in the transition region at [AHS PREPRINT 5361 871-31096 hypersonic flow velocities HELLYAB, K. 1. 871-29172 VTOL in the urban context rAIAA PAPER 71-5071 A71-29549 EEBMAN, S. H Altimeter-airspeed and Each number transducers HACKETT. J. E. A71-30322 Vortex wakes behind high-lift wings HEBSKIND, E. E. A71-28033 A circular slot aperture with arbitrary HAPPIER, P. polarization for aerospace applications Predictive calcnlations of attenuation of A71-31075 absorbing ducts adaptable to bypass jet engines EEWES. E. V. A71-30522 ALPk - A survey of airport fire and rescue EAINLINE, B. C. facilities, 1971, North America Powered wheels - A concept for parking and taxiing N7 1-26466 of commercial transport airplanes HICKKAU, K. E. [SAE PAPER 7104461 871-30530 Bigh entrainment ejector design HALL, G. E. [ASKE PAPER 71-PE-341 A71-29469 Recirculation characteristics of a small-scale HITCH, H. P. Y. VTOL lift engine pod Design for lateral gusts [ NASA-CR-17741 871-25397 A71-29786 HALL, 0. J., JB. HLUCHAI, S. A. Theoretical and experimental analysis of acoustic Altimeter-airspeed and Mach number transdncers linings for ducts with flow A71-30322 [AIAA PAPER 71-731: 871-30778 EOCKHAK, G. A. HALLIDAY. A. S. Plush mounted aeronautical antenna Part 4 - Xeasurements of lift, drag, and pitching 871-31043 moment on a series of three delta wings HOEPS, K. W. N71-24573 The economics of snbsonic transport airplane EAMES, D. P. design, evaluation and operation Strain gauge torquemeters for use in helicopter [ SAE PAPER 7104231 A71-28310 transmission systems EOEGKAN, E. [AHS PREPRINT 5631 A71-31110 Measurement of a helicopter's gyro displacements HAIILTON, E. K. in some different flying conditions Correlation of space shuttle applicable [ POA-Z-C-2356-49-/72/] N71-26567 experimental hypersonic aerodynamic HOHEUEISEB. K. H. characteristics with theory The method of multiblade coorainates in the linear N71-26066 analysis of lifting rotor dynamic stability and BABEL, P. gust response at high advance ratio Use of miniaturized microphones in the study of [AHS PREPRINT 5121 A71-31083 the sound radiation of vibrating modes in EOLLEIAN. E. C. rotating machines In-flight evaluation of the lateral handling of a A71-30517 four-engine jet transport during approach and E-7 EOLLIDAY. 6. PEBSOBAL AUTEOE IBDEX landing ILICEEV, V. D. [ NASA-TN-D-63391 871-25537 Allouance for the operational experience in the BOLLIDAY, 6. determination of the lifetime of a structure Development testing of the L-1011 independent A71-29231 landing monitor ILIPP, K. U. [SAE PAPER 7104431 A71-28324 A comparison of minimum time profiles for the EOLLIMAB, E. J. F-104 using Balakhrishnan's epsilon technique Radio frequency utilization in the bands of and the energy method principal interest for aeronautical satellites A71-28831 [NASA-TM-X-65527] 1171-25920 ILIBSKAYA, 6. B. HOLLIBGHOBTH. D. on transonic flow perturbations caused by Development and service experience of the PT6A vorticity reduction gearbox B71-25714 [SAE PAPER 7104331 A71-28318 ILLG, 8. EOLLOUAY, J. F. Filamentary composite reinforcement of metal coated columbium for gas turbine engine structures application A71-28168 [SAE PAPER 7104601 A71-28334 INOUYB, H. EOOPEB. Ef. E. An evaluation of theories for predicting turbulent The Boeing Model 347 advanced technology skin friction and heat transfer on flat plates helicopter program at supersonic and hypersonic Hach numbers [AHS PREPRINT 5711 A71-31112 A71-29868 HOPKIBS. E. J. IBTBIEBI. P. P. An evaluation of theories for predicting turbulent static and dynaatic aerodynamics of space shuttle skin friction and heat transfer on flat plates vehicles at supersonic and hypersonic Mach numbers N71-26062 A71-29868 IRODOV. E. D. HOEIUCEI, SI Longitudinal stability criteria for a ground- Gas turbine combustors effect airplane [ NAL-TR-2081 871-26298 A 7 1- 2 9 2 2 8 EORLOCK, J. E. IEOBS, E. P., JB. A comparison of the performance of three model Energy state approximation and minimum-fuel axial flow turbines tested under both steady and fixed-range trajectories pulse flow conditions A71-30609 A71-29819 IUBUSOV. F. s. HOVIS. U. A. Problem of gear link design for grinding-belt Optical properties of clouds machines N71-25260 871-28943 EOHABD. E. U. IZIAYLOV, A. A. Flight systems, flight deck display and automatic Aviation and astronautics in the USSR flight control [ NASA-TT-F- 131421 N71-25024 A71-29132 BOHETE, M. S. Advanced composite cost comparison J A71-29656 JACKSOB, C. E. ESU. C. C. Future prospects for air transport - Long haul air On flow past a supercavitating cascade of cambered transport blades A71-30161 [ ASME PAPER 71-FE-61 A71-29448 JACQUES. J. EUPPMAN, E. E. Influence of the presence of a plane on the The dynamical behaviour of a flexible cable in a measurement of line-containing spectra uniform flow field A71-30523 A71-31026 JABOTA, 1. S. EUPPORD. D. D. 1 comparison of the performance of three model The economics of subsonic transport airplane axial flow turbines tested under both steady and design, evaluation and operation pulse flou conditions [SAE PAPER 7104231 A71-28310 A71-29819 EUGEES, J. E. JANSEN, H. AN/ASN-86 Inertial Navigation Set Compressor sensitivity to transient and distorted [AHS PREPRINT 5331 A71-31094 transient flows EUBT, J. 1. [AIAA PAPER 71-6701 A71-30734 Shock interference heating and density ratio ,JEFPEEIS, R. P. effects. Part 2 - Hypersonic density ratio Evaluation' of fuel flowmeter instrumentation Final effects report, 5 Bug. - 20 Oct, 1970 N71-26058 [ AD-7192801 871-24479 EYNES. C. S. JEPPERY. E. W. Factors affecting handling qualities of a lift- The Imperial College graphite heated hypersonic fan aircraft during steep terminal area wind tunnel approaches [ IC-AERO-71-01 3 W71-24675 [AHS PREPRINT 5441 A71-31101 JENKIBS, J. 0. 1. Interface circuits drive high-level suitches from low-level inputs I A71-28910 IANKO, A. K. JEROME. P. E. A solution for an axisymmetrical three- component Experimental study of the thermal wake flow of incompressible viscous fluid interference between closely spaced wires of an A71-30855 X-type hot-wire probe IAUSEEV, K. G. A71-31022 Problem of gear link design for grinding-belt JOGLEKAE. E. E. machines A model for the wake geometry of the lifting rotor A71-28943 in forward flight and an evaluation of the IBBAGIIOV. S. G. sensitivity of computed blade loads to the wake Assessment of measurement errors in the testing of geometry axial-flow compressors and turbines N71-26583 A71-28582 JOHNSEN, E. L. Gasdvnamic verification calculations of multistaqe Predicted performance of a 15-80 kile reactor axial-flow compressors on a digital-computer Brayton power system over a range of operating A71-28584 conditions [ NASA-TM-X-67833 3 N71-24690 B- 8 PERSONAL AUTBOB INDEX KULAGIB, I. I. JOHNSOB. 8. A- KLEIBELBTI G. W. Airbone data acquisition system for atmospheric Contemporary approach to commercial powerplant and meteorological research development A71-30311 [SAE PAPER 7104493 871-28327 JOBBSON, IT. KLINKBLB, P. Application of a lifting-surface theory to the Design of a linear array of blade antennas for calculation of helicopter airloads aircraft-satellite communication [ABS PBEPBINT 510) A71-31081 A71-31062 JOBBSTON. J. P. KOBBYNSKI, 1. AB-568 vehicle development Experimental verification and application of a [ABS PREPRINT 574 ] A71-31115 method of calculation for the sound spectrum of jets on the ground and in the air A71-30524 K KOCHANSKI, K. E. KAAITABI, 6. E. Design integration - The key to effective engine Plow fields and aerodynamic heating of space condition monitoring shuttle orbiters [SAE PAPER 7104471 A71-30531 N71-26053 A systems approach to engine condition monitoring KAKHOVSKII, K. V. [AIAA PAPEB 71-6521 A71-30728 Effect of the penetrating ability of jets on the KOGAN. 1. N, peripheral nonuniformity of a gas temperature Similarity and variation of the aerodynamical field at the outlet of a gas turbine engine characteristics in the transition region at chamber hypersonic flow velocities A71-28971 A71-29172 KALLIS, J. 1. KOLGAN, V. P. Plowfields produced by multiple jets in a ByperSOniC flow around a delta wing supersonic stream A71-29189 [AIAA PAPER 71-7281 A71-30775 KOLKOV, V. G. KALBIZHENSKII, E. IA. Investigation of the vortex system of a helicopter Scanning systems for theraal viewers rotor [ AD-7198541 N71-25053 871-29235 KABLASBOV. A. V. KOMODA. PI. Fatigue strength of aircraft skin elements A model test on the hovering performance of jet affected by corrosion flapped rotor A71-278 19 [ NAL-TR-2111 N71-25396 KATZEN. E. D. KDNABSKI, 1. Static and dynamic aerodynamics of space shuttle Predicting airframe/exhaust nozzle interactions at vehicles transonic Mach numbers 871-26062 [AIAA PAPER 71-7203 A71-30771 KAYLOR. D. M. KONDO, J. Air passenger traffic in short-haul markets computer aided design of civil transport plane 871-26528 A71-30398 KAZIN. S. B. KONIABV, V, G. Some experimental results on lift fan noiE Approximate calculation of a certain class of reduction gliding trajectories [AIAA PAPER 71-7431 871-30784 A7 1-29185 KBANE. a. P. KOBOL, 0. 6. IPR hover for heavy lift helicopters with slung Differential method of manufacturing complex load precision fuselage parts [ AHS PREPRINT 540 3 A71-31097 A71-30267 KEDDIE. B. KOSTAREV, V. V. A note on the optimum averaging time of wind Use of weather radar for aviation information for conventional aircraft landings [ PMO-264-TP-148 ] N71-24394 A71-30394 KOSTEBIN, V. A. Some aspects of wind information required in the Influence of bypass of air behind the compressor landing of aircraft into a variable-area exhaust nozzle on the A71-30395 indices gas turbine jet engine KEELER, a. A. A71-28586 One operator's look at maintainability KRAFT, G. A. [SAE PAPER 7104321 A71-28317 Potential of methane fueled supersonic transports KELLY, a. A. over a range of cruise speeds up to Nach 4 A review of helicopter aerial problems [ NASA-TI-X-22813 N71-25384 A71-31048 KRASILSBCHIKOV, A. P. WMMIEBLING. P. Ballistic wind tunnel for drag measurements on A comparison of pilot performance using a center models during free flight at supersonic speeds stick vs side arm control configuration A71-29201 Technical report, nay - Oct. 1968 KBASNOPP, E. [ AD-7208461 871-25846 An experimental study of rectilinear jet-flap KERWIN, P. T. cascades Design point characteristics of a 15-to-80 kNe [ASIE PAPER 71-PE-141 871-29453 nuclear-reactor Brayton-cycle power system KRAUSE, 1. N. [iiASA-TU-X-67811] 371-24689 A review of the mass-flux probe KBOBOBBTKH, A. A71-29925 Parachute KBECHETNIKOV, IU. D. [ AD-7194801 N71-24351 Beat and mass transfer in the turbulent flow of a KICKS, J. C. chemically active gas in the manifolds of a Bigh frequency rake probes for inflight intake hydro-jet engine airflow distortion measurements A71-28589 A71-30321 KREJSA. E. A. KING. K. P. Blown flap noise research A piloted simulator study of a jet VTOL aircraft [AIAA PAPER 71-7453 A71-30785 in partially jet-borne flight KRUCKENBERG, H. D. [ARC-R/n-3647] 871-25065 Evaluation of American Airlines' B747 prototype KIRBY, J. C. AIDS Engine Uonitoring Program Day and night fire power of the Cheyenne [AIAA PAPER 71-6481 A71-30725 [AHS PREPRINT 5301 871-31091 KULAGIN, I. I. KLECKNBB, 8. P. Principles of the theory of aviation gas turbine Iilitary/commercial STOL transport commonality engines [ SAE PAFER 7104681 A71-28336 [ AD-71 99 131 171-25808 B-9 KULIKOHSKI, A- J. PERSONAL AUTHOR INDba WLIKOWSKI, A. J. 871-28745 En route speed control techniques LEGG. K. A71-28884 Aviation within the total transport system KUO, CI-C. 871-30165 Perturbation and harmonic balance methods for LEIBY. D. W. nonlinear panel flutter Technical report, 1' Design integration - The key to effective engine Dec. 1969 - 15 Mar. 1971 condition monitoring [NdSA-CR-111907] N71-25362 [SAE PAPER 7104473 A51-30531 KUBAIISHIE. T. A. A systems approach to engine condition monitoring Measurement of light pressure forces and of [AIAA PAPER 71-6521 A71-30728 aerodynamic forces acting on a body of complex LEMON, T. E. E. shape in a free-molecule flow measurements of static straios on titanium nnder A71-29155 rapid heating KUBTZ. A. D. A71-29833 The design and fabrication of transducers for the LEBAEB. J. measurement of fluctuating pressures from DC to Plug in relay - Panacea or Pandora's BOX over 100 KEz in jet engine testing 871-28841 A71-30324 LEVINSTEIA, K. A. KUSSMANN. A. Improved aluminide coatings for nickel base alloys Survey of different models for computing the flow Final report of a lifting rotor [NASA-CE-72863] N71-25454 [ DLR-MITT-70-19 3 N71-24489 LEHIS. A. Fuels for aircraft gas turbine engines A71-28754 L LEVIS, E. B.. I1 LADSON. C. L. Army helicopter performance trends Hypersonic aerodynamic characteristics of DL-4 [AHS PREPRINT 5001 A71-31076 lifting entry vehicle LIN, S. [ NASA-TI-X- 1994 ] N71-26354 Sonic-boom analog for investigating indoor LAFOBGE, S. V. acoustical waves Rotor stability derivatives determined from wind A77-30200 tunnel tests of an instrumented helicopter LITCBPOBD, G. 8. [AHS PREPRINT 5431 A71-31100 New developments in scanning bean landing guidance LAIAB, J. E. systems, part 2 Final annual report Effects of aeroelasticity on static aerodynamic [AD-7189721 N71-24555 derivatives LIUBIIIOV, V. V. N71-24707 Electrical power supply systems of airplanes and LAIHIOTTE, D. J. helicopters Airfield pavement condition survey, USNS Adak, A71-29525 Alaska LLOYD, J. E. [AD-7198891 N7 1-2560 4 Low Reynolds number turbulent flow in large aspect LAIBOUEIOU, J. ratio rectangular ducts Use of miniaturized microphones in the stedy of [ASME PAPER 71-PE-A] A71-29378 the sound radiation of vibrating modes -2 LOCKIAN, H. K. rotating machines Plow fields and aerodynamic heating of space A71-30517 shuttle orbiters LAIBOUBUE, A. C. 171-26053 The behavionr of the leading-edge vortices over a 1016. H. E. delta wing following a sudden change of Precipitation detector Patent incidence TNASA-CASE-XLA-26191 N71-26334 [ ARC-R/M-3 645 ] N71-24482 LOVE, E. S. LAUDSBEBG. T. J. Design of bodies for low drag and high performance An experimental study of rectilinear jet-flap in practical hypersonic fliqht cascades N71-24704 [ASME PAPER 71-FE-141 A71-29453 LUKASHOV, A. G. LAEIE. A. V. Problem of position determination of the neutral Phenomenon of vortex formation associated with the layer and critical curvature radius in waffle oblique flou past a rotor panels under purely elastoplastic bendihg A71-29217 A71-28940 LASKIU. A. S. LUKIB, I. I. Variable aerodynamic forces in a tnrbine stage Electrical power supply systems of airplanes and induced by a vane cascade in the wake of a. helicopters preceding cascade A71-29525 [ NASA-TT-P- 136311 171-25998 LUTSKII, V. LATCEAU. E. P. Stability and controllability of supersonic Vacuum heat treating of jet engine components aircraft, 1970 A71-28145 [ AD-7198041 871-25032 LAUGHBET. J. A. Stability and controllability of supersonic Analytical and experimental evaluation of aircraft, 1969 performance prediction methods applicable to [ AD-71 9 8031 N71-25049 exhaust nozzles Stability and controllability of supersonic [AIAA PAPER 71-7193 A71-30770 aircraft LAZZABIAO. L. [ AD-720740 1 N7 1- 26538. Aeronautical Institute of the University of Pisa - LuTTon, T. c. Activities of the 1960-70 decade- Projects United States Coast Guard evaluates hovercraft currently under way [AHS PREPRINT 5721 A71-31113 871-30822 LYSOV, 1. I. LEE, C. E. Problem of position determination of the neutral Design criteria for selection of aircraft electric layer and critical curvature radius in waffle power generation and distribution systems panels nnder purely elastoplastic bending [SAE PAPER 7104441 A71-28325 A71-28940 LEE, J. T. Conparison of thunderstorms over Oklahoma and Malaysia based on aircraft measurements M A71-29752 111. C.-Y. LEPEBVBE. A. E. Potential flow interaction between blade rows in Ignition theory and its application to the axial-flow compressors altitude relighting performance of gas turbine 871-28883 combustors B-10 PERSONAL AUTHOR INDEX MITCHELL, C. G. E. MACH, K. D. HAYBBEY, J. P. I. Systems aspects of augmentor combustion The behaviour of the leading-edge vortices over a instability delta wing following a sudden change of [AIAA PAPER 71-6971 871-30756 incidence BACK. J. C. [ ARC-R/U-3645 ] N71-24482 Evaluation of rotor controls designed for IAYES. A. E. increased safety Preliminary measurements and flow visualization [ ABS PREPRINT 5501 A7 1-31 102 studies of pressure fluctuations on space IACKEY. A. C. shuttle configurations The effects of parameter variation on inflight B71-24663 wind loading IC PADDEE. J. V. N71-24664 Aircraft noise type certification orientation IACPHEHSON. J. I. session - Lecture notes, supplement 2 Final Stratospheric turbulence and temperature change report measurements from the Coldscan program [HBC-TR-300-SUPPL-2] N71-26305 A71-29767 HC LEAN. 8. E. IADAN, S. The use of high intensity xenon lighting to The effect of flow direction on combined enhance US Army aircraft day/night conspicuity convective heat transfer from cylinders to air [ AD-7186391 171-24669 A71-28985 IC PHEBSON, A. IAHONEY, J. A piloted simulator study of a jet VTOL aircraft Fincap communication aerials in partially jet-borne flight A7 1-31 047 [ARC-R/H-3647] 1171-25065 IAIB, A. A. ICCONNELL, 1. J. Aerodynamic behaviour of bodies in the wakes of Army/Navy operational evaluation of offshore other bodies discharge of containerships A71-29265 [ABS PREPRINT 5731 871-31114 IAISE, G. ICCROSKEY, A. J. Lee side heating investigations. Part 2 - Lee Detailed aerodynamic measurements on a model rotor side heating iwestigations of simple body like in the blade stall regime configurations [AXS PREPRINT 5211 871-31087 N71-26061 ICIABUS, E. 1. P. EAKABEVSKII. A. I. Development of an approach and landing system with First born of Soviet aviation science special reference to the effects of turbulence [AD-719802] N71-25048 A71-29773 IALCOLI! G. N. NCPHEBSON, A. Static and dynamic aerodynamics of space shuttle Comparison of thunderstorms over Oklahoma and vehicles Malaysia based on aircraft measurements N71-26062 A71-29752 NABCONI. P., JB. IELLENTHIN, J. A. A numerical procedure to calculate the inviscid Static and dynamic aerodynamics of space shuttle flow field about a space shuttle orbiter vehicles traveling at a supersonic/hypersonic velocity N71-26062 N?’ -26056 IENGBS. I. J. IABKOPOIJLOS, D. Precipitation detector Patent A microstrip p.i.n. diode controlled I-band [NASA-CASE-XLA-2619] 871-26334 digital phase shifter IEBLE, I. A71-31055 High-speed flash photography of jets and study of IABSHALL, R. 1. noises of aerodynamic origin Combustion instability in turbojet and turbofan A71-28767 augmentors HBBBITT. E. J. [AIAA PAPER 71-6981 A71-30757 Day and night fire power of the Cheyenne MARVIN. J. G. [AHS PREPRINT 5301 871-31091 Flow fields and aerodynamic heating of space IBTZGEB, F. B. shuttle orbiters Results of initial prop-fan model acoustic N71-26053 testing. Volume 2 - Appendices B thru F IASEK, E. V. [ NASA-CR-111842-21 N71-25784 An analysis of predicted space shuttle Results of initial prop-fan model acoustic temperatures and their impact on thermal testing. Volume 1 - Discnssion protection systems [ NASA-CR- 11 1842-1 1 N71-25785 871-26054 IIHALCEA, E. IASSEB. C. C. Evaluation of flight measurements and the plotting Nuclear powered air cushion vehicles for of loading collectives transoceanic commerce N71-24389 [ NASA-TU-X-2293 ] N71-25783 IIKELADZE, V. G. IATEEB. G. G. Investigation of the aerodynamic characteristics Plow fields and aerodynamic heating of space of elevons on low-aspect wings shuttle orbiters A71-29190 N71-26053 EILELLI, R. J. BATHER. G. K. IPR hover for heavy lift helicopters with slung Flight studies of clear air turbulence - The load current position and.further research needs [ AXS PREPRINT 5401 A71-3 1097 A71-29753 HILLER. G. P. IATSUOKA, K. Numerical evaluation of the downwash integral for On separation control of flow along curved wall by a liftinq rectanqular planform various forms of jets or suctions - Controlling [ NPL-HA-501 871-24483 characteristics and comparison of effects .IILNE. E. D* A71-29433 The strongly controlled aircraft IATTHEAS, P. A. A71-31024 A microstrip p.i.n. diode controlled L-band IIBANOV, A. D. digital phase shifter The Yak-40 aircraft flight test procedures A7 1-3 1055 A71-29911 EAOLL, D. J. IITCEELL. E. A. Aerodynamic behaviour of bodies in the wakes of Design tradeoffs for HP and synchronous satellite other bodies data collection systems 1171-29265 A71-30900 IAVBIPLIS, P. IITCEELL, C. 6. B. Aerodynamic research on high lift systems Some measured and calculated effects of runway A71-29910 unevenness on a supersonic transport aircraft 8-11 IIOIBABD, J. PERSONAL AUTHOB IBDEX A71-30305 BASYBOV, 1. K. UOIBABD, J. Determination problem of sound lilait expenditures Fluctuation of sound pressures created by a fan in per parameter unit in civil transport aircraft a very low speed subsonic wind tunnel test design stream /0.10 less than V less than 20 m/sec/ A71-28945 A71-30526 BAZABOV, G. I. UOOBE. S, E. A solution for an axisymmetrical three- component 'Safe Weigh' - An accurate and economical on board flow of incompressible viscous fluid weighing system A71-30855 A71-30320 BAZABOVA, 1. P. II0BA.A. J. F. fleasurement of light pressure forces and of GO/NO-GO engine tester aerodynamic forces acting on a body of complex A71-30327 shape in a free-molecule flow IIOBAB. W. P. A71-29155 The use of simulation to promote safety and BAZABYCHEV. A. P. economy in flying training Research study of optimal treatment routines [ SAE PAPER 7104751 871-28340 applicable to an automated orifice-making Development of an individualized ground training process program for DC-10 flight crews A71-28941 [SAE PAPER 7104721 A71-30538 HELSEH. U. De IIORELLI. P. Theoretical and experimental analysis of acoustic Elevator-induced manoeuvring loads from the linings for ducts with flow standpoint of airworthiness requirements for [AIAA PAPEB 71-731 1 A71-30778 sailplanes NEVRIUEV, V. IA. 871-29256 Differential method of manufacturing complex IORETTI, G. precision fuselage parts A numerical procedure to calcnlate the inviscid A71-30267 flow field about a space shuttle orbiter BEWIIAB. 1. J. traveling at a supersonic/hypersonic velocity AEea navigation systems and displays N7 1-26056 [SAE PAPER 7104571 A71-30533 UOBGAH, G. nIcHoLLs, J. I. Avionics interference prediction model fleasurements of stratospheric airflow and clear [AD-718997 3 W71-24357 air turbulence, up to 63000 ft. over and IOBINO. 1. downwind of mountainous terrain Perturbation and harmonic balance methods for A71-29755 nonlinear panel flutter Technical report, 11 nIcoLo, G. B. Dec. 1969 - 15 Bar. 1971 Conceptual lines for the definition of an [NASA-CR-l11907] N71-25362 aeronautical project IIOBISSET, J. A71-30824 The 'flercure' - The first aircraft of a new BIKOLAEV, A. V. generation Plow in the inlet section of a supersonic diffuser A71-29276 channel when the boundary-layer is Separated by IIOBRISSEY, E. G. a shock wave Stratospheric turbulence and temperature -hauge 871-29175 measurements from the Coldscan program BIKOLAEV. V. S. A71-29767 Wind-tunnel simulations of viscous hypersonic BOBSS. n. n. flows Air turbulence - Hidden and revealed A71-29224 A71-29768 BIKOLSKII, A. A. UOSES, E. J. similarity laws for three-dimensional steady Electronic Engine condition Analysis System separated liquid and gas flows past bodies [SAE PAPER 7104481 A75-30532 A71-29169 moxon, E. B. BIKOLSKII, IU. V. The evolution of the RB 162 combustion system for Experimental study of heat transfer on spheres and V.T.O.L. applications sharp cones in a rarefied hypersonic qas flow A71-28742 871-29176 IUELLER, E. J. BOBUEILEB, T. E. P. Absorption effect on VHF propagation between The role of heat conduction in leading edge synchronous satellite and aircraft Summary heating theory and experiment report [ARC-CP-11261 N71-24446 [NASA-TE-X-65507] N71-24914 A new series of low-drag aerofoils IUELLER, K. [ ARC-R/H-3618] 871-24498 Baggage conveyor system in the New Frankfurt NOOBAN, J. U. terminal Aerospace materials selection and verification of 871-29312 structural designs developed by means of high BUGLER, S. W. velocity impact testing Precipitation detector Patent A71-29642 [NASA-CASE-XLA-2619] N71-26334 BOBSTEB, E. E. IIUHLSTEIB, L., JB. Combustion and heat transfer in gas turbine Buffet response of space shuttle launch systems, Proceedings of an International configurations as determined by tests of an Propulsion Symposium. College of Aeronautics, aeroelastic model Cranfield, Beds., England, April 15-17, 1969 N71-24662 A71-28739 ULWRO, A. 1y. Some observations of the atomizing characteri9tics A high speed airborne scanning aerial with matched of air-blast atomizers patterns A71-28756 A71-31036 BOSEK, S. 1. IIUZIO, 1. J. Shuttle airbreathing propulsion The role of kinetics in engine emission of nitric [ AIAA PAPER 71-6621 A71-30731 oxide novozHILov,. v. v. 871-30454 Calculation of three-dimensional structures. Number 13 N A71-30888 BARDIZZI, 1. E. Optimal and suboptimal control synthesis for 0 minimum time VTOL transition oconnoB, s. J, 871-30799 Feel augmentation and sensitivity control in high speed helicopters E-12 PERSOBAL AUTHOR INDEX PRESZ, U.. JR. [AHS PREPRINT 5421 871-31099 method /incompressible fluid/ ODGERS, J. A71-30443 Some considerations of the measurement of PBBELSHlEIU, B. KH. temperatures within aircraft combustion Investigation of the iaeal cycle of a chambers, using a calorimetric probe continuouscombustion gas turbine with stepwise A71-28757 heat release, overexpansion cycle OKA, T. A71-28583 A model test on the hovering performance of jet PEREPUKEOV, V. A. flapped rotor Similarity and variation of the aerodynamical [ NAL-TR-2113 N71 - 2539 6 characteristics in the transition region at OLEARY, C. 0. hypersonic flow velocities Flight tests to investigate the problems of steep A71-29172 approaches by STOL aircraft PEBRETT, E. B., JR. [ARC-CP-1138] 871-25050 The National Airport System Plan - Its history and OLSEN, U. A. its potential Bloun flap noise research [SAE PAPER 7104141 A71-28306 [AIAA PAPEH 71-7451 A71-30785 PERDLLI, 1. OOSTHUIZEN, P. E. Use of miniaturized microphones in the study of The effect of flow direction on combined the sound radiation of vibrating modes in convective heat transfer from cylinders to air rotating machines 871-28985 A71-30517 OTABI. K. Preliminary results in a study of the infrared Use of weather radar for aviation emission of a hot jet [ UNO-264-TP- 1481 N71-24394 A71-30520 OIEN, E. H. PERVDSHIN, G. E, Electrical and physical nature of microbial Experimental study of heat transfer on spheres and membranes implicated in aircraft fuel quantity sharp cones in a rarefied hypersonic gas flow probe malfunction A71-29176 [SAE PAPER 7104391 871-28321 PETERSON, V. 1. Static and dynamic aerodynamics of space shnttle vehicles P PETROV, K. P. N71-26062 PACE. C. W.. JR. Airport certification Investigation of means of increasing the lift/ [SAE PAPER 7104131 A71-28305 drag ratio of conical bodies PADFIELD. G. D. A71-29183 The strongly controlled aircraft PHILLIPS, 1. H. A71-31024 Gust alleviation PAGLINO. V. 1. 171-24709 Forward flight performance of a coaxial rigid PIABULLI. V. J. rotor A study of the effects of nonuniform swash- plate CARS PREPRINT 5241 A71-31090 stiffness and out-of-blade track on rotor PAPPAS, C. C. dynamics and stability Flow fields and aerodynamic heating of space [AES PREPRINT 5111 A71-31082 shuttle orbiters PICKBTT. G. F. 871-26053 The prediction of the spectral content of PARKER. B. J. combination tone noise Optimal and suboptimal control synthesis for [AIAA PAPER 71-7301 A71-30777 minimum time VTOL transition PIERCE, J. A. 871-30799 The development of long-range hyperbolic PARSONS, E. J. navigation in the united States Supersonic combustion research techniques in a A71-30711 hypersonic shock tunnel PIETERSEN. 0. B. 1. A71-29578 Design of a linear array of blade antennas for PATRL, R. P. aircraft-satellite communication Experimental study of the thermal wake A71-31062 interference between closely spaced wires of an PLAHOUSKI. S. C. X-type hot-wire probe Traversing probe Patent 871-31022 [ NASA-CASE-XFR-02007 3 N71-24692 PAUL, U. PODOBIN, V. P. Structural stability investigations of the Ballistic wind tunnel for drag measurements on helicopter VFW-83 models during free flight at supersonic speeds 871-24390 A71-29201 PAULLIN. E. L. PONTANO, B. A. Aviation and environmental quality - A survey of Interference criteria between space-borne and the SAE/DOT Conference on aircraft and the earthbound aeronautical services Environment 871-28873 [AIAA PAPER 71-7291 A71-30776 PORTER, 8. E. PADLSEN, U. E. Salt driers assure really dry fuel to aircraft Development of airborne remote clear air [SAE PAPER 7104403 A71-28322 turbulence, CAT, detection equipment POWELL, C, 8.. JR. A7 1-29765 Instrument for measuring the dynamic behavior of PEARSON, E. D. liquids Patent A comparison of the performance of three model [ NASA-CASE-XLA-055411 N71-26387 axial flow turbines tested under both steady and POYNTON, 3. P. pulse flow conditions Automatic inspection. diagnostic and prognostic A7 1-2981 9 systems for Army aircraft PEASLEE, J. C. [AIAA PAPER 71-6491 A71-30726 Comparison of STOL design criteria for commercial POPSER, J. E. and military transport aircraft The evolution of the RB 162 combustion system for [SAE PAPER 7104651 A71-30536 V.T.O.L. applications PECHOTA, A. P. A. A71-28742 Game theory and the use of game planning PRATT, K. G. techniques for aircraft evaluation Response of flexible airplanes to atmospheric A71-28880 turbulence PELISSIER. R. N71-24708 Vortex theory €or a propeller of constant PRESZ. U.. SR. aerodynamic pitch and study of the wake Predicting airframe/exhaust nozzle interactions at confiquration with the aid of the smoke trail transonic Nach numbers B-13 PRIDE, R. A. PERSONAL AUTHOR INDEX [AIAA PAPER 71-7203 871-3077 1 tunnel tests of an instrumented helicopter PRIDE. R. A. [AHS PREPRINT 5431 A71-31100 Filamentary composite reinforcement of metal ROI, P. E. structnres Airbreathing nuclear propulsion - A new look A71-28168 A71-29930 PBIBZ. R. Airbreathing nuclear propulsion, a new look Determination of the lifetime of helicopter [ NASA-TM-X-67837 ] N71-25524 components Nuclear powered air cushion vehicles for N71-24386 transoceanic commerce PUGACHEQ. A. I, [ NASA-TB-X-2293 3 871-25783 Technical maintenance of aircraft ROIABCHUK, V. N. 1. AD-7203661 N71-25955 Aircraft materials science and treatment of PUTEOFF. R. 6. materials Freliminary impact speed and angle criteria for 871-29529 design of a nuclear airplane fission product ROSE. J. F.. JR. containment vessel Beasurement and analysis of C-SA interior acoustic [ NASA-TB-X-2245] N71-25411 environments during flight operations Final PYSHNOQ, V. S. report, Jul. - Bug. 1970 Principal characteristics of aircraft flight [ AD-7197461 N71-25060 mechanics ROSEN, 6. A71-29043 Prop-Fan - A high thrust, low noise propulsor [SAE PAPER 7104701 A71-28338 ROSS, E. U., JR. Q A general theory of parachute opening QUEIJO, 1. J. [ AD-7 19698 3 871-24433 Methods of obtaining stability derivatives ROSS, J. A. N71-24703 The economics of subsonic transport airplane QUICK, J. E. design, evaluation and operation A B.A.C. view of Q/STOL [ SAE PAPER 7104233 A71-28310 A71-30 163 ROSS, P. A. Experimental correlation of installation effects for inlet/airplane integration R [AIAA PAPER 71-7591 A71-30792 BADCHENKO, A- I. ROSSIAN, B. E. Fatigue strength of aircraft skin elements A new concept- UCAT - ultra Compact Airport affected by corrosion Terminal A71-27819 871-29313 RAINBY. A. 6. ROTSHTEIB, A. IA. Control considerations in severe turbulence Beasurement of geomagnetic components from moving 871-29772 platforms RANSOBE. B. K. A71-28249 STOL - An asset for lanhattan ROUILLER, P. [AIAA PAPER 71-5081 A71-29550 Some considerations of the measurement of RAY. V. A. temperatures within aircraft combustion Numerical evaluation of the downwash integral for chambers, using a calorimetric probe a lifting rectangular planform A71-28757 [ NPL-MA-90 3 N71-24483 ROBE. B. E. BEIBHABT. p. A- Development progress on CF6 engines Propulsion testing from the aircraft [SAE PAPER 7104211 A71-28308 manufacturers’ point of view ROUE. I. [SAE PAPER 7104501 A71-28328 Development of high-response data analysis aids BICHIRDSON, C, S, for inlet-engine testing The night rescue terminal navigation problem A71-28032 [AAS PREPRINT 534) A71-31095 RUDY, D. E. RICEilRDSOB, R. Effect of angle of attack on boundary-layer Yankee escape system transition at Mach 21 A7 1-2 9383 A71-29887 RICHTER, 6. BUIPORD, K. Preliminary results in a study of the infrared Factors affecting fuel control stability of a emission of a hot jet turbine engine and helicopter rotor drive system A71-30520 [AAS PREPRINT 5601 A71-31107 EIDER, C. K. BunmL, K. G. Measurement of extreme mechanical turbulence The costs/reliability relationships of development during low level flights by Mirage A3-76 testing and demonstration A71-29756 [ SAE PAPER 7104521 A71-28330 BIECKE. 6. T. RUSSELL. U. Combustion instability in turbojet and turbofan From automatic landing to Category I11 augmentors [SAE PAPER 710441 J A71-28323 [AIAA PAPER 71-6981 A71-30757 BYAN, K. H. RIEDIBGER, 1. A. Evaluation of coated alloys for turbine components The role of aircraft in the intraurban of advanced gas turbine engines transportation. system for the Detroit A71-29635 metropolitan area BYZHIBSKII, D. A. [AIAA PAPER 71-5041 A71-29548 Aircraft materials science and treatment of BOABTBEE. B. materials The flight test instrumentation installation for A71-29521) the Concorde SST RZEAVIB, IU. A. A71-30055 Assessment of measurement errors in the testing of ROBINSOB, P. R. axial-flow compressors and turbines ALPA - A survey of airport fire and rescue ~71-2a582 facilities, 1971, North America N71-26466 ROBINSOB. Re C. S Preliminary measurements and flow visualization SADLEB. S. 6. studies of pressure fluctnations on space A method for predicting helicopter wake geometry, shuttle configurations wake-induced flow and wake effects on blade N71-24663 airloads ‘3BTERT, R. E. [ABS PREPRINT 5231 A71-31089 Rotor stability derivatives determined from wind E-14 PERSOHAL AUTHOR INDEX SNESEKO, I. I. SAITO, T. SBUEBOV, V. 6. Gas turbine combustors Effect of airstream-mechanical propellant [ NAL-TR-208'J N71-26298 atomization on the carbon deposition rates in a SALISBURY. M. If. gas-turbine engine combustion chamber Some effects of designing for increased safety in A71-28970 turbulence SETZE, P. C. A71-29777 VTOL propulsion system development SALTANIS. P. B. [ABS PREPRIBT 5621 A71-31109 . Preliminary development of an active transmission SEAP. K. T. isolation system Aerodynamic forces on autocabs, appendix 11 [AHS PREPRINT 514.1 A71-31085 N71-26129 SALTZIAN, E. J. SEAW, R. Traversing probe Patent A comparison of the performance of three model [NASA-CASE-XPR-02007] N71-24692 axial flow turbines tested under both steady and SANFORD. R. H. pulse flow conditions HLH primary flight control system design A71-29819 [AHS PREPRINT 5031 A71-31079 SEAY. E. P. SANTIHI, P. GO/NO-GO engine tester Influence of structural nonlinearities on panel A71-30327 flutter SEILOV, A- A. 871-30825 Irregular optimal trajectories of a spacecraft SATO, fl. during flight in the atmosphere On separation control of flow along curved wall by A71-29229 various forms of jets or suctions - Controlling SHIflA, F. characteristics and comparison of effects Patigne of aircraft structures A71-29433 All-29434 SAVIH, V. S. SHORE, C. P. Aircraft anti-icing system - Principles of design Application of recent panel flntter research to and test methods the mace shnttle. Part 2 - Influence of edue [ AD-7199221 N71-25622 clips' and flow angularity SAVINOV, A. A. N71-24661 Interference between a wing and a jet in cross SEULGA, V. F. wind Aircraft refractometer A71-29207 All-28250 SAWYER, R. F. SHUPE, 8. K. The role of kinetics in engine emission of nitric A stability and control theory for hingeless oxide rotors A71-30454 [AHS PREPRINT 5411 A71-31098 SCHEUCH. G. SIDDOH. T. E. Roissy-en-Prance new major airport for Paris A miniature turbulence gauge utilizing aerodynamic A71-29309 lift SCHLADER. A. P. A71-28158 Some considerations of the measurement of SIMAKOV, 1. I. temperatures within aircraft conbustion Selection of a cam profile for the computing- chambers, using a calorimetric probe resolving unit of an altimeter A71-28757 A71-28938 SCHMID. S. G. SIIPSON, A. General aviation, naval aviation and congestion Wake induced flutter of circular cylinders - with an example from southern California flechanical aspects [ AD-71 9 906 3 N71-25621 A71-31021 SCHMIDT. C. SIflPSON, J. A. Preliminary results in a study of the infrared An attack helicopter weapons delivery computer emission of a hot jet [AHS PREPRINT 5311 A71-31092 A71-30520 SINDZINGRE. fl- SCHMIDT. G. French research on metallic matrix composites Fuel-optimal landings of jet-supported VTOL 871-30473 aircraft SIBIGNABO, 1. A. A71-29281 Acoustic liner design from a fluia mechanics SCHNEIDER, A. approach Radio frequency utilization in the bands of [AIAA PAPER 71-7571 A71-3 079 1 principal interest for aeronautical satellites SKELTOB, 6. B. [ NASA-TB-X-655271 N71-25920 Gust effects on V/STOL aircraft SCHUL'PZ. R. 1. A71-29775 Energy state approximation and minimum-fuel SLATTER, H. V. fixed-range trajectories Flight tests to investigate the problems of steep A71-30609 approaches by STOL aircraft SCBUMACHER, E. [ ARC-CP-11381 N71-25050 Dynamic testing of helicopter components SMITH, E. G. N71-24388 Lift ratings of V/STOL. propulsion units SCOTT. J. A. [SAE PAPER 7104711 A71-30537 Microbiological contamination of aircraft fuel SMITE, E. G. tanks - Airframe considerations size effects on the design of large rotor systems [SAE PAPER 7104381 A71-28320 [AHS PREPRINT 5521 A71-31104 SEEGMILLER. E. 1. SMITE, E. J. Flow fields and aerodynamic heating of space A comparison of minimum time profiles for the shuttle orbiters P-104 using Balakhrishnan's epsilon technique N71-26053 and the energy method Shock interference heating and density-ratio A71-28831 effects. Part 1 - Plow field visualization, SMITE, 1. R. thermocouple measurements, and analysis Airbone data acquisition system for atmospheric N71-26057 and meteorological research SELLEREITE, B. K. A71-30311 Powered wheels - A concept for parking and taxiing SMITE, P. E. of commercial transport airplanes Atmospheric temperature deviations from the [SAE PAPER 7104463 A71-30530 International Standard and its effect on SELLERS. T. B. barometric altimeters Consideration of Reynolds number simulation for A71-30323 subsonic shuttle tests SIIESEKO, I. I. N71-26065 The Yak-40 aircraft flight test procedures a-15 SOKOLOV, V. I. PEESOBAL AUTEOB INDEX A71-29911 CARS PEEPRINT 5601 A71-31107 SOKOLOV. V. I. STEPKA, P. S. The assembly of gas turbine aircraft engines Analyses of cooled turbine airfoil COUfigUratiOnS /selected chapters/ at conditions of supersonic flight [AD-7198233 871-25209 [ N ASA-TH-X- 178 2 1 N71-26355 SOKOVISEIB. IU. A. STEUAET, A. U. Plane jet of a conducting fluid in a slipstream Development and service experience of the PT6A A71-29610 reduction gearbox SOBBEBOBU. U. G. 0. [SAE PAPER 7104331 A71-28318 Results of high-speed flight research uith the high performance UR-1 compound helicopter STEUABT.Shuttle U. airbreathingL. propulsion [ABS PBEPRIBT 5701 A71-31111 [AIAA PAPER 71-6623 A71-30731 SOPEB. I. J. STICKLE. J. W. Plug in relay - Panacea or Pandorals BOX Direct lift control system Patent 871-28841 [BASA-CASE-LAE-10249-1] N71-26110 SOBOKA, B. 0. STOCKEAB, J. A flou about a low-aspect-ratio delta wing at Study of visible exhaust smoke from aircraft jet large angles of attack engines 871-25282 [SAE PAPER 7704281 A71-28314 SOTEEBAN, A- STOUT, E. G. Some combustion aspects of plenum chamber burning The role of aircraft in the intraurban A71-28743 transportation system for the Detroit SOUBDBABAYAGAB, S. metropolitan area Effect of axial velocity variation in aerofoil [AIAA PAPER 75-5041 A71-29548 cascades STRAELE, U. C. A71-28467 On combnstion generated noise SPAIYOL, B. E. 1. [AIAA PAPER 71-7351 A71-30780 Areas of grouth in air transport STRABZ, D. A71-30160 Lou stratus at Embakasi Airport Nairobi SPABKS, SI. E. A71-29106 A note on the optimum averaging time of uind STBATTOB. U. K. information for conventional aircraft landings Preliminary design methods of V/STOL prop- rotors 871-30394 [ARS PREPRINT 5541 871-31106 SPARROU, E. B. STBEELOU. E. Low Reynolds number turbulent flou in large aspect Evaluation of flight measurements and the plotting ratio rectangular ducts of loading collectives [ASfiE PAPER 71-FE-A] A71-29378 N71-24389 SPILLABE. D. J. STUEGEOB. J. E. Vacuum heat treating of jet engine components Turbulence experience recorded by CAADBP A71-28145 A71-29771 SPIBIDOBOV. IU. A. STURGESS, G. J. Effect of the penetrating ability of jets on the Correlation of data and prediction of peripheral nonuniformity of a gas temperature effectiveness from film cooling injection field at the outlet of a gas turbine gine geometries of a practical nature chamber A71-28751 A71-28971 sacra, s. B. Generalized characteristic of peripheral Righ temperature turbine design considerations nonuniformity in the temperature field of a gas [SAE PAPER 7104621 871-28335 at the outlet of a gas-turbine engine combustion SUD. I. K. chamber An over-view of the airport noise problem A71-28972 871-29304 ST. JOEB. B. S. SULLIVAN, D. C. Load estimation methods for preliminary design The role of military aviation greases in subsonic veight prediction commercial airplane design A71-28211 [SAE PAPER 7104111 A71-28304 STALEY. J. T. SULLIVAB. E. J. Investigation to develop a high strength Turbofan engine considerations for reaction drive stress-corrosion resistant naval aircraft rotors aluminum alloy Final report, 16 Dec. 1969 - 16 CARS PREPRINT 5611 871-31108 Sep. 1970 SllBIDA, P. T. [AD-7203981 N71-25876 Filamentary composite reinforcement of metal STABPEB, J. T. structures VSTOL - Prospects for civil aviation 871-28168 A71-30162 SUSSBAB, B. B. STABCO, J. J. Development of high-response data analysis aids ROW VAST troubleshoots a doppler radar for inlet-engine testing A71-28778 A71-28032 STANLEY, J. E. SUZUKI. K. Improved aluminide coatings for nickel base alloys Gas turbine combustors Final report [ NAL-TR-2081 N71-26298 [ NASA-CR-72863 1 N7 1-25454 SUAIB, E. 1. STABKBAB, E. S. Control of V/STOL aircraft in turbulence The role of kinetics in engine emission of nitric A71-29776 oxide SUABKE. K. V. A71-30454 Powered uheels - A concept for parking and taxiing STEELE, E. E. of commercial transport airplanes Satellite aided vehicle avoidance system Patent [SAE PAPER 7104463 871-30530 [NASA-CASE-ERC-l0090] N71-24948 SUABDEN, 1. C. STEIB. D. Compressor sensitivity to transient and distorted Optimization of military VTOL secondary power tiansient flows systems [AIAA PAPER 71-6701 871-30734 [SAE PAPER 7104451 A71-28326 SYKES, D. 1. STEPHENS, D. G. Pressures on boat-tailed afterboaies in transonic Instrument for measuring the dynamic behavior of flow vith a low-thrust jet liquids Patent A71-29889 [NASA-CASE-XLA-O5541] 871-26387 STEPHENSOB. C. Factors affecting fuel control stability of a turbine engine and helicopter rotor drive System B-16 PEESOUAL AUTEOB IUDSX VASILEV, L. A. A71-28841 TEOIAS, P. T Influence of the presence of a plane on the TABAK. E. 6. measurement of line-containing spectra The use of high intensity xenon lighting to A71-30523 enhance US Army aircraft day/night conspicuity TEOEAS, U. U. [ AD-7 186393 N71-24669 Lift ratings of V/STOL propulsion units TAGAUOV. G. I. [SAE PAPER 7104711 A71-30537 Limiting flows of a viscous fluid with stationary TEOEPSOU, 6. E. separation zones at Reynolds numbers tending to Pail-safety for the E-46 rotor blade infinity [AES PREPRINT 5511 A71-31103 A71-29204 TEOISOU. 1. E. TAKASAUA, K. Measurement of extreme mechanical turbulence A model test on the hovering performance of jet during low level flights by Mirage A3-76 flapped rotor 871-29756 [ NAL-TR-2113 N71-25396 TEOBBUBU. D. E. TALAUTOV. A. V. A comparison of pilot performance using a center Combustion in a flow stick vs side arm control configuration A 7 1- 2 8 9 54 Technical report, May - Oct. 1968 Role of turbulence intensity during the mixing of [ aD-720846] 871-25846 plane isothermal slipstreams in an enclosed flou TEBAVES, J. 871-28962 Antennas for sideways looking airborne radar Effect of the penetrating ability of jets on the A71-31041 peripheral nonuniformity of a gas temperature TEUBIIAE, W. E. field at the outlet of a gas turbine engine The future of STOL chamber [SAE PAPER 7104641 871-30535 A71-28971 TODA, A. Generalized characteristic of peripheral A model test on the hovering perioroance of jet nonuniformity in the temperature field of a gas flapped rotor at the outlet of a gas-turbine engine combustion [ BAL-TR-211 1 871-25396 chamber TONON, T. S. A71-28972 Acoustic liner design from a fluid mechanics TAMARU. T. approach Gas turbine combustors [AIAA PAPER 71-7571 A71-30791 [ NAL-TR-208 ] N71-26298 TOTIAB, E. E. TAUG. E. E. Powerplant testing from an operator's perspective Vertical-fin loads and rudder hinge-moment CSAE PBPBR 7104511 A71-28329 measurements on a 1/8 scale model of the N2-P3 TOWERS, J, lifting body vehicle at Mach numbers from 0.50 Engine condition monitoring to 1.30 A71-28177 [ NASA-TM-X-22861 N71-24581 TBAVNIKOVA, 1. I. TAUG, P. K. Measurement of light pressure forces and of Acoustic liner design from a fluid mechanics aerodynamic forces acting on a body of complex approach shape in a free-molecule flow [AIAA PAPE" 71-7573 A71-30791 A71-29155 TABUG,.I. Y. TBEUSSABT, E. Optimal and suboptimal control synthesis for Use of weather radar for aviation minimum time VTOL transition [UMO-264-TP-1481 N71-2&394 A71-30799 TRUSOVA. 0. A. TABZANIU, P. J., JB. Influence of the real properties of air on flow Prediction of control loads due to blade stall parameters around an elliptical cone - [AHS PREPRINT 5131 A71-31084 Aerodynamic characteristics of elliptical cones TATE, B. 1. at large angles of attach Boeing 747 training developments and A71-29191 implementation TUNAKOV. A. P. [SAE PAPER 7104731 A71-28339 Assessment of measurement errors in the testing of TAYLOR, J. axial-flow compressors and turbines Gust loads for structural design A71-28582 871-29784 Investigation of the ideal cycle of a TAYLOR. 1. U.. JR. continuous-combustion gas turbine with stepwise ? zomparison of minimum time profiles for the heat release, overexpansion cycle P-104 using Balakhrishnan's epsilon technique 871-28583 and the energy method Gasdynamic verification calculations of multistage 871-28831 axial-flow compressors on a digital computer TCEEUG. P. A71-28584 The dynamic characteristics of a five component TUBNBOU. J. E. oscillating balance Preliminary impact speed and angle criteria for A71-30333 design of a nuclear airplane fission product TESCB, u. a. containment vessel Task 4 stage data and performance report for [ NASA-TU-X-22451 N71-25411 casing treatment investigations. Evaluation of TUBUBULL. E. C. range and distortion tolerance for high Llach VTOL propulsion system development number transonic fan stages, volume 1 [AES PREPRINT 5621 A71-31109 [NASA-CR-82862 ] N71-25460 Task 4 stage data and performance report for casing treatment investigations. Evaluation of U range and distortion tolerance for high Hach UIAUSKII, A. A. number transonic fan stages, volume 2 Calculation of three-dimensional structures. r NASA-CR-828671 N7 1-2 546 1 Number 13 TEOMAS, C. L. A71-30888 Sonic boom reflection factors for flight near the UPPINGTOU. D. C. threshold Mach number The Imperial College graphite heated hypersonic A71-30610 wind tunnel TEOEAS, D. D. [ IC-AERO-71-01 1 N71-24675 A world wide synopsis of turbulence related accidents A71-28885 V TEOMAS, E. U. VASILEV, 1. A. - Plug in relay - Panacea or Pandora's BOX Measurement of light pressure forces and of B-17 VAUGEN, E. R. PERSONAL AUTEOR INDEX aerodynamic forces acting on a body of complex A71-29483 shape in a free-molecule flow WERNICKE. K. G. 871-29155 Full-scale proprotor developmeVc VAUGEN. E. B. [AHS PREPBIlT Sol] A71-31077 Effect of yaw of repose on ballistic match of IIERIIIEIB, C. E. similar projectiles A 1540 to 1660 Iiiz propagation between A71-29890 geostationary satellites and aircraft summary VENUTI. P. R. report RLH primary flight control system design [ NASA-TM-X- 6550d ] N71-24913 [ABS PREPRINT 5031 A71-31079 WESTEBLIN. V. VEBIBDEE, F. E. Antenna for speech communication set PPL37 Measurement of extreme mechanical turbulence measnrements of impedance on the production during low level flights by Hirage A3-76 version in light metal 871-29756 [ FOB-3-C-3602-613 871-26150 VICBNESS. J. WHITE, R. A. Optimization of military VTOL secondary power Some results on the heat transfer within resonant systems cavities at subsonic and supersonic Uach numbers [SAE PAPER 7104451 A71-28326 [ASKE PAPER 71-FE-91 A71-29450 VILLIERS. J. WEITEEEAD, A. 8.. JR. Air traffic control and data processing in France Lee side heating investigations. Part 1 - A71-30382 Experimental lee side heating studies on a delta VIBNICEENKO. N. K. wing orbiter Studp of clear sky turbulence in the stratosphere N71-26060 [JPRS-531331 N71-25746 WHITLOW. J. E., JR. VINOGRADOV. IU. V. Potential of methane fueled supersonic transports Role of turbulence intensity during the mixing of over a range of cruise speeds np to Uach 4 plane isothermal slipstreams in an enclosed flow [ NASA-TH-X-22813 N71-25384 A71-28962 QEITNOBE, C. A. VIVIEB. J. F. Development of the Lockheed L-loll’s flying Air traffic control and data processing in France stabilizer A71-30382 [SAE PAPER 7104261 B71-28312 von EARDEBBERG, P. ti. UEITTAKEE. n. Preliminary development of an active transmission Theoretical assessment of flame tube temperatures isolation system in a combustor operating at typical S.S.T. [AHS PREPRINT 5141 A71-31085 conditions VOEOBKIN, 8. P. A71-28749 Fatigue strength of aircraft skin elements ‘WILCOX, P. 8. affected by corrosion Thick high aspect ratio wing, part 2 A71-27819 171-24659 VREEBOEG, J. P. B. aILLxAns. n. c. Design of a linear array of blade antennas for An airborne phased array for use in an ATC aircraft-satellite communication satellite system in I-band 871-31062 A71-31054 UILLIFORD. J. R. Special problems in helicopter handling gnalities W as influenced by ASB requirements HALL. E. M. V. A71-29384 Investigation of the suitability of gelled methane WILSON, E. J. for use in a jet engine Final report, 15 Jnn. Installation and testing of strain gages for 1970 - 15 Feb; 1971 high-temperature aircraft applications TNASA-CR-72876 1 N71-25772 A71-30681 WABREN,,F. W. G. HILSOB, G. G. Partially trapped waves Effect of paw of repose on ballistic match of A71-29763 similar projectiles IIASEBUEN, E. A71-29890 Instrument Society of America, International WILSON, E. J. Aerospace Instrumentation Symposium, 17th. Las Analysis of subjective ratings for the XB-70 Vegas, Nev.. Hay 10-12, 1971, Proceedings airplane response to atmospheric turbnlence and A71-30309 controlled inputs WASSENBERGE. E. A. A71-29774 Aspects of air law and civil air policy in the WIIIICK, A. B. seventies Requirements, performance and integration of 871-29938 modern navigation aids WASSEBBAUER. J. F. [SAE PAPER 7104561 871-28333 Nach 2.5 performance of a bicone inlet with WINN. A. 1. internal focused compression and 40 percent Evalnation of fuel flowmeter instrumentation Final internal contraction report, 5 Aug. - 20 Oct. 1970 [ NASA-TN-X-2294 1 N71-25872 [ AD-7192801 N71-24479 UATERS. J. F. WIBSTOB, D. C. Aircraft noise txpe certification orientation V-12 has civil, military missions session Final report A71-30420 [ BRC-TR-300 ] N71-26304 UINTEE~ETER. C. F. Aircraft noise type certification orientation Static tests of a 0.7 scale augmentor wing flap session - Lecture notes, supplement 2 Final for the modified C-8A airplane - Test reshlts report and analysis [ ERC-TE-300-SUPPL-2] N71-26305 [ NASA-CR- 11 43151 N71-26416 UATTS,.G. A. WINTEE~UTE. G. Eorizontal stoppable rotor conversion Rain erosion resistant radomes for supersonic [AHS PREPRINT 5021 A71-31078 aircraft WEIUABN, A. 871-29645 Fuel-optimal landings of jet-supported VTOL WITT, E. E. aircraft Protective coatings for a hypersonic flight 871-29281 load-bearing refractory alloy control surface WEISS. U. 1. A71-29646 Fail-safety for the E-46 rotor blade UOLFE. J. A. [AHS PREPRINT 5511 A71-31103 Application of a digital computer to the WEBIIICKE, J. closed-looD control of a uind tunnel model Visual flight simulation with high information trajectory-simulation system density image storage media A71-30334 B-18 PERSONAL AUTEOB INDEX ZIEGLEB, E. WONG, E. Y. The role of heat conduction in leading edge heating theory and experiment Z [ARC-CP-1126] N71-24446 ZAGALSKY. N. 8. 1000, D. Energy state approximation and minimum-fuel Commercial VSTOL and the jet VTOL transport fixed-range trajectories A71-29131 A71-30609 ELH primary flight control system design ZAIKA, A. IA. [AHS PREPRINT 5031 A71-31079 Patigue strength of aircraft skin elements WOODGATE, L. affected by corrosion Part 1 - Measurements of the oscillatory A71-27819 pitchinq-moment derivatives on a delta wing with ZBOEIL, P. E. round leading edges in incompressible flow The antenna performance of the L-1011 Tristar N71-24570 A71-31060 Part 2 - Measurements of the oscillatory ZEILIN. IU. 1. pitching-moment derivatives on a slender Minimum-drag wing-fuselage combination for sharp-edged delta wing in incompressible flow snpersonic speeds N71-24571 a71-29182 Part 3 - Measurements of the oscillatory Optimal distribution of wing thickness in pitching-moment derivatives on a sharp-edged snpersonic flow delta wing at angles of incidence for which A71-29222 vortex breakdown occurs ZEIBNIKOV. B. 1. N71-24572 Investigatiou of means of increasing the lift/ Part 4 - Measurements of lift, drag, and pitching drag ratio of conical bodies moment on a series of three delta wings A71-29183 N71-24573 ZHIVOV, 1. Z. WOODGEE, G. E. Plane jet of a conducting fluid in a slipstream JT9D development for airline operation A71-29610 ~SAEPAPER 7104341 A71-30528 ZBUEII. I. G. WOODWAHD, D. S. Measurement of geomagnetic components from moving The two-dimensional characteristics of a 12.2 platforms percent thick RAE 100 aerofoil section A71-28249 [ ARC-R/M-3648] N71-24488 ZIEGLEB, E. WOODWARD, B. EL The major development trends in air transport and The development of lonq-range hyperbolic European co-operation navigation in the United States 871-30302 A71-30711 A wind tunnel investigation of jets exhausting WOODWOBTH. J. into a crossflow. Volume 4 - Additional data New developments in product support for the three jet configuration [SAE PAPER 7104371 A71-30529 [AD-718123] N71-24491 WOOLEB, P. T. A wind tunnel investigation of jets exhausting A wind tunnel investigation of jets exhausting into a crossflow. Volume 1 - Test description into a crossflow. Volume 4 - Additional data and data analysis for the three jet configuration [AD-7181221 871-24492 [ AD-7 18123 3 N71-- ' 49 1 A wind tunnel investigation of jets exhausting A wind tunnel investigation of jets exhausting into a crossflow. Volume 2 - Additional data into a crossflow. Volume 1 - Test description for the one jet configuration and data analysis [ AD-7202321 N71-26516 [ AD-7 18122 3 N71-24492 A wind tunnel investigation of jets exhausting A wind tunnel investigation of jets exhausting into a crossflow. Volume 3 - Additional data into a crossflow. Volume 2 - Additional data for two-jet configurations €or the one jet configuration [ AD-7202331 N71-26517 [ AD-7202321 N71-26516 A wind tunnel investigation of jets exhausting into a crossflow. Volume 3 - Additional data for two-jet configurations [ AD-7202331 171-26517 AOBTEANN, F. X. Airfoils for the variable geometry concept A71-29257 WRIGHT, F. P. Area navigation systems and displays [SAE PAPER 7104571 A71-30533 UBLGHT. P. L. Static tests of a 0.7 scale augmentor wing flap for the modified C-8A airplane - Test results and analysis [NASA-CR-1143153 N71-26416 Y YATES, E. C., JH. Flutter and unsteady lift theory N71-24706 YIN. S.-K. The method of multiblade coordinates in the linear analysis of lifting rotor dynamic stability and gust response at high advance ratio [AES PREPRINT 5121 A71-31083 YOUNG. C. Shock interference heating on the space shuttle booster during ascent N71-26059 PUSTINICE, J. Circumferential traversing technique for intra- stage analysis of axial flow compressors [ASEE PAPER 71-PE-331 A71-29468 B-19 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 8) AUGUST 1971 Typical Contract Number Index Listing NAS12-2081 871-24869 I NAS3- 13 37 3, NASA ORDER 1-60739 N71-25784 871-25785 NUMBER NASU-1695 NUMBER N71-25024 Listings in this index are arranged alphanumerically by contract number. NASR-2038 Under each contract number, the accession numbers denoting documents N7 1-25822 N71-25998 that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing NGL-25-001-32 first. The accession number denotes the number by which the citation is 871-30311 identified in either the IAA or STAR section NGL-33-016-119 AF 33/615/-67-C-1349 A71-30820 A7 1-29 645 N00014-69-C-0101 A71-30609 NGR-15-005-G69 AP 33/657/-69-C-0552 A7 1-29776 A71-28 032 N00019-69-C-0219 A71-31081 NGR-22-009-0 10 AF 33/657/-70-C-0511 N71-24869 A71-30770 N00019-69-C-0292 A71-30771 N71-25876 NGR-22-009-303 A7 1-3108 1 AF 44/620/-68-C-0023 N00019-70-C-0118 A71-30799 871-25876 NGB-22-009-387 N71-25362 AP-APOSR-67-0672A NAS1-6448 A71-30604 871-31089 NGR- 52-3025-00 871-30068 AF-APOSR-1251-67 NAS1-9434 N71-24954 '1-30333 NOW-66-0657-F A7 1-3 1 100 AF-EOAR-67-5 NAS1-10272 A71-29578 N71-26417 NRC A-2003 A71-30604 DA-31-124-ARO/D/-349 NAS1-10410 A71-29467 N71-24586 NRC A-5573 A71-28985 DA-44-177-AMC-364/T/ h'AS2-4 151 A7 1-31 1 11 A71-31083 NSF GK-2053 A71-29450 DOT-FA70WA-2446 NAS2-4824 N71-26303 A71-29469 NSF GK-5608 N71-26304 A71-30799 N7 1-263 05 NAS2-5168 A7 1-31 078 NSP GK-13303 DOT-TSC-5 A71-29378 N7 1-24869 NAS2-5462 A71-30784 NSR-31-001-104 DRB-9551-12 N71-26170 A71-31022 1852-5473 A71-31087 PD/48/09/ADM P19628-70-C-0291 N71-24446 N71-24357 NAS2-6025 N71-26416 124-64-02- 03-23 F33615-68-C-1097 N71-26354 N71-25846 NAS3-10498 N71-25397 126-15 F33615-69-C-,1110 N71-25411 N7 1-24555 NAS3-11157 22 N71-25783 N71-25460 F33615-69-C-1602 N71-25461 126-15-01-02-22 N71-24491 N71-26355 N71-24492 NAS3-11160 N71-26516 N71-25454 126-62-0 1-04-24 N71-26517 N71-25537 NAS3-14305 FA-69-UA-2045 N71-25772 126-62- 1 1- 02 A71-30777 N71-24582 N AS 5- 1 1 63 4 FA-69-2208 A71-30898 720-03 A71-28314 N7 1-25384 NAS8-20625 A7 1-25 87 2 N00014-68-A-0091 A71-29448 72 7-00-00-01-24 N71-25621 N71-24581 c- 1 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (08) 4. Title and Subtitle 5. Report Date August 1971 AERONAUT1 CAL ENGINEER I NG - A Special Bibl iography (Supplement 8) 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. 10. Work Unit No. 9. Performing Organization Name and Address National Aeronautics and Space Administration 11. Contract or Grant No. Washington, D. C. 20546 13. Type of Report and Period Covered 112. Sponsoring Agency Name and Address 14. Sponsoring Agency Code 15. Supplementary Notes 16. Abstract This special bib1 iography 1 ists 540 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1971. Emphasis is placed on engineering and theoretical aspects for design, construction, evaluation, testing, operation and performance of aircraft (including aircraft engines) and associated components, equipment and systems. Also included are entries on research and development in aeronautics and aero- dynamics and research and ground support for aeronautical vehicles. 17. Key Words (Suggested by Authorts)) I 18. Distribution Statement Aerodynamics Aeronautical Engineering Aeronautics Bibl iographies 19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price" Unclassified Unclassified 168 $3.00 HC