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Aeronautical NASA SP-7037 (98) Engineering July 1978 A Continuing NASA Bibliography with Indf:

National Aeronautics and Space Administration

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NASA SP-7037(98)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 98

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in June 1978 m • Scientific and Technical Aerospace Reports (STAR) • Internationa/ Aerospace Abstracts (IAA)

Scientific and Technical Information Branch 1978 National Aeronautics and Space Administration Washington, DC This Supplement is available from the National Technical Information Service (NTIS), Springfield. Virginia 22161. at the price code E02 ($475 domestic. $9 50 foreign) INTRODUCTION

Under the terms of an mteragency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering The first issue of this bibliography was published in September 1970 and the first supplement in January 1971 Since that time, monthly supplements have been issued This supplement to Aeronautical Engineering — A Continuing Bibliography (NASA SP-7037) lists 399 reports, journal articles, and other documents originally announced in June 1978 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA) The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals This procedure, which saves time and money, accounts for the slight variation in citation appearances Three indexes -- subject, personal author, and contract number -- are included An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A78-10000 Series)

All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc (AIAA). as follows Paper copies of accessions are available at $6 00 per document up to a maximum of 20 pages, the charge for each additional page is $0 25 Microfiche"1 of documents announced in IAA are available at the rate of $250 per microfiche on demand, and at the rate of $1 10 per microfiche for standing orders for all IAA microfiche The price for the IAA microfiche by category is available at the rate of $1 25 per microfiche plus a $1 00 service charge per category per issue Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1 35 per microfiche

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STAR ENTRIES (N78 10OOO Series)

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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 AVAILABILITY

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

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements is $45 00 domestic. $75 00 foreign All questions relating to the subscriptions should be referred to NTIS. Ann Subscrip- tions. 5285 Port Royal Road, Springfield Virginia 22161

VI ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics Pendragon House. Inc and Astronautics 899 Broadway Avenue Technical Information Service Redwood City California 94063 750 Third Ave New York. NY 10017 Superintendent of Documents U S Government Printing Office British Library Lending Division Washington D C 20402 Boston Spa, Wetherby Yorkshire, England University Microfilms Commissioner of Patents A Xerox Company U S Patent Office 300 North Zeeb Road Washington, D C 20231 Ann Arbor Michigan 48106

Energy Research and Development University Microfilms. Ltd Administration Tylers Green Technical Information Center London England P 0 Box 62 Oak Ridge. Tennessee 37830 U S Geological Survey ESA-Space Documentation Service 1033 General Services Administration ESRIN Building Via Galileo Galilei Washington, D C 20242 00044 Frascati (Rome) Italy

U S Geological Survey Her Majesty's Stationery Office 601 E Cedar Avenue P 0 Box 569. S E 1 Flagstaff. Arizona 86002 London, England

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

U S Geological Survey National Aeronautics and Space Bldg 25, Denver Federal Center Administration Denver, Colorado 80225 Scientific and Technical Information Branch (NST-41) Washington, D C 20546 Zentralstelle fur Luftfahrtdoku- mentation und -Information National Technical Information Service 8 Munchen 86 5285 Port Royal Road Postfach 880 Springfield, Virginia 22161 Federal Republic of Germany TABLE OF CONTENTS IAA Entries 273 STAR Entries 299

Subject Index A-1 Personal Author I ndex B -1 Contract Number Index C-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT -AVAILABLE ON MICROFICHE —«-N78-1O020*# Boeing Vertot Co Philadelphia Pa-» —•-WIND TUNNEL INVESTIGATION OF ROTOR LIFT AND NASA ACCESSION PROPULSIVE FORCE AT HIGH SPEED DATA ANALYSIS -CORPORATE NUMBER —*• Frank McHugh Ross Clark and Mary Soloman Oct 1977 SOURCE 211 p 3 Vol -•-(Contract NAS1-14317) TITLE . ^NASA-CR-145217-App-l D210 111351) Avail NTIS- HC A10/MF A01 CSCL01A-* .PUBLICATION The basic test data obtained during the lift-propulsive force DATE AUTHORS limit wind tunnel test conducted on a scale model CH-47b rotor are analyzed Included are the rotor control positions blade loads and six components of rotor force and moment corrected for -AVAILABILITY CONTRACT hub tares Performance and blade loads are presented as the SOURCE OR GRANT. rotor lift limit is approached at fixed levels of rotor propulsive force coefficients and rotor tip speeds Performance and blade load trends are documented for fixed levels of rotor lift coefficient REPORT as propulsive force is increased to the maximum obtainable by -COSATI NUMBERS _ the model rotor Test data is also included that defines the CODE effect of stall proximity on rotor control power The basic test data plots are presented in volumes 2 and 3 Author

TYPICAL CITATION AND ABSTRACT FROM IAA

NASASPONSORED. AVAILABLE ON If MICROFICHE j— »-AA77 8 13071 _^. Toward a new V/STOL generation L Roberts- AIAA ACCESSION NUMBER \ I anid S B Anderson (NASA Ames Research Center, Moffett Field.- Calif^Astronautics and Aeronautics, vol 15, Nov 1977^> 22-27 -AUTHORS while many V/STOL problems are now better understood and TITLE . technology has progressed to the point where higher thrust/weight ratios and greater stability augmentation are achievable, a number of AUTHOR'S TITLE OF still existing insufficiencies provide a sobering reminder that learning AFFILIATION PERIODICAL- in ground testing and simulation, and careful methodical planning, are a prerequisite for any research and development program The -PUBLICATION present paper is centered on the major technical problems for the DATE Navy Type multimission V/STOL aircraft The aircraft's configurations with and without forward lift fan are discussed, along with the propulsion systems, testing techniques, controls, displays, flight dynamics, and ground/flow field interactions V P AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 98)

JULY 1978

A78-28789 Microfractographic fracture analysis of some aircraft parts S Nishijima, C Masuda, and M Shimodaira (National Research Institute for Metals, Tokyo, Japan) Japan Society of Materials Science, Journal, vol 27, Jan 1978, p 9-13 8 refs In Japanese, with abstract in English A technique for the microfractographic fracture analysis of IAA ENTRIES aircraft parts, such as propeller blades and hubs and landing gear link assemblies, is presented The method is illustrated by examples of fatigue caused fracture Analyses are performed by striation and bench-mark spacings, and by the undulating pitches of tear-dimple A78-28523 # Choice of optimal ellipsoid-surface projection facets caused by fast overload fractures S C S onto a sphere in solving problems of air navigation (0 vybore optimal'noi proektsu poverkhnosti elhpsoida na sferu pn reshenu zadach vozdushnoi navigatsn) V N Gan'shm (Lenmgradskn A78-28833 Clear air turbulence accidents A I Brunstem Inzhenerno Stroitel'nyi Institut, Leningrad, USSR) and A V Lipin (National Transportation Safety Board, Washington, D C ) SAFE Geodezna i Aerofotos'emka, no 5, 1977, p 20-25 5 refs In Journal, vol 8, Spring 1978, p 17-19 Russian National Transportation Safety Board air carrier records for It is demonstrated that for purposes of air navigation it is most 1964-1975 show 68 accidents involving clear air turbulence (CAT) suitable to approximate a geodesic line by the central section of an One hundred eighty-four persons were injured and there were ellipsoid Kavraisku's simple method (1958) for projecting an thirty six fatalities Most aircraft involved were jets and most ellipsoid surface onto a sphere is analyzed, it is shown that in these accidents occurred between 31,000 and 35,000 feet in normal cruise projections the central section of the ellipsoid is in the form of the CAT forecasting was not particularly accurate The airlines have arc of a large circle Formulas for the transformation of elements suffered severe economic penalties, probably in excess of (azimuths and arc lengths) of the central section to elements of a $23,000,000 annually It is concluded that more accurate and timely 'Kavraiskn sphere' are presented B J CAT forecasts are needed, CAT detection systems, airborne and ground-based are needed, and real-time weather data are required on the ground and particularly in the cockpit (Author) A78-28560 Mode of operation and characteristics of Darneus rotors (Arbeitsweise und Merkmale von Darneus-Rotoren) H Selzer and C Cohrt (ERNO Raumfahrttechmk GmbH, Bremen, A78-28834 Automatic airspace R E Gillman Exxon Air West Germany) In Energy from wind, Meeting, 4th, Bremen, West World, vol 30, no 1, 1978, p 6 10 Germany, June 7, 8, 1977, Report Munich, Computer techniques, both in ATC and on board aircraft, are Deutsche Gesellschaft fur Sonnenenergie, 1977, p 111-124 In discussed with reference to their effectiveness in ensuring smooth German separation and sequencing of commercial air traffic Attention is Some of the mam features of the operation of a vertical-axis given to the terminal configured vehicle concept, which utilizes new (Darneus) rotor for wind energy conversion are examined The basic display systems to assist the pilot, especially during the landing method for calculating the performance index of a rotor is shown phase A TV screen, called the Electronic Attitude Direction Startup behavior, materials, conversion technique, and efficiency of Indicator (EADI) is evaluated in terms of its ability to graphically operation are briefly discussed Curves showing the dependence of present runway approach patterns, i e , aircraft attitude, heading, and the performance index on the high-speed rpm number for an tracking D M W experimental Darneus rotor are given along with a design chart giving the rotor diameter vs design wind speed relation for rotors of four A78-28835 Advanced flight decks for the 80s P N Giles different output classes from 1 kW to 100 kW P T H. (British Aircraft Corp, Ltd, Commercial Div , Weybridge, Surrey, England) Exxon Air World, vol 30, no 1, 1978, p 11-14 A78-28610 Boundary-layer interaction with a non- A modified VC-10 mock-up is employed to test new flight deck equihbnum two-phase stream on a surface being burned out in an display systems Attention is given to man-machine interaction, axisymmetric Laval nozzle A A Glazunov, E G Zauhchnyi, V la whereby the former makes decisions based on information provided Ivanov, and A D Rychkov IPMTF - Zhurnal Prikladnoi Mekhaniki i by the latter Flight parameters evaluated include aircraft attitude, Tekhnicheskoi Fiziki, May-June 1977, p 5362 ) Journal of Applied location, distance from the runway, and engine functioning Pilots Mechanics and Technical Physics, vol 18, no 3, Jan 10, 1978, p asked to evaluate the display systems generally gave them favorable 323-330 18 refs Translation A method incorporating hyperbolic differential equations of ratings D M W subsonic and transonic flow is developed for analyzing the non- stationary problem of two-phase (gas and solid-particle) flow in an A78-28880 Use of NS LX1600A as a short-range altim- axisymmetric Laval nozzle Attention is given to the interaction of a eter B L Sawford and P C Manms (Commonwealth Scientific and turbulent boundary layer formed on the ablating nozzle wall with Industrial Research Organization, Div of Atmospheric Physics, the nonequilibnum flow Numerical results are presented for Aspendale, Victoria, Australia) Journal of Physics E ' Scientific two-phase mixtures with the following parameter values an initial Instruments, vol 11;Feb 1978, p 158-160 pressure of 43 atm, an initial temperature of 3450 K and particle Characteristics of the LX1600A pressure transducer are ex- diameters of 2 microns B J. amined with the object of using the device as a short-range altimeter

273 A78-28900

for probing the lowest kilometer or two of the atmosphere In this A78-28961 ff Transonic flows past a lift profile (O trans- application the device is subject to large temperature changes and zvukovykh techennakh okolo nesushchego krylovogo profilia) lu B stringent power restrictions It is shown that pressure determination Lifshits and 0 S Ryzhov Akademna Nauk SSSR, Izvestna, to plus or minus 1 5% over ranges of 2 and 20 kPa is possible Mekhamka Zhidkosti i Gaza, Jan-Feb 1978, p 104-112 14 refs In provided that temperature effects are calibrated out Operation of Russian the device in a pulsed mode results in a considerable saving in power Asymmetric transonic gas flows past a lifting wing are analyzed consumption (Author) An asymptotic solution to the flow problem is obtained for a region at some distance from the wing, and the dependence of the terms of the asymptotic expansion on the parameters characterizing the A78-28900 Fault tolerant flight controls R Poupard longitudinal and transverse dimensions of the wing is examined A (IBM Corp , Federal Systems Div , Owego, N Y ) Aviation Engineer- law governing the variation of the lift as a function of the difference ing and Maintenance, vol 2, Jan 1978, p 19,21,22,29 8 refs between Mach = 1 and the freestream Mach number is derived, A method which uses multiple digital computer systems in assuming that the difference is small V P fly-by-wire flight control is described in terms of its tolerance to faults Attention is given to the concept of 'coverage', which means that a fault can be detected, traced to a specific unit, and correct A78-28969 # Investigation of the flow in a plane diffuser by operation can be continued even after failure has occurred The means of a laser Doppler anemometer (Issledovanie techenna v number of faults which can be tolerated within a given system is the ploskom diffuzore s pomoshch'iu lazernogo Doplerovskogo anemo- subject of a hard- and software analysis The NASA F-8 digital metra) A la Shkvar Akademna Nauk SSSR, Izvestna, Mekhamka fly-by-wire research program is presented as an illustration of a Zhidkosti i Gaza, Jan -Feb 1978, p 159-161 5 refs In Russian two-fault tolerant redundant system, with particular applications in Space Shuttle avionics D M W A78-28972 # An analytic study of free molecule flow fields at the front and back edges of a plate (Analiticheskoe issledovame polei svobodnomolekuliarnogo techenna v raionakh perednei i zadnei A78-28956 # Hydrodynamic effect on a contour produced kromki plastmy) S V Musapov Akademna Nauk SSSR, Izvestna, by an ideal incompressible flow of constant vorticity (Gidrodma- Mekhamka Zhidkosti i Gaza, Jan -Feb 1978, p 171 176 5 refs In micheskoe vozdeistvie na kontur so storony potoka ideal'noi Russian neszhimaemoi zhidkosti s postoiannoi zavikhrennost'iu) S D An analytic investigation of density fields and mass flux at the Vil'khovchenko Akademna Nauk SSSR, Izvestna, Mekhamka Zhid- front and back edges of a plate fixed parallel to a free molecule flow kosti i Gaza, Jan -Feb 1978, p 52-58 11 refs In Russian is presented The limiting perturbations which may occur in the In the present paper, a problem involving a flow of uniform current are identified It is found that the effects previously observed vorticity is reduced to the problem of the motion of a deformable under transient conditions (such as the development of a boundary contour in a potential flow An approximate method for calculating layer, the formation of a shock wave, and a rarefied wake) are the hydrodynamic effect on the contour for a class of flows is analogous to processes in the collisionless mode S C S proposed and is used to derive linear-approximation formulas for the hydrodynamic forces and moments The results are expressed in terms of the local characteristics of the external flow and the A78-29089 # Observability criteria for nonlinear dynamic hydrodynamic characteristics of the contour's configuration The systems subjected to multiparameter measurements (Kritern nabliu- properties of the configuration characteristics are identified for daemosti nelmemykh dmamicheskikh sistem pri rrmogomernykh contours with one and two symmetry axes Expressions, based on izmerenuakh) A M Kovalev (Akademna Nauk Ukramskoi SSR, conformal mapping, are obtained for calculating the hydrodynamic Institut Prikladnoi Matematiki i Mekhamki, Donetsk, Ukrainian characteristics of the contour's configuration V P SSR) Prikladnaia Mekhamka, vol 13, Dec 1977, p 95-101 10 refs In Russian A78-28958 * Calculation of supersonic flows past wings The paper deals with the problem of observing a nonlinear with allowance for trailing tangential discontinuities within the dynamic system where the function of the phase coordinates, which framework of a model employing a system of Euler equations is being measured and which is known at specified moments of time, (Raschet sverkhzvukovogo obtekanna kryl'ev s uchetom skho- is a nonlinear vector function Global and local formulations of the diashchikh s kromok tangentsial'nykh razryvov v ramkakh modeh, sufficient observability conditions are derived The applicability of ispol'zuiushchei sistemu uravnenu Eilera) A N Mmailos Akademna sounding navigation to the autonomous determination of aircraft Nauk SSSR, Izvestna, Mekhamka Zhidkosti i Gaza, Jan -Feb 1978, phase coordinates is studied from the standpoint of observability p 78-89 14 refs In Russian theory V P

A78-29174 Giants battle in US small turbine market J P Geddes Interavia, vol 33, Mar 1978, p 179184 A78-28959 H Stability of subsonic gasdynamic flows (K Rising fuel costs, federal noise regulations, and the availability ustoichivosti dozvukovykh gazodmamicheskikh techenu) F A of new technologies have spurred the development of a new Slobodkina Akademna Nauk SSSR, Izvestna, Mekhamka Zhidkosti i generation of jet engines for small aircraft This paper describes a Gaza, Jan-Feb 1978, p 90-97 10 refs In Russian variety of such engines (under 4,500 kp thrust) with reference to A system of partial differential equations describing the small market demand projections, and to the feasibility of designing new perturbations of the steady flow of a perfect mviscid gas in a channel airframes around them Included in the discussion are turboprops as of variable cross section is analyzed The steady flow equations and well as fan jets D M W the boundary conditions are analyzed, and the solution of the linearized equations is sought in the form of v(x) exp (lambda t), where v(x) is an eigenfunction, and lambda is the natural frequency A78-29175 US Navy examining a wide range of V/STOL of the boundary value problem under consideration Using this concepts H Levy Interavia, vol 33, Mar 1978, p 227-229 approach, the problem can be reduced to the solution of ordinary V/STOL and VATOL (vertical attitude take-off and landing) differential equations with variable coefficients that depend on the aircraft, designed to become operational in the 1990s, are analyzed lambda parameter Analytical solutions are obtained for small values within terms of mission requirements Three basic mission types are of lambda and for absolute values of lambda much greater than outlined high-speed multi-mission, supersonic fighter/attack, and unity V P anti-submarine (a LAMPS Mk 3 replacement) Attention is given to a

274 A78-29326

circulation control wing (CCW), which uses trailmg-edge blowing to of a number of microprocessors to control simulator peripherals are increase lift (the Coanda effect) Similar to the CCW is the X-wmg mentioned Included in the treatment of simulator visual information rotor, built from high-strength composite materials, which can be processing are field of view, resolution, contrast and color, per- stopped in flight and locked at a fixed angle to the fuselage in order spective and distortion, stereoscopic effects, depth of focus, and to improve lift and control at high speeds Also discussed is the dynamic response Motion generation systems, as well as the effects VATOL concept as applied to RPVs D M W of pitch, roll, yaw, sway, heave and surge motions on pilot behavior receive attention In addition, problems such as turbulence modeling and loss of control at the extremes of the aircraft maneuvering A78-29207 A method of calculating ILS approach sur- envelope are discussed J M B faces L Marquma Sanchez (Escuela Tecnica Superior de Ingemeros Aeroniuticos, Madrid, Spain) Airport Forum, vol 8, Feb 1978, p 9-12, 14 A78-29215 The aerodynamic behaviour of fully inflated A mathematical analysis is presented for ILS which expands the parachutes R M Ayres Aeronautical Journal, vol 82, Jan 1978, p obstacle free room an approaching aircraft can use to maneuver It is 38-44 15 refs Research supported by the Ministry of Defence and proposed that the first section of the instrument approach surface be Science Research Council replaced by one horizontal plane, immediately followed by a second Hydrodynamic theory as applied to three-dimensional objects section with a slope of 2 5 percent The 14 3 percent transition undergoing large oscillations at low speeds was adopted to model the surface slope could be replaced by a slope of 166 percent, and its aerodynamic behavior of fully inflated parachutes, the computer lower edge limited to a line parallel with the runway center line model is capable of simulating parachute descent behavior studied in DMW wind tunnel test data Inertia coefficients for parachute canopies are developed, and scale effects for the model parachutes are considered A78-29208 More public consultation on airport plans. L The parachute canopy force field as described by hydrodynamic P Michaels Airport Forum, vo\ 8, Feb 1978, p 25, 26, 28 (5 ff) theory appears to give an accurate representation of the descent 11 refs In English and German behavior of conventional flat circular canopies J M B This paper presents a critical review of airport planning over the last 20 years, stressing that the situation which has existed in the past, namely that almost every mid-size community wanted an airport has changed in the sense that airports must now be A78-29221 Microwave landing systems F Pogust (Cutler- considered within the framework of long range environmental Hammer, Inc , AIL Div , Deer Park, N Y ) IEEE Spectrum, vol 15, planning Thus, airport planning can no longer be internalized, i e , Mar 1978, p 30-36 concerned only with the requirements of air traffic in its vicinity The article discusses various types of microwave landing systems Instead, air transport must be integrated into a total system of (MLS), including the time reference scanning beam and the Doppler transportation, with attention to the health of the environment and system The development of the MLS is outlined, noting the primary the quality of life in the community it serves DMW deficiencies in instrument landing systems, and the introduction of Ground Control Approach (GCA) systems and Traffic Control and A78-29209 How to make an airport unattractive to birds Landing Systems (TRACALS) The implementation of the scanning- J Hild (Federal German Defence Geophysics Bureau, Cologne, West beam landing system, yielding an improved signal path at low Germany) Airport Forum, vol 8, Feb 1978, p 49, 50, 52-56 In earth-grazing angles, is reviewed Scanning-beam landing techniques English and German developed by the U S Navy are described S C S The paper presents methods for modifying the environment around airports to discourage the habitation of birds The experience of the German air force is used as a model Among the methods A78-29295 * # Flight simulation - A vital and expanding considered are siting dumps far from runways, allowing grass to technology in aircraft development P A Reynolds (Calspan Corp, grow long and remain damp (because this environment is less suitable Buffalo, NY) and G W Hall (NASA, Ames Research Center, for the growth of large bird colonies), and allowing the growth of Moffett Field, Calif) American Institute of Aeronautics and woods and thickets in the airport vicinity (because this habitat is Astronautics, Annual Meeting and Technical Display, 14th, Wash- suitable for smaller birds, which present less of a hazard to air ington, DC, Feb 7-9. 1978, Paper 78-337 11 p 28 refs traffic) DMW Flight simulation, both ground and m-flight, is experiencing major technological improvement and growth The increased capabilities are providing new opportunities for support of the aircraft development process The development of faster digital computers, A78-29213 Factors influencing schedule reliability in improved visual displays, better motion systems and increased international operations R J Yates (Qantas Airways, Ltd , Sydney, interest in simulation fidelity has improved the ground simulator to Australia) Aeronautical Journal, vol 82, Jan 1978, p 1-11 the point where it accomplishes a major portion of the aircraft Scheduling problems encountered by an international airline development before work on the flight article begins The efficiency operating long-distance routes between the Northern and Southern of the ground simulator as a forecaster for the flight testing phase is Hemispheres are discussed Timetable setting, which depends on becoming well established In-flight simulation is properly being used curfews in effect at the airports of arrival and departure, is to bridge the gap between the ground simulator and the flight test considered, variations in flight time due to more or less favorable article Simulation provides the vital link between analysis, aero- wind components are also mentioned Airport departure delays dynamic tests, and subsystem tests and the flight test article This caused by aircraft defects, government authorities, passenger and paper describes the latest advances in flight simulation and its baggage transport, ramp handling and crew relief problems also increasing role in the aircraft development process (Author) receive attention J M B

A78-29326 * # Steady-state unbalance response of a three- A78-29214 Current problems of flight simulators for disk flexible rotor on flexible, damped supports. R E Cunningham research K J Staples (Royal Aircraft Establishment, Bedford, (NASA, Lewis Research Center, Cleveland, Ohio) American Society Hants, England) Aeronautical Journal, vol 82, Jan 1978, p 12-32 of Mechanical Engineers, Design Engineering Technical Conference, 34 refs Chicago, III, Sept 26-29. 1977, Paper 41 p 15 refs Computation systems, visual information processing and motion Experimental data are presented for the unbalance response of a systems of flight simulators used for research are discussed In flexible, ball bearing supported rotor to speeds above the third lateral particular, the application of distributive processing and the adoption bending critical Values of squeeze film damping coefficients

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obtained from measured data are compared to theoretical values Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut obtained from short bearing approximation over a frequency range fur Aeroelastik, Gottingen, West Germany) Zeitschnft fur Flug- from 5000 to 31,000 cycles/mm Experimental response for an wissenschaften und Weltraumforschung, vol 2, Jan -Feb 1978, p undamped rotor is compared to that of one having oil squeeze film 43-51 13 refs dampers at the bearings Unbalances applied varied from 0 62 to 15 1 Analytical solutions are presented for the unsteady aerodynamic gm-cm (Author) pressure distributions on slender ellipsoids of revolution, oscillating harmonically in subsonic compressible flow The governing potential equation is first transformed into the classical Helmholtz wave A78-29327 * ft 'Chain pooling' model selection as developed equation by applying a gauge transformation and a coordinate scale for the statistical analysis of a rotor burst protection experiment A transformation Then, with introduction of nonorthogonal prolate G Holms (NASA, Lewis Research Center, Cleveland, Ohio) spheroidal coordinates, the wave equation is solved for the prescribed American Statistical Association, Annual Meeting, 137th, Chicago, body surface and flow field boundary conditions through application lll,Aug 15-18, 1977, Paper 60 p 18refs of the method of separation of variables For a variety of slender A statistical decision procedure called chain pooling had been spheroids, performing harmonic rigid body plunging and pitching developed for model selection in fitting the results of a two-level oscillations, the unsteady aerodynamic pressure on the body surface fixed-effects full or fractional factorial experiment not having is calculated These analytical results are compared to corresponding replication The basic strategy included the use of one nominal level experimental results and to numerical results obtained from a panel of significance for a preliminary test and a second nominal level of approach and from Slender-Body Theory (Author) significance for the final test The subject has been reexammed from the point of view of using as many as three successive statistical model deletion procedures in fitting the results of a single experi- A78-29401 # The helicopter as a control object (Vertolet ment The investigation consisted of random number studies in- kak ob'ekt upravlenna) S lu Esaulov, 0 P Bakhov, and I S tended to simulate the results of a proposed aircraft turbine engine Dmitnev Moscow, Izdatel'stvo Mashmostroenie, 1977 192 p 38 rotor-burst-protection experiment As a conservative approach, popu- refs In Russian lation model coefficients were chosen to represent a saturated 2 to The helicopter is considered as a plant or control object in the the 4th power experiment with a distribution of parameter values analysis of helicopter motion Equations of motion are obtained for unfavorable to the decision procedures Three model selection the helicopter with articulated suspended absolutely rigid blades by strategies were developed (Author) taking into account six degrees of freedom Characteristics of some types of main rotors are examined A simplified linearization of the A78-29330 * # General aviation energy-conservation research helicopter equations of motion are obtained separately for forward programs at NASA-Lewis Research Center E A Willis (NASA, and lateral motion by substituting the resultant for the main rotor Lewis Research Center, Cleveland, Ohio) Western Michigan Univer- The dependence of the dynamics of helicopter motion dynamics on sity, Conference on Energy Conservation in General Aviation, the forward speed is analyzed M L Kalamazoo, Mich , Oct 10, 11, 1977, Paper 23 p 14 refs A review is presented of non-turbine general aviation engine programs underway at the NASA-Lewis Research Center in A78-29478 Effect of reliability programs on life cycle cost Cleveland, Ohio The program encompasses conventional, lightweight A case history R G Bertschy (Harris Corp, Syosset, NY) diesel and rotary engines Its three major thrusts are, in order of (Society of Reliability Engineers, Annual Canadian Symposium on priority (1) reduced SFCs, (2) improved fuels tolerance, and (3) Reliability Engineering, 4th, Ottawa, Canada, Oct 13, 14, 1977) reducing emissions Current and planned future programs in such Microelectronics and Reliability, vol 17, Jan 1978, p 914 areas as lean operation, improved fuel management, advanced cooling The effects of TACAN test set reliability programs on life cycle techniques and advanced engine concepts, are described These are costs (LCC) of a specified TACAN test instrument are examined The expected to lay the technology base, by the mid to latter 1980s, for numbers of reliability problems which have been prevented or passed engines whose total fuel costs are as much as 30% lower than today's on to production or field are identified for the following reliability conventional engines (Author) activities design review (DR), failure analysis (FA), reliability demonstration, DR + FA, full reliability program, and no reliability A78-29334 Optimum tail plane design for artificially program The LCC for the full reliability program is used as the stabilized aircraft (Optimale Leitwerksauslegung fur Flugzeuge baseline since that represents the actual program for which costs are kunstlicher Stabihtat) G Sachs (Munchen, Hochschule der Bundes- available It is shown that the implementation of design review or wehr, Neubiberg, West Germany) Ze/tschrift fur Flugwissenschaften failure analysis would not be as cost effective as the combination of und Weltraumforschung, vol 2, Jan -Feb 1978, p 1-10 12 refs In the two The full reliability program chosen by the US Air Force for German the TACAN test set program proves to be the most effective The paper deals with optimum tail plane influence on drag and approach in reducing the total LCC S D lift in trimmed flight and with the possibility of utilizing the lift and drag optimum c g range in designs of artificially stabilized aircraft A A78-29479 The AN/ARC-164 radio - Life-cycle-cost simple relation of wing tail interference drag resulting from mutual savings W H Boden (Magnavox Government and Industrial Elec- vortex interaction is developed Then, relations for minimum tronics Co , Ft Wayne, Ind ) (Society of Reliability Engineers, trimmed drag and for the drag optimum c g position are presented Annual Canadian Symposium on Reliability Engineering, 4th, It is shown how to design the tail plane so that the drag increase Ottawa, Canada, Oct 13, 14, 19771 Microelectronics and Reliabili- caused by c g deviation from the drag optimum c g position remains ty, vol 17, Jan 1978, p 15-23 small In regard to lift effects, it is shown how the maximum The life-cycle-cost (LCC) model for the new US Air Force/Army trimmed lift can be increased by full utilization of tail lift potential 10-watt UHF radio AN/ARC 164 deals with three increments of Then, it is described that the usable c g range is determined by costs the original acquisition cost of the hardware, the initial control requirements Finally, it is examined how the optimum drag logistics cost for documentation, training, spares, etc , and the cost and lift c g range can be made compatible with the usable c g range of recurring logistics to support the radio The discussion focuses on determined by control requirements (Author) the LCC verification test designed to determine whether the radio meets its specified reliability and maintainability criteria The most important economies achieved by MTBFs and MTTRs appears to be the reduction of Air Force personnel requirements, both at the base A78-29338 Prediction of the unsteady airloads on har- avionics and at the depot Recommendations for future programs are monically oscillating spheroids based on an analytical solution of the to better identify cost drivers, to simplify the LCC model, to accept governing wave equation K -L Chao and H Forschmg (Deutsche the principle of separating the LCC verification test and the real

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world, and to gear the verification plan to intended performance A78-29588 ff Properties of fuels used in the Czechoslovak SD aircraft industry (Vlastnosti pahv pouzivanych v Cs. leteckem prumyslu) J Krotky (Konference na thema Regulace Leteckych A78-29582 # Influence of structural components of a by- Proudovych Motoru, Velesm, Czechoslovakia, June 1-3, 19761 pass engine on its flight characteristics (Vliv konstrukcnich prvku Zpravodai VZLU, no 4, 1977, p 181-187 In Czech dvouproudoveho motoru na jeho letove vlastnosti) T Etlik and Z Those characteristics of jet engine fuels that might influence the Masek (Konference na thema Regulace Leteckych Pmudovych reliability of the fuel system are analyzed Particular attention is Motoru, Velesm, Czechoslovakia, June 1-3, 19761 Zpravodai VZLU, given to antiwear properties, lubricating ability, and corrosive action no 3, 1977, p 103-112 In Czech Causes of fuel pollution by mechanical microparticles, water, and Increasing the by-pass ratio is discussed as a possible means of microorganisms are examined Higher standards for fuel purity are satisfying the increased demands for greater values of the takeoff/ called for PTH cruise thrust ratio in STOL aircraft To achieve a by-pass ratio greater than 10 it is necessary to use a fan and reversible rotor blades However, the low specific thrust and low nozzle exit velocity in the A78-29589 ff Mam characteristics of the ADT 4000-4100 outer circuit complicate the aerodynamic solution of the fan for digital computer for a hybrid computing system (Zakladm charak- large mass flow rate The resulting constraint makes it impossible to tenstiky cislicoveho pocitace ADT 4000-4100 pro hybndni vy- design and build by-pass engines of this design type with by pass pocetni system) P Neustupa (Konference na thema Regulace ratio greater than 10-12 PTH Leteckych Proudovych Motoru, Velesm, Czechoslovakia, June 1-3, 1976) Zpravodai VZLU, no 4, 1977, p 189-192 In Czech A78-29583 ff Control of aircraft turbine engine acceleration The requirements on a computer for modeling a modern jet (Rizeni rozbehu leteckych turbmovych motoru) J Muller (Kon- engine are examined The merits of analog and digital machines for ference na thema Regulace Leteckych Proudovych Motoru, Velesm, these purposes are compared A brief description of the ADT 4000 Czechoslovakia, June 1-3, 1976) Zpravodai VZLU, no 3. 1977, p desk computer with operational memory of 16K words and 16 113-122 In Czech (maximum) interface panels, and the larger version ADT 4100 with Methods of controlling the transient processes in gas turbine operational memory of 32K words and 56 interface panels, is given engines by using suitable combinations of the thermodynamic Performance characteristics are summarized, and elements of the similarity variables of the engine are discussed Two main types of operating system are enumerated PTH controllers are examined controllers giving the fuel as a function of the thermodynamic variables, and feedback controllers controlling the angular acceleration of the rotor For both of these types of controllers a knowledge of the total pressure at the engine inlet is A78-29590 H Determining the reliability requirements of sufficient Simple control algorithms are given for designing a aircraft engine control systems during design stage (Pozadavky na complete controllpr, including a controller for the steady state spolehhvost projektovanych soustav rizeni leteckych motoru) M PTH Svoboda (Konference na thema Regulace Leteckych Proudovych Motoru, Velesm, Czechoslovakia, June 1-3, 1976.) Zpravodai VZLU, A78-29584 ff Using simulation to determine the transfer no 4, 1977, p 193-201 6 refs In Czech function of the electronic part of a control loop (Vyuzrti simulatoru The requirements on reliability of aircraft engine control k urceni prenosu elektronickeho clenu regulacm smycky) J Barton systems are expressed through the reliability characteristics of the (Konference na thema Regulace Leteckych Proudovych Motoru, repair parts The requirements are derived from acceptable safety Velesm, Czechoslovakia, June 13, 1976) Zpravodai VZLU, no 3, levels and the criterion of attaining optimal cost effectiveness of the 1977, p 123-131 7refs In Czech designed system PTH A method of determining the dynamic characteristics of the corrector unit of a control system by simulating the dynamic A78-29641 * ft Investigation of interior noise in a twin-engine characteristics of an aircraft engine is proposed The transfer light aircraft J S Mixson, C K Barton (NASA, Langley Research function is simulated on an analog computer in real time and is used Center, Hampton, Va ), and R Vaicaitis (Columbia University, New in the model solution of a gas turbine engine with actual parts of the York, N Y ) Journal of Aircraft, vol 15, Apr 1978, p 227-233 26 control circuit PTH refs This paper describes experimental studies of interior noise in a A78-29586 tt Use of a stepping motor for measuring fuel twin-engine, propeller-driven, light aircraft An analytical model for quantity in a digital system for control of rotational speed (Pouzrti this type of aircraft is also discussed Results indicate that interior krokoveho akcmho clenu k rizeni mnozstvi paltva v obvodu cislicove noise levels in this aircraft due to propeller noise can be reduced by regulace otacek) J Muller (Konference na thema Regulace Le- reducing engine rpm at constant airspeed (about 3 dB), and by teckych Proudovych Motoru, Velesm, Czechoslovakia, June 1-3, synchrophasing the twin engines/propellers (perhaps up to 12 dB) 1976) Zpravodai VZLU, no 4, 1977, p 161-170 16refs In Czech Ground tests show that the exterior noise pressure imposed on the The possible effect of the dynamics of the stepping motor of a fuselage consists of a complex combination of narrow-band har- fuel valve on the transient characteristics of rotational speed control monics due to propeller and engine exhaust sources This noise is is analyzed The lower stopping speed of the stepping motor as reduced by about 20-40 dB (depending on the frequency) by compared to a valve with proportional characteristic must be taken transmission through the sidewall to the cabin interior The into account PTH analytical model described uses modal methods and incorporates the flat-side geometrical and skin-stringer structural features of this light A78-29587" # Properties of hydraulic servomotor controlled aircraft (Author) by flapper valve or by edge valve (Vlastnosti hydraulickeho servo- motoru nzeneho klapkou-tryskou nebo nozovym ventilem). E A78-29642 * # Low-speed test limit of V/STOL model Heriban /Konference na thema Regulace Leteckych Proudovych located vertically off-center S Shmdo and W H Rae, Jr Motoru, Velesm, Czechoslovakia, June 1-3, 1976 > Zpravodai VZLU, (Washington, University, Seattle, Wash ) Journal of Aircraft, vol 15, no 4, 1977, p 171-179 In Czech Apr 1978, p 253, 254 7 refs Grants No DA- The equation of motion of the hydraulic servomotor in a ARO(D)-3M24-G1114,No NGR-48-002-035 turbojet engine control system is derived On the basis of this, the A vertically off-centered V/STOL model - a 2-ft-diam three- dynamical parameters are determined as functions of fuel pressure in bladed aluminum propeller operating in a rotor mode - is tested in an the controlled chamber Special attention is given to the influence of 8 by 12 ft wind tunnel with and without ground plane along with an the real flow characteristics of the nozzle on the dynamic properties associated 3 by 4 5 ft test section insert The objective was to assess of a hydraulic servomotor P.T H the effect of the vertically off-centered model on the low-speed test

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limit The aerodynamic data of the model at a constant negative In the present paper, the occurrence of pilot error is discussed in angle of attack (-3 deg) are recorded at selected tunnel dynamic terms of the skill/difficulty balance The application of information pressures to provide adequate data points to define the model lift theory to the evaluation of the difficulty of pilot tasks is examined, variation with respect to the tip speed ratio The adverse effect of the and a method of optimizing the arrangement of instruments on the rotor low-speed test limit is observed in the form of lift change with instrument panel to facilitate the pilot's task is outlined A logical respect to the tip speed ratio A major conclusion is that for rotors basis for flight safety analysis is formulated, along with requirements tested with a ground plane or in the vicinity of the floor, the ratio of for aircraft and crew V P distance between floor and model to rotor radius defines the low-speed test limits S D A78-29712 Computation of the pressure on the surface of a fuselage with a wing in an ideal fluid L A Maslov and V P lush in A78-29643 * # Handling qualities of aircraft in the presence (Akademua Nauk SSSR, Izvestua, Mekhanika Zhidkostt i Gaza, of simulated turbulence I D Jacobson and D S Joshi (Virginia, May-June 1977, p 110-115) Fluid Dynamics, vol 12, no 3, Jan University, Charlottesville, Va ) Journal of Aircraft, vol 15, Apr 1978, p 433-438 Translation 1978, p 254-256 Grant No NGR-47-005-208 A method proposed by White (1952) for calculating the surface A previous paper (1977) has presented results from flight pressure on a fuselage is extended to a fuselage/wing configuration A simulator experiments on mstrument-flight-rule handling-quality distinctive feature of the extended method is the technique studies of a STOL-type aircraft in the presence of various models of developed for solving the basic integral equation The technique is simulated turbulence (Gaussian, modified Gaussian, Rayleigh, and shown to reduce the computational labor without impairing ac- variable length and intensity, VLI) In this paper, additional results curacy V P are presented for flight simulator experiments on visual-flight-rule approach landings of a STOL-type aircraft Pilot opinion ratings of the landing approach with visual display are analyzed to determine A78-29718 Drag formula for elongated aircraft noses M the most realistic turbulence model and to identify the variables that I Folle (Akademua Nauk SSSR, Izvestna, Mekhanika Zhidkosti i critically affect the handling quality of aircraft in turbulence It is Gaza, May-June 1977, p 156 160 ) Fluid Dynamics, vol 12, no 3, shown that turbulence simulated by a VLI model adequately match Jan 1978, p 472-476 6 refs Translation the desired statistical properties of real atmospheric turbulence, and A drag formula in the framework of linear theory is obtained for that aircraft handling quality and pilot task performance are the case of low supersonic speeds for an ob|ect whose elongated critically affected by turbulence Realistic turbulence models present forebody in cross section is an n-rayed star which undergoes a greater difficulty in controlling the aircraft than a simple Gaussian smooth transition to a circular midsection The solution of the wave model S D equation for the elongated forebody is considered, and the drag of a reference cylindrical surface is calculated M L A78-29657 Product support for French equipment used by civil aviation companies (L'apres-ven'e des equipements francais A78-29720 Normal force of a flat triangular wing in a aux compagnies aenennes civiles) P Gravelle (Societe Francaise supersonic flow V I Lapygm (Akademua Nauk SSSR, Izvestna, d'Equipements pour la Navigation Aenenne, Division Apres-Vente, Mekhanika Zhidkosti i Gaza, May-June 1977, p 162-164 ) Fluid Orly, France) L'Aeronautique et I'Astronautique, no 68, 1978, p Dynamics, vol 12, no 3, Jan 1978, p 479,480 8 refs Translation 11 16 In French In numerical calculations for conditions of flow with bow shock Product support is discussed from the viewpoint of the aviation wave attached to a leading edge, the coefficient of normal force of a equipment construction industry Concepts of reliability and windward side of a flat delta wing depends on a certain parameter for maintenance of equipment are examined, and the interrelationship of a broad range of conditions For engineering calculations, a simple air company and equipment company desires within the framework relationship can be obtained by representing these characteristics in of government regulation of the industry is considered Several kinds the form of laws of similarity Two cases in which the normal force of equipment guarantees are surveyed, and problems caused by arising on the windward side of the wing do not depend on the sweep product support delays are described M L angle are analyzed M L A78-29777 * # Preliminary design of composite wings for A78-29672 # Theory of dolphin-style sailplane flight and buckling, strength and displacement constraints J H Starnes, Jr the principles of dynamic flight II (Teoria przelotu szybowcowego (NASA, Langley Research Center, Structures and Dynamics Div , metoda delfmowama oraz zasady lotu dynamicznego II) J Hampton, Va ) and R T Haftka (Illinois Institute of Technology, Sandauer (Instytut Lotnictwa, Warsaw, Poland) Techn/ka Lotnicza i Chicago, III ) In Structures, Structural Dynamics and Materials Astronautyczna, vol 33, Feb 1978, p 8-10 5 refs In Polish Conference, 19th, Bethesda, Md , April 3-5, 1978, Technical Papers The current status of the theory of dolphin-style flight is New York, American Institute of Aeronautics reviewed, and the associated aerial tactics are discussed The optimal and Astronautics, Inc, 1978, p 1-13 10 refs Grant No NsG-1266 flight parameters under simulated meteorological conditions are (AIAA 78-466) analyzed, and the basic principles of dynamic flight are outlined An unstiffened panel buckling constraint for balanced, sym- Some aspects of using Abzug's speed ring for cloud street flying are metric laminated composites is included on the global design level in examined V P a mathematical programming structural optimization procedure for designing wing structures Constraints are introduced by penalty A78-29673 # Aircraft and helicopter cockpit noise (Halas w functions, and Newton's method based on approximate second kabmach samolotow i smiglowcow) A Rudiuk (Instytut Lotnictwa, derivatives of the penalty terms is used as the search algorithm to Warsaw, Poland) Technika Lotnicza i Astronautyczna, vol 33, Feb obtain minimum-mass designs Constraint approximations used 1978, p 10-14 6 refs In Polish during the optimization process contribute to the computational In the present paper, the detrimental influence of cockpit noise efficiency of the procedure A criterion is developed that identifies on pilot hearing and reactions is studied as a function of noise the appropriate conservative form of the constraint approximations duration and intensity The acoustic spectrum is analyzed, and an that are used with the optimization procedure Minimum-mass design attempt is made to establish acceptable noise level standards The results are obtained for a multispar high-aspect-ratio wing subjected need for reducing noise in crop-duster cockpits is noted V P to material strength, minimum-gage, displacement, panel buckling A78-29674 # Systematic analysis of safety in aviation II and twist constraints The material systems considered for the (Systemowa analiza bezpieczenstwa w lotnictwie II) J Morawski examples are all graphite-epoxy, graphite-epoxy with boron-epoxy and T Smolicz Technika Lotnicza i Astronautyczna, vol 33, Feb spar caps, and all aluminum The composite material designs are 1978, p 23-25 13 refs In Polish shown to have an advantage over the aluminum designs since they

278 A78-29812

can often satisfy additional constraints with only small mass A78-29806 # The use of transient testing techniques in the increases (Author) Boeing YC-14 flutter clearance program R S Imes (Boeing Co , Seattle, Wash ), W P Jennings (ASTEC Engineering Co , Renton, Wash ), and N L Olsen (Hewlett-Packard Co , Bellevue, Wash ) In A78-29785 ~ Crashworthmess of aircraft fuselage structures Structures, Structural Dynamics and Materials Conference, 19th, R C Tennyson, J S Hansen, H Teichman (Toronto, University, Bethesda, Md, April 3-5, 1978, Technical Papers Toronto, Canada), F Cicci, and M loannou (De Havilland Aircraft New York, American Institute of Aeronautics and of Canada, Ltd, Downsview, Ontario, Canada) In Structures, Astronautics, Inc , 1978, p 295-299 5 refs (AIAA 78-505) Structural Dynamics and Materials Conference, 19th, Bethesda, Md , Excitation and analysis techniques used in transient testing are April 3-5, 1978, Technical Papers New York, discussed together with the results of YC-14 tests employing these American Institute of Aeronautics and Astronautics, Inc , 1978, p methods The YC-14 flutter clearance program used transient 101-109 12 refs National Research Council of Canada Grant No techniques in wind tunnel model, ground vibration, electrical flight A-9185, Canadian Transportation Development Agency Contract No control system-structural interaction, and flight flutter tests Results 01SU,T8200-6-6549 (AIAA 78-477) presented indicate that detailed data can be obtained using transient A combined analytical and experimental programme was under- techniques at costs and flow times lower than those associated with taken to study the dynamic structural response of aluminum model conventional techniques (Author) aircraft fuselage structures A drop-test gantry was used to provide a simulation of the wheels-up landing condition for both level and oblique angle impacts on a concrete pad for a range of wing loads A78-29809 tt Experimental investigation of composite wing and vertical descent velocities Dynamic measurements of strain and failure J H Pimm (Vought Corp, Dallas, Tex) In Structures, g loads at discrete locations were obtained together with high speed Structural Dynamics and Materials Conference, 19th, Bethesda, Md , photographs of the failure modes for comparison with a lumped April 3-5, 1978, Technical Papers New York, mass-stiffness model of the structure using a finite element approxi- American Institute of Aeronautics and Astronautics, Inc , 1978, p mation (Author) 320-324 7 refs Contract No F33615-73 C-5066 (AIAA 78-509) A premature structural failure occurred during static testing of the No 1 composite outer wing for the A-7D aircraft Failure was at A78-29794 * A fail-safe analysis of a spanwise wing-panel 120% of design limit load (150% required) A thorough investigation splice J M Anderson (Georgia Institute of Technology, Atlanta, was initiated to determine the cause of this failure Experimental and Ga), C S Chu, and J F Malluck (Lockheed-Georgia Co , Marietta, analytical methods were utilized This paper emphasizes the experi Ga ) In Structures, Structural Dynamics and Materials Conference, mental activity and presents correlation to current failure theories A 19th, Bethesda, Md, April 3-5, 1978, Technical Papers discussion of events which led to the wmg failure and conclusions New York, American Institute of Aeronautics and made from the investigation are provided The wing was modified Astronautics, Inc, 1978, p 183-186 5 refs (AIAA 78-487) and subsequently qualif'ed (Author) Transient dynamic analyses have been performed for a typical wing-panel assembly The assembly consists of a center panel and two side panels containing short edge cracks at the spanwise splices A78-29811 ff Cutout reinforcement of stiffened cylindrical The analysis employs the finite-element method and exploits a shells J A Cervantes (USAF, Flight Dynamics Laboratory, Wright- special singularity element to represent the crack-tip neighborhood Patterson AFB, Ohio) and A N Palazotto (USAF, Institute of Transient stress-intensity factors are determined for the edge cracks Technology, Wright-Patterson AFB, Ohio) In Structures, Structural following failure of the center panel Stress-intensity factors corre- Dynamics and Materials Conference, 19th, Bethesda, Md , April 3-5, sponding to instantaneous failure of the center panel are sub- 1978, Technical Papers New York, American stantially higher than a static prediction An additional case of Institute of Aeronautics and Astronautics, Inc , 1978, p 331-339 5 less-than-mstantaneous failure is analyzed and an assessment of the refs (AIAA 78-512) effect of fastener stiffness is presented (Author) A study was carried out to determine the optimum placement and volume of a reinforcing frame around a cutout in an axially loaded stringer and ring and stringer stiffened cylindrical shell The problem was analyzed using the linear bifurcation portion of STAGS (Structural Analysis of General Shells) Four parameters were varied stringers versus rings and stringers, cutout size, ratio of frame volume A78-29805 f? A theoretical technique for analyzing aero- to cutout volume, and frame position It appeared that in most cases elastic stability of bearmgless rotors D H Hodges (U S Army, the position with the frame next to the cutout edge was the most Aeromechanics Laboratory, Moffett Field, Calif) In Structures, effective This can be attributed to the frame's ability to delay the Structural Dynamics and Materials Conference, 19th, Bethesda, Md , onset of local buckling However, there was a relative maximum in April 3-5, 1978, Technical Papers New York, the frame distance versus critical load curves for a frame positioned American Institute of Aeronautics and Astronautics, Inc , 1978, p away from the cutout edge at a low ratio of frame to cutout volume 282-294 22 refs (AIAA 78-503) (Author) A technique is introduced for aeroelastic stability analysis of certain hmgeless helicopter rotors termed bearmgless because of their A78-29812 # Stress analysis of typical flaws in aerospace lack of a pitch-change bearing The rotor is modeled as three or more structural components using 3-D hybrid displacement finite element rigid blades each joined to the hub by means of a flexible appendage method S N Atluri (Georgia Institute of Technology, Atlanta, Ga ) known as the flexbeam or strap The pitch-control system twists the and K Kathiresan In Structures, Structural Dynamics and Materials flexbeam to provide blade pitch change The analysis is capable of Conference, 19th, Bethesda, Md , April 35, 1978, Technical Papers implicitly treating the aeroelastic couplings that arise from the New York, American Institute of Aeronautics pitch-control geometry, the equilibrium deflected shape of the and Astronautics, Inc , 1978, p 340-350 28 refs Research sup- flexbeam, and the built-in angular offsets of the flexbeam and blade ported by the Georgia Institute of Technology, Grant No AF The stability of the system in both hub-fixed motion and coupled AFOSR 74-2667 (AIAA 78-513) rotor-body motion is considered The same basic parameters that An assumed hybrid displacement finite element method for the influence hmgeless rotor stability also influence bearmgless rotor solution of modes I, II and III stress intensity factors which vary stability Aeroelastic couplings can be chosen to stabilize most soft along an arbitrary curved three-dimensional crack front in structural inplane configurations for the hub-fixed case The same parameters components was developed for linearly elastic materials The present will also, under certain conditions, stabilize the coupled rotor-body method can be applied to three-dimensional mixed mode fracture system in hovering flight (air resonance) (Author) problems with complex crack and structural geometries Special

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crack front singular elements were developed where proper The basic principles of designing modern gyroscopic instruments asymptotic solutions for displacements and stresses are embedded for stabilizing the attitude of flight vehicles and orienting antennas The above finite element method is presently used to analyze some and optical systems are outlined The dynamic errors of gyroscopic important and typical flaw (fracture) problems which are commonly sensitive elements are analyzed, and their influence on the precision encountered in aerospace structural component applications of stabilization and orientation is examined The design and (Author) parameters of some advanced gyroscopic instruments are discussed, A78-29820 # A lifting surface theory based on an unsteady with particular reference to air-supported gyroscopes, gas floated linearized transonic flow model D D Liu (Northrop Corp , Aircraft spinning spheres, and free rotor gyroscopes V P Div , Hawthorne, Calif) In Structures, Structural Dynamics and A78-29906 Integrated Doppler/TACAN navigation Materials Conference, 19th, Bethesda, Md , April 3-5, 1978, Tech- through conformity with the least squares method - Analysis from nical Papers New York, American Institute of registered flight data (Integnerte Doppler /TACAN-Navigation durch Aeronautics and Astronautics, Inc, 1978, p 414-421 22 refs Ausgleichung nach der Methode der klemsten Quadrate - Erprobung Research supported by the Northrop Independent Research Program mit registnerten Flugdaten) K Ramsayer, M Reich, and W Scholler (AIAA 78-501) (Stuttgart, Univeriitat, Stuttgart, West Germany) (Deutsche Gesell- This paper presents the basic formulation of a unified unsteady schaft fur Ortung und Navigation, Kreiselsymposium, Stuttgart, West lifting surface method currently in progress, which would bridge the Germany, Sept 28, 29, 19771 Ortung und Navigation, no 4, 1977, purely subsonic and purely supersonic methods through the regime p 59-88 17 refs In German of linearized transonic flow An approximate transonic acceleration A Transall transport aircraft was used to test a composite system potential as well as its governing equation are derived The equation of navigation Directional impulses were measured by a Bendix includes a number of additional terms, which are due to mean flow Doppler radar DRA 12B, the magnetic course by a Sperry gyro- influence and have been ignored by previous investigators Con- platform SYP 820, and the aircraft distance and direction by an sequently, the transonic kernel functions are generalized based on on-board TACAN ARN 21B The data thus provided was subjected the concept of parabolic approximation to include the nonplanar to a computerized error analysis, and fitted to a least squares model case Numerical and analytical techniques to evaluate the transonic Attention is given to deviations in the data provided by the exact kernel functions will be described A Mixed Kernel Function location indicator, and to methods for correcting it The exponential procedure in combination with the oscillatory shock jump condition process is preferred to the window method as a means of data will be discussed Finally, assessments of various transonic kernel correction, because it is simpler D M W function methods are given (Author) A78-29907 Some test results concerning visibility of ob- A78-29822 tf Future trends in aircraft structural design and stacle and hazard beacons (Emige Versuchsergebnisse zur materials W A Stauffer (Lockheed California Co , Burbank, Calif ) Sichtbarkert von Hinderms- und Gefahrenfeuern) H -E Hoffmann In Structures, Structural Dynamics and Materials Conference, 19th, and R H Buell (Deutsche Forxhungs- und Versuchsanstalt fur Luft- Bethesda, Md, April 3-5, 1978, Technical Papers New York, und Raumfahrt, Institut fur Physik der Atmosphare, Oberpfaffen- American Institute of Aeronautics and Astronautics, Inc, 1978 11 hofen, West Germany) (Deutsche Gesellschaft fur Ortung und p (AIAA 78-465) Navigation, Kreiselsymposium, Stuttgart, West Germany, Sept 28, Future trends in the major fields of structures, dynamics and 29, 1977) Ortung und Navigation, no 4, 1977, p 89-97 6 refs In materials as applied to aircraft design are discussed In the field of German structures, the evolution of damage tolerance and durability require- Helicopter observations were used to determine maximum ments, commercial and military, is described and emerging trends for detection range for obstacle and hazard beacons A red 150 W the future identified In the field of dynamics and loads, improved obstacle beacon was detected in bright daylight at a distance of 2 load prediction methods, repeated loads spectra, and gust loads are km, and one hour after sunset at 7 km Horizontal standard visibility discussed from the standpoint of needed and attainable improve- ranged between 6 and 13 km No significant differences were noted ment In the field of materials, trends in the future development and between 100 and 150 W red obstacle beacons, but a 1000 W red potential of advanced aluminum alloys, titanium alloys, high-strength hazard beacon could be detected up to 6 km further than the steels, and advanced composites are presented Projections for obstacle beacons. The mast for the hazard beacons was detected production incorporation of these advances in new aircraft designs before the obstacle beacon during the day, but the reverse was true are made (Author) at night D M W

A78-29854 Geometric restitution of single coverage air- A78-29934 # Doppler MLS - The UK solution T Ford craft multispectral scanner data M M Ethndge and E M Mikhail Aircraft Engineering, vol 50, Feb 1978, p 4-7 (Purdue University, West Lafayette, Ind ) In Mapping with remote The ILS system for ATC is outdated and must be replaced This sensing data, Proceedings of the Second Annual William T Pecora paper presents an outline of the design and operating characteristics Memorial Symposium, Sioux Falls, S Dak , October 25-29, 1976 of the British Doppler MLS, which will permit precision approach Falls Church, Va , American Society of Photo- guidance over a wide angular area A source of radiation is moved at grammetry, 1977, p 382-392 9 refs constant velocity on the ground, and compared with a stationary In order to demonstrate the potential of MSS aircraft data, six frequency in an approaching aircraft The frequency difference restitution techniques are tested using four strips of actual data The provides a direct measurement of the angle of the receiver from the six techniques tested include the collineanty model, piecewise array boresight A unique frequency code is given for every angle in polynomials, weighted arithmetic mean, moving averages, meshwise the coverage D M W linear, and Gauss-Markov Since the Gauss-Markov technique has A78-29935 ff Fly-by-wire flight control R P G Collmson only been recently proposed, more discussion and computational Aircraft Engineering, vol 50, Feb 1978, p 8-13 results are presented A statistical evaluation was employed to Developments of automatic control systems for aircraft are determine the significance of various factors affecting the restitution outlined with attention to active controls These include sensors techniques, and results from this evaluation indicate that the which detect disturbances in flight stability and make automatic piecewise polynomial model is the optimum restitution technique of corrections by means of actuators and aerodynamic control surfaces those considered (Author) Advantages of active controls include improved handling and A78-29859 # Gyroscopic instruments of orientation and maneuvering, relaxed static stability margins, and direct lift control stabilization systems (Giroskopicheskie pribory sistem onentatsn i Also discussed are developments in fault detection technology, using stabilizatsn) D S Pel'por, lu A Osokin, and E R Rakhteenko digital data and fiber optics, and fault correction, using rate gyros Moscow, Izdatel'stvo Mashmostroenie, 1977 208 p 37 refs In and a quadruplex actuator The Boeing YC 14 is presented as an Russian illustration of up to date fly-by-wire technology D M W

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A78-29936 # Some lessons learned from aircraft accidents - memories used in the control system The prototype control system The engineering aspects E Newton Aircraft Engineering, vol 50, is subjected to evaluation J M B Feb 1978, p 16-23 Sources of aircraft failure (and disaster) are analyzed Major sources include material fatigue (25% of all accidents), fires, poor A78-30039 # The effect of hub fairings on wind turbine maintenance, misreading data, and defective engines Attention is rotor performance R E Wilson (Oregon State University, Corvallis, given to defects in the design and assembly of aircraft components Ore ) ASME, Transactions, Journal of Fluids Engineering, vol 100, and fail-safe criteria are discussed Murphy's Law (applied to Mar 1978, p 120-122 aviation) is cited, which states that if it is mechanically possible to Studies are made of the effect of hub fairings on the assemble a part incorrectly, someone, somewhere, sometime will do performance of a wind turbine The contribution of velocity change just that D M W to the torque is calculated and it is found that the effect on power may be either positive or negative Various hub fairings have been used to test both wind turbines and propellers It is shown that the design of an effective hub fairing must take into account the effect A78-29944 Critical considerations on the legal develop- of velocity change on torque, blade section aerodynamics, and the ment of personal liability with attention to air transportation potential flow around the center body in the rotor plane with (Kritische Betrachtung der gesetzlichen Entwicklung des Haftungs- reference to the specific center body being used S C S rechts der Personenbeforderung unter besonderer Berucksichtigung des Luftverkehrs) R Beme Zeitschnft fur tuft- und Weltraumrecht, vol 27, Mar 1978, p 3-14 46 refs In German A78-30096 Whither MLS F B Pogust (Cutler-Hammer, The question of an airline's liability to a passenger in case of AIL Div , Deer Park, N Y ) Journal of Air Traffic Control, vol 20, injury aboard an aircraft is examined with reference to German law Jan Mar 1978, p 8,9 regarding similar situations aboard a train Attention is given to the The concepts of commonality and proliferation are discussed international character of air traffic, noting that laws which might with reference to the use of microwave landing systems It is apply to German passengers on domestic airlines might not apply to suggested that, although common civil/military air navigation sys German passengers on foreign airlines, or to foreigners on German terns might have been desirable in the past, the situation is different airlines DMW for the case of MLS The reason for this conclusion is that the candidate systems for ICAO standardization were not conceived or A78-29945 Flying over the exclusive economic zone P P optimized as military tactical systems, which means that large-scale Heller Zeitschnft fur Luft- und Weltraumrecht, vol 27, Mar 1978, expenditures would be required to prove their military feasibility and p 15-17 10 refs to develop appropriate hardware The only advantage foreseen that The paper deals with legal problems arising from the definition would accrue to the armed services from adopting a standardized of the term 'high seas' In other words, does the 200 mile economic ICAO systems is that it would provide the ability to land at civilian zone, extending from the coastlines of many countries, constitute a airports during adverse weather, and cheaper alternative methods of part of the high seas in terms of aircraft overflight According to the achieving this ability are thought to exist Proliferation of landing Informal Composite Negotiating Text (ICNT), which followed the systems is said to be desirable since it would permit testing of various third UN conference on the Law of the Sea in 1977, the economic design approaches It is thought that the possibility of an alternative zone is not included in the term 'high seas' Thus, aircraft overflight system being chosen for standardization should not disturb users regulations become vague for this region and need to be legally who derive benefit from the system they selected M L defined DMW A78-30097 Landing systems - The Navy viewpoint D B A78-30002 Three-dimensional flow of hypersonic gas past Tuttle (U S Navy, Washington, D C ) Journal of Air Traffic Control, a thin airfoil A I Golubmskn and V N Golubkm (Tsentral'nyi vol 20, Jan-Mar 1978, p 19-22 Aerogidrodmamicheskn Institut, Zhukovskii, USSR) (Akademua A history of landing systems used by the USN is presented with Nauk SSSR, Doklady, vol 234, June 11, 1977, p 1032-1034) attention to the unique characteristics required for landings at sea Soviet Physics - Doklady, vol 22, June 1977, p 275, 276 8 refs Reasons why most landing systems used at sea were not incorporated Translation into Navy land airports and why some systems used at civilian or Formulas are derived for a low-aspect ratio thin wing at angle of other military airports were not adopted by the Navy are explained attack m hypersonic flow Its leeward side is in aerodynamic shadow, It is concluded that aging ground-controlled-approach (GCA) equip- while the windward side receives the main portion of aerodynamic ment should be retained throughout the 1980's and that a GCA loading Shock layer theory, with a small parameter epsilon defined update program should be initiated Modifications planned for the by density ratio for a strong shock, is used to analyze flow past the GCA update are surveyed A conversion to the national microwave windward surface Consideration is given to cases of a basic landing system (NMLS) in the mid-80's to mid-90's is planned with a 'Newtonian' flow and of a flow with conical symmetry (the formulas phase-out of GCA to follow M L obtained in this latter case are analogous to those for a delta wing) B J A78-30123 # Laser and optical methods of monitoring in aircraft construction (Lazernye i opticheskie metody kontroha v samoletostroenn) E T Vagner, A A Mitrofanov, and V N Barkov A78-30024 ff A reliable modular automatic system adapted Moscow, Izdatel'stvo Mashmostroeme, 1977 176 p 54 refs In to avionics controls Design through successive refinements - Produc- Russian tion (Automate sur et modulaire adapte aux regulations aviomques Consideration is given to the application of lasers and other ASMARA - Conception par raffmements successifs - Realisation) optical instruments to the quality control of assembly procedures m C Beounes Toulouse III, Universite, Docteur Ingenieur Thesis, aircraft production Particular attention is given to the monitoring of 1977 189 p 25 refs In French Research supported by the shapes and dimensions of aircraft parts, to the centering of parts via Direction des Recherches et Moyens d'Essais and SociSte Nationale laser beams, and optomechanical scanning systems for assembly B J d'Etude et de Construction de Moteurs d'Aviation A reliable modular control system for an aircraft turbine engine is developed through use of high-level integration circuits and A78-30124 # Helicopters Calculation of integral aero- hierarchical modeling and simulation The design process, which dynamic performance and air-technical data (Vertolety Raschet relies on successive refinements, makes use of PETRI nets for the mtegral'nykh aerodmamicheskikh kharaktenstik i letnc-tekhm- functional aspect, and state graphs associated with Markov processes cheskikh dannykh) L S Vil'dgrube Moscow, Izdatel'stvo Mashmo- for the reliability aspect Attention is also given to the processor and stroeme, 1977 152 p 59 refs In Russian

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Methods are outlined for calculating rotor performance and with attention to emulation versus direct digital synthesis and helicopter air-technical data within the framework of helicopter closed-loop simulation with actual hardware M L vortex theory Simplified methods of determining the induced velocity field of a rotor in hover and in vertical and horizontal flight A78-30253 Benefits of strapdown over gimbal INS sys- are described, along with methods of optimizing rotor blades for tems for aircraft application J C Shaw (Boeing Commercial various modes of helicopter operation The fundamentals of the Airplane Co , Seattle, Wash ) /Israel Annual Conference on Aviation theory of the blade-tip vortex sheet in horizontal flight are and Astronautics, 19th, Tel Aviv and Haifa, Israel, May 2, 3, 1977) examined, and the theory is applied to the determination of the Israel Journal of Technology, vol 15, no 1-2, 1977, p 11-21 11 aerodynamic moment and the components of the aerodynamic force refs arising in the rotor, and also to the determination of the flapping Independent laboratory and aircraft flight tests during 1975 of coefficient and inductive effects of rotors of a multirotor system three diverse potentially low-cost strapped-down (strapdown) mertial VP navigation systems (INS) have demonstrated the technical feasibility of a less-than one-nmi/h strapdown INS in an aircraft environment One system is an integrated strapdown air data sensor (ISADS) with A78-30175 # Weight design and the efficiency of passenger a projected production purchase price of S34K-41K per channel aircraft Volume 2 - Calculation of the center of gravity and Based on average industry data taken from a transport development moments of inertia of aircraft Weight analysis (Vesovoe proektirova- program, an ISADS type system is expected to have equivalent or nie i effektivnost' passazhirskikh samoletov Volume 2 - Raschet lower total cost of ownership than the non-IMS, conventional tsentrovki i momentov mertsn samoleta Vesovoi analizl V M avionics it replaces, thus providing INS functions for no additional Sheinin and V I Kozlovskn Moscow, Izdatel'stvo Mashmostroeme, cost A direct comparison is made between an equivalent gimballed 1977 208 p 68 refs In Russian INS and two strapdown INS approaches, orthogonal and skewed- Principles of construction design and weight-reduction methods axis, to establish the potential cost effectiveness of the strapdown are discussed with reference to the airframe, propulsion unit, and INS approach (Author) equipment Described procedures of weight analysis involve classification of the forms of efficiency, parametric analysis, comparison A78-30256 Performance of the ARAVA aircraft with rules, and reduction methods The significance and calculation of the wing-tip wmglets Y Eliraz and D Han (Israel Aircraft Industries, center of gravity of aircraft are explained, and applications of this Ltd, Lod, Israel) (Israel Annual Conference on Aviation and calculation to problems involving passenger aircraft are considered Astronautics, 19th, Tel Aviv and Haifa, Israel, May 2,3, 1977) Israel The calculation and experimental determination of aircraft moments Journal of Technology, vol 15, no 1-2, 1977, p 35-43 7 refs of inertia are described Wl L A wing-tip wmglet configuration installed on the twin-engine ARAVA aircraft was flight tested recently Cruise and climb performance have been evaluated, the main objective being to A78-30244 # Profile of the airport-development crisis R J establish the one engine out-climb case Much consideration was Hodge (TippetS-Abbett-McCarthy-Stratton, Washington, D C) given to evaluating the lateral-directional characteristics of the Astronautics and Aeronautics, vol 16, Apr 1978, p 39-44 5 refs aircraft, up to the maximum sideslip angles associated with FAR The rapid increase in the volume of air traffic necessitates requirements for this type of aircraft The wmglet configuration improvement in ATC, as well as the construction of new airports evolved from a series of wind tunnel tests earned out in a low-speed Prospects for both are evaluated in terms of cost, government wind tunnel The wind tunnel tests indicated and the flight tests later regulation, aircraft payload and economy, and location of various substantiated that the adoption of wmglets to a STOL twin-engined urban centers D M W aircraft is strongly affected by the overall lateral-directional characteristics, some of which are difficult to simulate in wind tunnel A78-30245 # Looking offshore at the airport future C J testing, mainly those associated with strong propeller power effects, Lord (Ralph M Parsons Co, Pasadena, Calif) Astronautics and dynamic behavior, and Reynolds numbers The tested configuration Aeronautics, vol 16, Apr 1978, p 45-49 9 refs reduced the induced drag at climb lift coefficients by 20%, with good Increases in the volume of air traffic is expected to present a correlation between wind tunnel and flight test data (Author) critical problem for US and world airports during the 1980s Solving the problem of the trailing vortex behind aircraft, together A78-30257 Evolution of the aircraft gas turbine engine M with the microwave landing system (MLS), should ease the crunch A Zipkm (General Electric Co , Advanced Engineering and Tech- somewhat New airports, however, will still be needed This paper nology Programs Dept , Cincinnati, Ohio) (Israel Annual Conference discusses the feasibility of locating airports offshore, with attention on Aviation and Astronautics, 19th, Tel Aviv and Haifa, Israel, May to cost and population density factors The Honolulu International 2, 3, 1977) Israel Journal of Technology, vol 15, no 1-2, 1977, p Airport is presented as an example of an operational off-shore 44-58 facility Off-shore airports in Hong Kong, using land fill from The history of the aircraft gas turbine engine is presented with excavations, and for Cleveland, using land reclaimed from Lake Erie attention to engine power (thrust) efficiency and weight as well as by a polder (dike), are considered for the near future D M W improvements in component technology The development of gas turbine technology and its role in aircraft design are considered, engine performance trends are examined, future challenges posed by technological and environmental concerns are indicated, and new A78-30252 New trends and problem areas in automatic systems/applications are reported ML flight control D McRuer (Systems Technology, Inc , Hawthorne, Calif ) (Israel Annual Conference on Aviation and Astronautics, A78-30259 Analytical and experimental fatigue program 19th, Tel Aviv and Haifa, Israel, May 2, 3, 1977) Israel Journal of for the Kfir main and nose landing gears B Abraham (Israel Aircraft Technology, vol 15, no 1-2, 1977, p 1-10 52 refs Industries, Ltd, Lod, Israel) (Israel Annual Conference on Aviation Two categories of automatic flight control are discussed - those and Astronautics, 19th, Tel Aviv and Haifa, Israel, May 2, 3, 1977) in which additional functions are the consequence of greater Israel Journal of Technology, vol 15, no 1-2, 1977, p 70-78 9 refs interdependence between airframe and controller, and those which This paper describes the program that was carried out on the represent a revolution in which digital/discrete replace analog/ Kfir main and nose landing gears in order to insure adequate service continuous controller elements Concepts in the first category life The fatigue program began in the detail design phase, next came include fhght-phase-dependent flight control system configurations, the development of loading spectra used for analysis and test A active control, and control precision improvement Changes in fatigue analysis was then performed for several suspected critical mechanization features of flight control systems are examined, and locations on both gears A flight-by flight fatigue test was performed system level problem areas in automatic flight control are described, on both landing gears with the aim of demonstrating four service-

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lifetimes of operation Design modifications were introduced based aircraft is examined for turboprop transport aircraft Acceptable on the results of these tests Finally, rational inspection and designs for the double-pane windows and for the elastic fasteners for replacement intervals were established for the main and nose gear, the interior panels are shown Acoustic characteristics of double some of which require monitoring of aircraft operations (Author) walls are examined Data on the effect of the distance of the propeller tips from the fuselage and engine speed on noise level in the cabin are presented P T H A78-30273 H The An-26 aircraft Construction and use (Samolet An-26 Konstruktsna i ekspluatatsiia) Zh S Chernenko, A78-30356 ff Basic fatigue curves of aircraft structures G S Lagosiuk, and B I Gorovoi Moscow, Izdatel'stvo Transport, (Zakladm unavove krivky leteckych konstrukci) V Kahanek 1977 342 p In Russian Zpravodaj VZLU, no 6, 1977, p 291-301 15 refs In Czech The An-26, based on the An 24, is a medium-distance twin- The elements of representing the fatigue characteristics of whole engine turboprop transport aircraft which can transport 5 5 tons of aircraft and their parts are presented Suitable S-N curves and Haigh freight 1000 km with a 435 kn^ cruising speed at a height of 6000 diagrams for light alloy structures, steel lugs, welded steel structures m Topics discussed include airframe construction, flight control, the and joints are taken from the literature for the purpose of designing undercarriage, the hydraulic system, the propulsion unit, high- new aircraft and calculating their life at the design stage Methods of altitude equipment, the deicing system, and transport and accom interpreting the fatigue curves and using them for life prediction of modations equipment The operation of some systems is explained aircraft parts are described P T H M L

A78-30351 tf Aircraft noise and its sources (Hluk let ad el a A78-30357 H Choice of engine design for small transport jeho zdroje) J Sulc Zpravoda/ VZLU, no 5, 1977, p 231-244 25 aircraft (Prispevek k volbe koncepce leteckeho motoru pro maly refs In Czech dopravm letoun) J Ruzek and E Henban Zpravodaj VZLU, no 6, Fundamental theories on noise sources in aircraft are reviewed 1977, p 303-308 In Czech The principles of noise generation and the acoustic properties of the The influence of the heat circuit parameters on the parameters principal noise sources are described, with attention given to piston of a bypass engine under conditions of ground running is analyzed engine exhaust processes, exhaust jets from jet engines, the com- The dependence of the optimal compression value in the blower on pressor of a jet engine, and airscrews and rotors The effect of these the bypass ratio, total air compression in the compressor, and the sources on noise levels in the cabin is examined, and the effects of total gas heat before the turbine is established The effect of the further sources such as the turbulent boundary layer and the air bypass ratio on the average fuel consumption and the blower size is conditioning system are also discussed Sonic boom is briefly analyzed, and it is shown that a turboprop engine gives more thrust considered P T H and has less fuel consumption than a bypass engine The method of reversing the thrust of a bypass engine by rolling up the fan rotor A78-30352 H Effect of noise on life of aircraft structure and blades is analyzed P T H design of parts resistant to acoustic loads (Vliv hluku na zivotnost letecke konstrukce a konstrukce casti odolnych proti akustickemu zatizeni) K Tyzner Zpravodaj VZLU, no 5, 1977, p 245-252 18 A78-30358 # The problem of the acoustic properties of the propeller and Q-fan type blower with regard to exterior and interior refs In Czech noise in transport aircraft (Prispevek k problematics akustickych The effect of aircraft noise on the fatigue strength of aircraft vlastnosti vrtule a dmychadla typu Q-fan z hlediska vnejsiho a structures, instruments, and systems is examined The design of parts vnitrmho hluku dopravnich letadel) R Eichler Zpravodaj VZLU, to withstand acoustic loading is described, and recommendations are no 6, 1977, p 309-316 11 refs In Czech given for the design of special antiacoustic equipment P T H The interior and exterior noise due to the power plant of a transport aircraft is examined The noise characteristics of ordinary A78-30353 ft Measuring noise m aircraft cabins (Mereni propellers are compared with those of a low-noise airscrew with hluku v kabmach letadel) P Marjanek Zpravoda/ VZLU, no 5, Qfan type blower The possibility of suppressing noise through 1977, p 253-258 5 refs In Czech proper use of present-day materials for passenger cabin walls is The complex acoustical engineering problem of measuring discussed P T H different types of noise in aircraft cabins is discussed The mam types of equipment used in such measurements are briefly characterized A typical measuring system, including the airborne part and the ground part of the system, is described Examples of noise spectra in a A78-30360 fi Fatigue life analysis of the L 13 /Blamk/ transport aircraft cabin are given which show how the amount of glider V Kahanek ZpravaVZLU.no Z-31, 1977 24 p 9 refs information on the frequency composition of noise depends on the A review of the service life analysis conducted on the L 13 bandwidth of the analysis procedure P T H Blanik wing and horizontal tail surfaces is given It covers all modes of operation, including take-off, flight training to a sailing syllabus as well as the glider handling on the ground The analysis is completed A78-30354 if Methods and equipment for testing for with results of the measurements in operating conditions, par- acoustic fatigue (Zkusebni metody a zanzeni pro zkouseni akusticke ticularly from the glider load assessment at winch launching The unavy) D Sejnost Zpravodaj VZLU, no 5, 1977, p 259261 In paper contains a program of fatigue testing of the wing and Czech horizontal tail surfaces mounts From the fatigue tests, those Methods for testing the acoustic fatigue resistance of samples of principal failures are mentioned, for which the safe life of wing and aircraft structural components are discussed A method of obtaining tail surface were determined In conclusion there are recommenda- a high experimental noise level by means of a modulated air jet is tions concerning operation and maintenance as well as important discussed The use of a wideband siren for modulating the jet is structural design experience resulting from the analysis and fatigue described P T H tests (Author)

A78-30506 * Remotely piloted aircraft in the civil environment T J Gregory, W P Nlelms (NASA, Ames Research A78-30355 ff Methods of reducing aircraft noise (Metody Center, Moffett Field, Calif I, and J S Karmarkar (Systems Control, snizovani hluku letadel) J Hofr Zpravodaj VZLU, no 5, 1977, p Inc. Palo Alto, Calif) Mechanism and Machine Theory, vol 12, no 263-270 6 refs In Czech 5, 1977, p 471-479 9 refs The problem of reducing internal aircraft noise is considered Improved remotely piloted aircraft (RPAs), i e , incorporating The dependence of the cabin noise on the general layout of the reductions in size, weight, and cost, are becoming available for

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civilian applications Existing RPA programs are described and A78-30679 # Runway roughness characterization by DOS predicted into the future Attention is given to the NASA Mim- approach F Nassirpour, S G Kapoor, and S M Wu (Wisconsin, Sniffer, which will fly to altitudes of more than 20,000 m, sample University, Madison, Wis ) ASCE, Transportation Engineering Jour- the atmosphere behind supersonic cruise aircraft, and telemeter the nal, vol 104, Mar 1978, p 213-226 13 refs data to ground stations Design and operating parameters of the The proposed dynamic data system for runway roughness aircraft are given, especially the optical sensing systems, and civilian characterization involves the development of a mathematical model RPA uses are outlined, including airborne research, remote mapping, in the form of a stochastic differential equation for runway profile rescue, message relay, and transportation of need materials Civil heights, computation of the geometric statistical properties of regulatory factors are also dealt with D M W runway profiles from parameters of the model, and application to the characterization of runway roughness at four major airports A preliminary evaluation of this approach to characterizing runway A78-30572 ff Effect of boundary layer suction through slits unevenness is presented along with a critical review of power on the efficiency of turfaomachme outlet diffusors (Vlnanie shche- spectrum analysis of runway roughness The dynamic data system levogo otsosa pogranichnogo sloia na effektivnost' vykhodnykh and some applications are described, and results involving depth diffuzorov turbomashm) A A Basovskaia and A P Stepanenko measures, stochastic models, correlation, and the spectrum are (Akademna Nauk Ukramskoi SSR, Institut Mekhamcheskoi Teplo- reported M L fiziki, Kiev, Ukrainian SSR) Energetika, vol 21, Jan 1978, p 134-137 6refs In Russian The influence of slit arrangement and suction intensity on losses A78-30689 II Tunnel interference assessment by boundary in short conical and annular curvilinear diffusors were studied measurements C F Lo (ARO, Inc, Arnold Air Force Station, experimentally at inlet section Mach numbers of 02 to 04 and Tenn ) AIAA Journal, vol 16, Apr 1978, p 411-413 5 refs Reynolds numbers of 450,000-900,000 It is shown that suction An approach is proposed which avoids the difficulties en- reduces losses effectively only in very short diffusors with angles and countered in the classical method of assessing and correcting wind expansion ratios significantly larger than optimum By application of tunnel interference This approach requires only the measurement of suction, it is possible to increase turbine efficiency It is shown that a flow variables at a control surface near the tunnel wall inside the test diffusor with an L/D ratio of 0 54 and a diffusor with a relative section A two-dimensional example is chosen to illustrate the length of 0 8, without suction have identical loss coefficients M L formulation of the computation procedure The Fourier transform technique is applied to the subsonic flow case for obtaining the interference flowfield and the flow variables under free-air conditions at the control surface To validate the approach, a numerical demonstration is performed by simulating the flow in a wind tunnel A78-30677 # Tandem-queue algorithm for airport user with the mviscid transonic small-disturbance equation The approach flows W J Dunlay, Jr (Pennsylvania, University, Philadelphia, Pa ) is also verified experimentally for a two-dimensional 15 24-cm-chord and C -H Park (Seoul National University, Seoul, South Korea) airfoil, the tunnel test section configuration consisting of variable ASCE, Transportation Engineering Journal, vol 104, Mar 1978, p perforated walls for the top and bottom walls and solid plexiglass 131 149 14 refs US Department of Transportation Contract No sidewalk S D OS-50232 The paper presents an analytical framework for uniting successive queueing models of airport components into a modular airport A78-30690 * ft Influence of spin rate on side force of an system model The objective is to represent the arrival rate at one set axisymmetnc body R L Kruse (NASA, Ames Research Center, of components as a function of the arrival rates and operating Moffett Field, Calif) AIAA Journal, vol 16, Apr 1978, p 415, characteristics of the preceding set of components An algorithm is 416 presented which applies to sets of successive components that are Results are presented for an experimental study in which a used by nearly all passengers, it is assumed that all passengers go 10-deg half-angle pointed cone model 579 cm long and made of directly from one of these sets to the next without making magnesium (for lightness and minimization of inertia! effects) is spun intermediate stops In a continuation of the analysis, detailed at several rates about its axis of symmetry The model is spun in both consideration is given to the effects of optional or ancillary activities directions, but most of the data presented are for the counter- that exist between certain sets of components on the flow of clockwise rotation The resulting side force is recorded on an passengers through subsequent airport processing components One oscillograph It is shown that the side force observed occurs under of the conclusions is that queueing models of successive sets of conditions of spin about the longitudinal axis, and that the general components within an airport can be related using transfer times, shape of the side-force curve with roll position does not depend time-dependent delays, and flow-split (and directional split) per- strongly on spin rate However, the peak-to-peak value of side force centages M L decreases substantially with spin rate, suggesting that the vortices producing the side force require a significant amount of time to A78-30678 # Airport/community environmental planning change position and/or strength S D S C Orlick (California Polytechnic State University, San Luis Obispo, Calif ) (American Society of Civil Engineers, Conference on Airport Planning, University of Washington, Seattle, Wash , Feb 3-5, A78-30697 # The division of air transport markets between 1977) ASCE, Transportation Engineering Journal, vol 104, Mar carriers-Local service operations E R D Andersen and W I Bobye 1978, p 187-199 26 refs (Pacific Western Airlines, Ltd, Vancouver, Canada) (Canadian The paper is concerned with the nature of recent airport Aeronautics and Space Institute, General Meeting, Toronto, Canada, environmental planning practices, the inherent shortcomings of these May 11, 1976 ) Canadian Aeronautics and Space Journal, vol 24, practices, and the type of changes that will bring about desired Jan-Feb 1978, p 17-31 9 refs improvements The tendency of project sponsors to use environ- Government regulations and economic constraints on Canadian mental impact statements more as an aid to decision making than as local-service air carriers are discussed Among the economic con- a means of informing the public is considered A composite model of straints considered are aircraft productivity, operating costs and recent airport environmental planning practice, which is based on an passengers' acceptance of turboprop craft, multi-stop service and eight-step model of rational planning, is examined with attention to long traveling times Subcontracting of thin routes to carriers owning methodological deficiencies, input weaknesses, and structural weak aircraft with small seating capacities may provide a local-service nesses Planning processes are discussed which would replace the carrier with an alternative to flying these routes at low capacity with concept of airport environmental planning with the concept of larger aircraft The future Canadian demand for 50-seat turboprop community environmental planning for airports M L and 100-seat jet aircraft is assessed J M B

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A78-30698 ft Aviation fuel usage - Economy and conserva- A78-30891 Vanational principles for the transonic airfoil tion V F J Craig and B G Smith (Roads and Transportation problem G F Carey (Texas, University, Austin, Tex ) Comouter Association of Canada, Annual Conference, 8th, Quebec City, Methods in Applied Mechanics and Engineering, vol 13, Feb 1978, Canada, Sept 13. 19761 Canadian Aeronautics and Space Journal, p 129-140 11 refs vol 24, Jan-Feb 1978, p 34-49 The transonic airfoil problem is formulated, and associated Methods of conserving aircraft fuel are discussed, the emphasis is vanational principles are constructed Both the full potential form of on short-term operational and procedural measures Reduction of the governing equations and small disturbance theory are considered required fuel reserves for flights operating under excellent weather Vanational functionals are developed for the full potential equation conditions, minimization of let-powered taxiing maneuvers, better using a modified Plateau integral and also directly from the sequencing of takeoffs at peak hours, and the selection or ap- continuity equation A simpler nonlinear functional is obtained for propriate airspeed, altitude, climb, cruise and descent options are the small disturbance approximation by direct divergence manipula- cited as means to limit unnecessary fuel consumption In addition, tions to a weak solution form of the Galerkin requirement For the use of turboprop aircraft on short-haul sectors and more rational slightly supercritical flows, iterative methods and Mach number air routings and terminal area control are suggested to decrease fuel perturbation techniques lead to simpler but less general vanational waste J M B principles Appropriate finite element formulations are developed using the principles (Author) A78-30850 ,? The wind and turbulence measuring system of the MAE Airborne V/STOL Simulator M Sinclair and W S Hmdson A78-31019 * On sound transmission into a heavily-damped (National Aeronautical Establishment, Flight Research Laboratory, cylinder L R Koval (Missoun-Rolla, University, Rolla, Mo ) Ottawa, Canada) Canada, National Research Council, Division of Journal of Sound and Vibration, vol 57, Mar 8, 1978, p 155, 156 Mechanical Engineering and National Aeronautical Establishment, Grant No NsG-1050 Quarterly Bulletin, no 4, 1977, p 27 29, 31-40 A mathematical model for the transmission of sound into a thin An airborne V/STOL simulator has been used to record monocoque cylindrical shell is discussed The model is used to characteristics of disturbances in the boundary layer of the earth evaluate an oblique plane wave incident upon a flexible thin Real-time wind and turbulence calculations are made both directly cylindrical shell The solution is applicable to the transmission of from a Ooppler radar and indirectly through integration of the sound under actual flight conditions The model is then used to accelerations derived from an accelerometer/gyroscope package, the determine curves of cylinder-transmission loss for heavily damped final mertial velocity computation relies on a mixing of the cylinders Numerical results are found for several plane wave in- redundant estimates in a third-order complementary filter system cidence angles for a narrow-bodied jet fuselage made of aluminum It Time histories of computed wind components and of a shear is noted that damping (i e , the loss factor) increases, dips because of encounter are presented J M B reduced cylinder resonances, and eventually disappears when the loss factor of the shell is large enough S C S

A78-30856 Alloy heeds and design - The airframe R F A78-31034 Sensitivity reduction in aircraft control sys- Simenz (Lockheed California Co, Science and Engineering Div, tems N Sundararajan (Indian Space Research Organization, Vikram Burbank, Calif) and M A Steinberg (Lockheed Aircraft Corp, Sarabhai Space Centre. Trivandrum, India) IEEE Transactions on Burbank, Calif ) In Fundamental aspects of structural alloy design Aerospace and Electronic Systems, vol AES-14, Mar 1978, p New York, Plenum Press, 1977, p 229-254, 292-297 5 refs Discussion, p 254-256 8 refs A method for reducing trajectory sensitivity to parameter Clad aluminum surfaces and exfoliation-resistant alloys selected perturbations for linear feedback systems is described Application of for the airframes of wide-body aircraft are discussed, and develop- the method to the design of aircraft control systems, with special ments in titanium- and aluminum-alloy designs for advanced aircraft reference to a helicopter forward flight control system, is illustrated are reviewed In aluminum alloy design, the emphasis is placed on the The response of the system based on this method is found to be attainment of superior fatigue and strength properties in conjunction better than that obtained with fixed-feedback gam controllers, with immunity to stress-corrosion cracking Achievement of lower although the response may not be as good as that of an adaptive cost titanium alloys with more reliable fatigue and toughness control scheme The mam advantage of the method is the simplicity properties is a principal aim for airframe development programs In of its implementation relative to that of the adaptive control scheme addition, fail-safe and damage-tolerant structures are important which requires an on-board computer (Author) requirements in advanced airframe design J M B

A78-31038 Radio interference in helicopter-borne pulse Doppler radars M K Moavem (Pahlavi University, Shiraz, Iran) IEEE Transactions on Aerospace and Electronic Systems, vol A78-30886 Space optical communications with the AES-14, Mar 1978, p 319-328 7 refs IMd YAG laser M Ross, J Abernathy, J Wolf (McDonnell Douglas Radio interference generated in a helicopter-borne pulse Astronautics Co , St Louis, Mo I, P Freedman, G Matassov, and J Doppler radar system due to rotating blades is analyzed for the case D Barry (USAF, Space and Missiles System Organization, Los that blades are located in the far field region of the radar antenna A Angeles, Calif) IEEE, Proceedings, vol 66, Mar 1978, p 319-344 first-order estimate of the blade interference power spectrum is 38 refs obtained as a function of antenna depression angle and radar The development of a Nd YAG space laser communication (helicopter) altitude and speed Numerical calculations show that system is discussed with respect to history, potential applications, blade interference is very weak compared with the direct ground and present status The basic design of an Air Force Space clutter It extends, however, into the clutter-free region which causes Communications Flight Test operable at a data rate of 1000 Mbit/s is false alarms and degrades the radar performance (Author) described at both the system and component level An engineering feasibility model of this system has been completed, and the results A78-31050 Flight tests of digital data transmission J R of tests data are reported Communications at 1000 Mbit/s with a Juroshek, G E Wasson, and G H Stonehocker (NOAA, Institute for receiver sensitivity of 20 photoelectrons/bit was demonstrated for a Telecommunication Sciences, Boulder, Colo ) IEEE Transactions on bit error rate of 10 to the 6, mtertermmal tracking with angle errors Aerospace and Electronic Systems, vol AES-14, Mar 1978. p less than 1 microrad, and station to station acquisition in less than 6 403-410. 8 refs Research supported by the US Department of s A simulated range of 40,000 km was used (Author) Transportation and FAA

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A series of flights were made to measure the characteristics of Canada, October 3, 4, 1977, Proceedings air-to-ground digital transmission in the VHP aeronautical mobile Ottawa, Canadian Aeronautics and Space Institute, 1978, p 1-1 to frequency band Digital transmission rates of 2400 and 4800 bit/s 1-32 were used with minimum shift keying (MSK) as the baseband The objective of the NASA Aircraft Energy Efficiency Program modulation format Signal level, signal fading, and radio horizon is to accelerate the development of advanced technology for more characteristics are described Bit error rates and the causes of the energy-efficient subsonic transport aircraft This program will have errors also are discussed (Author) application to current transport derivatives in the early 1980s and to all-new aircraft of the late 1980s and early 1990s Six major A78-31126 Some specific hydrodynamic and aerodynamic technology projects were defined that could result in fuel savings in problems of surface-effect ships with sidewalls (Quelques problemes commercial aircraft (1) Engine Component Improvement, (2) d'hydro-aerodynamique speafiques des NES/AQL) R J Balquet Energy Efficient Engine, (3) Advanced Turboprops, (4) Energy and F Jodelet (Service Technique des Constructions et d'Armes Efficiency Transport (aerodynamically speaking), (5) Laminar Flow Navales, Division Navires Speciaux, Paris, France) Association Control, and (6) Composite Primary Structures B J Technique Maritime et Aeronautique, -Bulletin, no 77, 1977, p 415-429, Discussion, p 430-432 In French A78-31303 # Prospects for energy conserving STOL trans- Interrelated hydrodynamic and aerodynamic problems asso- ports using prop-fans B Eggleston (de Havilland Aircraft of Canada, ciated with the development of surface effect ships, which ride on an Ltd , Downsview, Ontario, Canada) In Canadian Symposium on air cushion, are discussed Topics considered include the partitioning Energy Conserving Transport Aircraft, Ottawa, Canada, October 3, 4, of and the required pressure for the air cushion, the behavior of the 1977, Proceedings Ottawa, Canadian Aero- air cushion over oil, the significance of sidewall dimensions, and nautics and Space Institute, 1978, p 2-1 to 2-16 8 refs problems associated with support, water exclusion, and propulsion A study has examined the application of the prop-fan type of The importance of the length/breadth ratio parameter is indicated advanced propeller design to a 1986 technology, 50 passenger STOL M L transport aircraft cruising at Mach numbers of 0 50, 0 60 and 0 70 Comparisons were made with an equivalent 1977 technology STOL transport (cruising at Mach 038) sized to meet the same design A78-31127 Mixed ventilated foils (Ailes ventilees mixtes) requirements In a 1986 technology aircraft the greatest fuel savings M Pouillot (Societe Nationale Industrielle Aerospatiale, Division were found at Mach 0 50 and maximum energy efficiencies of 98 Helicopteres, Mangnane, Bouches-du-Rhone, France) Association passenger miles per Imperial gallon were predicted At short ranges Technique Maritime et Aeronautique, Bulletin, no 77, 1977, p the direct operating costs of the 1986 technology aircraft at Mach 433-455, Discussion, p 456-460 15refs In French 0 50 and 0 60 were found to be very similar to the 1977 technology The paper surveys several approaches to analyzing mixed STOL transports The energy efficiencies of a prop-fan aircraft ventilated foils considered with reference to hydrofoils The term designed for Mach 070 were found superior to 1977 technology 'mixed' indicates an immersed foil design which can be adapted to STOL and jet CTOL aircraft by 10-20% B J several modes of operation Classic hydrodynamic profiles and mixed profiles are compared, indirect and direct problems are examined, A78-31304 * if Some aspects of powerplant airframe integra- and experimental investigations of two-dimensional models along tion affecting fuel conservation J E Far bridge (de Havilland with qualitative studies of three-dimensional assemblages are re- Aircraft of Canada, Ltd , Downsview, Ontario, Canada) In Canadian ported Direct problems include two-dimensional flow with and Symposium on Energy Conserving Transport Aircraft, Ottawa, without a free surface and three-dimensional flows M L Canada, October 3, 4, 1977, Proceedings Ottawa, Canadian Aeronautics and Space Institute, 1978, p 3-1 to 3-15 12 refs Research sponsored by the Department of National A78-31152 Supersonic transports H A Goldsmith Defence of Canada and NASA (British Aircraft Corp, Bristol, England) In Advancing tech- The performance criteria for STOL transport aircraft place many constraints on engineering design, which, in turn, may have a nologies London, Mechanical Engineering Publi- direct bearing on fuel efficiency these constraints become even more cations, Ltd , 1977, p 10-24 severe with the introduction of powered-lift for turbofan aircraft Techniques for minimizing the drag of supersonic transport Consideration is given to some aspects of performance and design aircraft are considered, and the rationale leading to adoption of a which arise as a result of powerplant/airframe integration and an maximum speed of about Mach 2 3 for first-generation slender wing supersonic transports is discussed The efficiency of the supersonic attempt is made to assess these factors in terms of transport fuel transport craft may be limited by the convergence of inlet air efficiency The drag polars of various powered lift concepts are momentum and gross thrust with increasing Mach number The analyzed to determine the installed thrust/weight required and a kinetic heating which determines a great deal of supersonic transport simple method of relating this to fuel efficiency is suggested Some structural design also receives attention J M B other factors have been identified as being important to this aspect of design and these are discussed in more general terms Finally, special consideration is given to recent Canadian research in the A78-31153 The aircraft ducted fan R M Denning (Rolls realm of supercritical airfoil technology as applied to an multi-foil Royce, Ltd , Bristol Engine Div , Bristol, England) In Advancing section which could be utilized both for the STOL regime of flight technologies London, Mechanical Engineering and for cruise at transonic speeds (Author) Publications, Ltd , 1977, p 25-40 Aircraft turbofan design is discussed, with attention given to A78-31305 « Improved energy efficiency for small CTOL efficiency, noise characteristics, pressure ratios, and the effects of transport aircraft S Bernstein, G A Adams, and A Oberti flight speed Two- and three-shaft fan engines are described, engine (Canadair, Ltd, Montreal, Canada) In Canadian Symposium on design improvements such as the increase of peak gas temperatures Energy Conserving Transport Aircraft, Ottawa, Canada, October 3, 4, and the development of air-cooled turbine blades are mentioned The 1977, Proceedings Ottawa, Canadian Aero- noise emission from high bypass ratio engines is also assessed In nautics and Space Institute, 1978, p 4-1 to4-14 addition, variations in specific fuel consumption with flight speed An exploratory investigation was carried out into potential receive consideration J M 8 improvements in fuel efficiency and direct operating costs (DOC) by the application of new airframe and propulsion system technologies (supercritical wings, advanced composite materials, high aspect ratio A78-31302 * # The NASA Aircraft Energy Efficiency Pro- wings, advanced propulsion systems, wing tip winglets, active gram J M Klmeberg (NASA, Washington, DC) In Canadian controls and laminar flow) to the smaller CTOL transport aircraft Symposium on Energy Conserving Transport Aircraft, Ottawa, Fuel savings of up to 12% are possible by increasing aspect ratio

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alone Incorporation of supercritical airfoils and advanced com- engines of the type used for executive and commuter aircraft, i e , posites with the higher aspect ratios can save a further 5% Advanced turboprops up to 2500 SHP and turbofans up to 6000 Ib thrust propulsion system technology offers similar or higher potentials for Using projections of technology improvements, equivalent 1987 fuel savings - 15-20% with new turbofans and a further 15-20% with production engines were synthesized, this showed that a 15-19% prop-fans Total cumulative fuel savings of 40-45% are possible with reduction in cruise specific fuel consumption could be expected for incorporation of all the new technologies investigated Equivalent this class of engine over the next 10 years Two pairs of aircraft were DOC improvements are of the order of 15-18% and these increase to designed - turboprop and turbofan powered using 1977 and 1987 20-22% as the fuel cost increases from 40 to 70 cents per gallon B J engines but constant 1977 airframe technology Reduction in specific fuel consumption and specific weight results in reduction in A78-31306 * # Fuel saving potential of Mach 0 8 twin engine aircraft weight for the same mission with further reduction in fuel prop-fan transports F J Davenport (Boeing Commercial Airplane flow, from 17% for the larger turbofan engine to 21% for the larger Co , Seattle, Wash ) In Canadian Symposium on Energy Conserving turboprop B J Transport Aircraft, Ottawa, Canada, October 3, 4, 1977, Proceed- ings Ottawa, Canadian Aeronautics and Space A78-31310 ft Energy conserving aircraft from the engine Institute, 1978, p 5-1 to 5-19 Contract No NAS29104 viewpoint R M Denning (Rolls-Royce, Ltd , Aero Div , Bristol, The fuel saving and economic potentials of the prop-fan England) In Canadian Symposium on Energy Conserving Transport high-speed propeller concept have been evaluated for twin-engine Aircraft, Ottawa, Canada, October 3, 4, 1977, Proceedings commercial transport airplanes designed for 33336 km range, 180 Ottawa, Canadian Aeronautics and Space Institute, passengers, and Mach 0 8 cruise A fuel saving of 9 7% at the design 1978, p 9-1 to 935 5 refs range was estimated for a prop-fan aircraft having wing-mounted The paper is mainly concerned with fuel-efficiency improvement engines, while a 58% saving was estimated for a design having the in conventional gas turbine propulsion systems for airline operation, engines mounted on the aft body The fuel savings and cost were a broad philosophy of engine improvements for short, medium and found to be sensitive to the propeller noise level and to aerodynamic long-haul aircraft is reviewed It is stressed that minimizing all drag effects due to wing-slipstream interaction Uncertainties in these aircraft direct operating costs is the ultimate yardstick for the engine effects could change the fuel savings as much as plus or minus 50% designer Higher fuel prices may change priorities in engine design A modest improvement in direct operating cost was estimated for the and justify more complex and expensive engines particularly for wing-mounted prop-fan at current fuel prices (Author) longer-range operations Optimum engine design for shorter range can be significantly different because of the implication of cyclic life on air-cooled turbine blades Lower-specific-thrust engines are A78-31307 /f Fuel efficiency - Where we are heading in the worthy of close consideration particularly for short-haul operation design of future jet transports R H Hopps (Lockheed-California BJ Co, Burbank, Calif) In Canadian Symposium on Energy Con- serving Transport Aircraft, Ottawa, Canada, October 3, 4, 1977, A78-31311 # Thrust computing system applications to in- Proceedings Ottawa, Canadian Aeronautics and crease engine life and provide fuel conservation G B Mackintosh Space Institute, 1978, p 6-1 to 6-16 (Computing Devices Co , Ottawa, Canada) In Canadian Symposium Consideration is given to the 1980s jet-transport market with on Energy Conserving Transport Aircraft, Ottawa, Canada, October emphasis on narrow-body vs wide body aircraft, the benefits of 3, 4, 1977, Proceedings Ottawa, Canadian increased size and capacity and the feasibility of superlarge aircraft Aeronautics and Space Institute, 1978, p 10-1 to 10-20 Research Technology of the 1980s relating to span, active controls and supported by the Canadian/United States Defense Production composites is briefly reviewed Three potential technologies for the Sharing Program 1990s are discussed laminar flow control, advanced turboprops and The paper describes a method of computing the gross thrust liquid hydrogen It is noted that the technology of the 1980s will not required by a jet engine based only on measurements of pressure in offer dramatic improvements over all the aircraft flown today, large 1tie engine tailpipe and of ambient static pressure It is shown how improvements can be offered only in comparison with the older this technique can be applied to improve the overall efficiency of narrow body aircraft B J engine operation, the result of this improvement is that the number of engines operating at abnormally high exhaust gas temperatures can be reduced In addition to the fuel saving achieved, very great A78-31308 # Aviation fuels - A supplier's perspective C B reductions in hot-section parts consumption and maintenance re- Rupar (Imperial Oil Enterprises, Ltd, Sarnia, Ontario, Canada) In quirements can result from even a small decrease in operating Canadian Symposium on Energy Conserving Transport Aircraft, temperature The performance of the thrust computation procedure Ottawa, Canada, October 3, 4, 1977, Proceedings is substantiated by data obtained on military aircraft engines under Ottawa, Canadian Aeronautics and Space Institute, USAF and Canadian Government contracts B J 1978, p 7-1 to 7-8 Current availability of aviation kerosene is limited by the freeze A78-31312 If STOL system fuel savings-Ground and air A point, flash point and aromatics content In the future these F. Toplis and J H Nazareth (de Havilland Aircraft of Canada, Ltd , constraints will become more critical as increasing volumes of Downsview, Ontario, Canada) In Canadian Symposium on Energy synthetic liquids are produced to supplement natural petroleum Conserving Transport Aircraft, Ottawa, Canada, October 3, 4, 1977, Ideally, to maximize security of supply and to control cost, the next Proceedings Ottawa, Canadian Aeronautics and generation of aircraft should be designed to operate safely and Space Institute, 1978, p 11-1 to 11-16 14 refs efficiently on fuels with a wider range of properties (Author) It is maintained that, for intercity travel, a STOL system with STOLports located near the major downtown passenger traffic zones A78-31309 # Aircraft fuel economy - The propulsion system can provide substantial savings in the fuel required for access and contribution R A Harvey, R E Morns, and B J Palfreeman (Pratt egress from the air terminal as compared to a CTOL system A model and Whitney Aircraft of Canada, Ltd, Longueuil, Canada) In for estimating the passenger traffic diverted to STOL from the CTOL Canadian Symposium on Energy Conserving Transport Aircraft, short haul system is described, the associated fuel savings and Ottawa, Canada, October 3, 4, 1977, Proceedings profitability of a STOL system are calculated For example, a STOL Ottawa, Canadian Aeronautics and Space Institute, system centered on the Toronto Island Airport using Dash 7 aircraft 1978, P 8-1 to 8-20 would prove more convenient than CTOL to some 1 5 million air Results are presented of some engine performance and design travelers in 1980 Also the STOL system would save close to 5 studies intended to determine the potential improvements in fuel million gallons of fuel as compared with a purely CTOL system and efficiency that can be made over a 10 year period by advances in could operate with a profit margin of some 30 million dollars in the engine technology The study is confined to 'small' gas turbine same year The STOL system would still save fuel when advanced.

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more fuel-efficient CTOL and STOL aircraft are presumably in internal anti-jamming system (ASPJ or airborne self protection operation in 1986 B J jammer) on the aircraft of both services into the 1990s The ASPJ, developed by the Navy, can operate in both lethal and non-lethal A78-31313 # The energy costs of some noise abatement modes, i e, flack suppression, anti-radiation missiles, precision procedures R K Leong (Transport Canada, Ottawa, Canada) In emitter locating systems, and support jamming and onboard Canadian Symposium on Energy Conserving Transport Aircraft, defensive ECM Program management and engineering objectives are Ottawa, Canada, October 3, 4, 1977, Proceedings outlined, with emphasis on design competition, risk reduction, high Ottawa, Canadian Aeronautics and Space Institute, initial production rate, and sustained production competition 1978, p 13-1 to 13-17 Attention is given to the installation of the ASPJ on currently The fuel consumption and noise reduction benefits of two noise operational aircraft, especially the F-14 and F-18 prototype DMW abatement departures are compared with a standard non noise abatement departure The analysis consists of determining the fuel A78-31733 Acoustic emission detection of fatigue crack consumed in each segment defined by changes in airplane configura- growth in a production-size aircraft wing test article under simulated tion, engine thrust or speed Results show that extra fuel is flight loads W M Pless, C D Bailey, and J M Hamilton consumed in each of the noise abatement departure procedures, the (Lockheed Georgia Co, Marietta, Ga ) (American Society for magnitude of the fuel penalty is aircraft dependent The weight of Nondestructive Testing, Spring Conference, Phoenix, Ariz, Mar the aircraft at takeoff is found to affect the amount of fuel 28-30, 1977) Materials Evaluation, vol 36, Apr 1978, p 41-48 10 consumed considerably in the case of the Boeing 747 (Author) refs Contracts No F33615-75-C 5249, No F33657-15053 AF Project 7531, AF Order P00972 A structural article representative of a large full-production A78-31314 # Air traffic control and energy conservation in military aircraft wing was subjected to flight by flight load spectra to air operations H R Merntt (Transport Canada, Ottawa, Canada) initiate and propagate fatigue cracks in 17 selected fastener holes in In Canadian Symposium on Energy Conserving Transport Aircraft, eight test areas One-hundred unit flights were applied to the wing to Ottawa, Canada, October 3, 4, 1977, Proceedings initiate crack growth at sharp notch sawcuts and existing cracks, Ottawa, Canadian Aeronautics and Space Institute, followed by 2,000 unit flights to propagate the cracks Seven test 1978, p 14-1 to 14-8 areas were monitored for acoustic emission (AE) using a 32 channel The Canadian ATC system is discussed in the framework of AE flaw locator system and triangulated sensor arrays AE was energy conservation in air transportation Such ATC activities as the detected from 12 of the 15 test holes monitored which experienced Joint Enroute Terminal System, the Integrated Communications crack growth After the tests, the test holes were removed from the Control System, MLS, The Vortex Avoidance System, area naviga- structure for fractographic analysis of crack growth Correlations tion, and airspace planning are examined It is concluded that good between AE and crack growth for several of the test holes are planning for the provision of energy conservation in future ATC discussed Experimental positioning of sensor arrays to determine services is to maintain a dynamic concept of user-demand change and possible airborne AE system configurations are discussed (Author) to produce, on a timely basis, those changes in operational capability which will best match system capacity with demands B J A78-31745 Going for a spin - Fighter style BRA Burns A78-31425 Fire power D Richardson Flight Inter- (British Aerospace Aircraft Group, Warton, Lanes, England) Flight national, vol 113, Apr 1,1978, p 921-926 International, vol 113, Apr 8, 1978, p 985-989 Airborne radar systems for western nations (USA, UK, France, Combat experience in Vietnam and Korea has underscored the Sweden, Israel), and for the USSR and China are reviewed in light of necessity for effective aircraft performance in air-to air combat recent developments in avionics A table of comparison is presented Causes of spin encountered during high angles of attack and rapid which outlines the available data relating to the performance lateral movement are analyzed with reference to aerodynamic design characteristics of the radar systems discussed, e g , China, Scan Can, parameters It is noted that rudder modifications can be effective in France, Cyrano, Aida, and Mirage 2000, Israel, EL/M-2001 B and reducing spin, especially within the framework of an aileron-rudder EL/M-2021, USSR. Skip Scan, Jaybird, High Lark, and Fox Fire, interconnect Also mentioned are the possibilities of forebody strake Sweden, SS-37 A and PS-46 A, UK, Tornado ADV and Blue Fox, addition and artificial stability control augmentation to con- and USA, AN/APQ, AN/APG, AN/AWG, and F-16 D M W ventionally designed aircraft in order to provide spin resistance throughout the entire flight envelope DMW A78-31582 # Special problems in the determination of the radiation characteristics of antennas on aircraft and satellites with A78-31755 ft Mirage 2000 (Mirage 2000) J Monsset Airet the aid of geometric diffraction theory (Spezielle Probleme bei der Cosmos, vol 16, Apr 1,1978, p 23-28 In French Bestimmung der Strahtungscharakteristik von Antennen auf Flug- Design characteristics of the Mirage 2000 air superiority fighter zeugen und Satelliten mit Hilfe der geometrischen Beugungstheone) are discussed with attention to the boron- and carbon-composite A Schrott and V Stem (Deutsche Forschungs- und Versuchsanstalt materials used in its construction, and in comparison with the Mirage fur Luft- und Raumfahrt, Institut fur Flugfunk and Mikrowellen, III and Mirage F-1 It is noted that the Mirage 2000 has a larger Oberpfaffenhofen, West Germany) fArbeitsgememschaft lono- surface area than the other Mirages, comparable to that of the F-15, sphare, URSI, and Nachnchtentechnische Gesellschaft, Gememsame and that its aerodynamics permit good overall stability, especially at Tagung, Klemheubach, West Germany, Sept 26-Oct 7, 1977) large angles of attack The construction and operation of the landing Klemheubacher Benchte, vol 21, 1978, p 41-50 8 refs In German gear are also outlined, with reference to its resistance to stress Also The methods of geometric diffraction theory are applied to the dealt with is the history of the development of the SNECMA M53 calculation of the radiating properties of high-frequency antennas of engine, and avionics for navigation, weapons systems, and aero- aircraft or satellites, where reflections from individual surfaces of the dynamic stability DMW aircraft or satellite contribute to the radiation field The paper describes the geometric diffraction computation of the diffracted A78-31811 # The effect of a parachute on the motion of an field for special cases such as (1) sudden change of the incident field, ax (symmetric object dropped from an aircraft (Wplyw spadochronu (2) the transition zone for convex bodies, and (3) caustics. P T H na ruch zasobnika osiowo symetrycznego zrzucanego z samolotu) J Marymak, K Michalewicz, and Z Wmczura (Warszawa, Politechnika, A78-31700 The next generation EW system - ASPJ C Wojskowa Akademia Techmczna, Warsaw, Poland) Mechanika Teo- Rodgers Military Electronics/Countermeasures, vol 4, Mar 1978, p retyczna i Stosowana, vol 16, no 1, 1978, p 57-70 28 refs In 34, 36, 42(3 ff) Polish Electronic warfare (EW) requirements of the Air Force and The paper analyzes the dynamic characteristics of an air- Navy have been sufficiently reconciled to permit the use of a single dropped free-falling axisymmetnc vehicle with drag chute and

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accelerating rocket engine The vehicle is considered a rigid body A78-31915" tt Differential altimetry for satellite orbit with five degrees of freedom, its motion is described by a system of determination H Hagar, Jr and D H Boggs (California Institute of nonlinear differential equations, which are integrated numerically. Technology, Jet Propulsion Laboratory, Pasadena, Calif) American Flight paths, changes in the angles of elevation, azimuth, attack and Astronaut/cat Society and American Institute of Aeronautics and sideslip are calculated as well as changes m center of mass for Astronautics, Astrodynamics Specialist Conference. Jackson Hole, different air-drop parameters Aerodynamic characteristics were Wyo, Sept 7-9. 1977, Paper 31 p 8 refs Contract No NAS7-100 obtained from wind tunnel tests B J Differential altimetry is concerned with the employment of differenced satellite altimeter measurements at orbit ground trace intersections The employment of this procedure makes it possible to A78-31836 # Some measurements in two-dimensional turbu- eliminate two of the major error sources found in direct altimetry lent wakes K W Eventt (Warwick, University, Coventry, England) Previous applications have not included the appropriate dynamic Aeronautical Quarterly. vol 29, Feb 1978, p-28-32 7 refs constraints required to account for correlations due to satellite orbit An investigation is made of the wakes behind four different motion A description is given of an investigation in which these two-dimensional bodies circular, square, aerofoil and reversed correlations are included The methodology produced is consistent aerofoil cylinders The lasting influence of the upstream history of with the dynamic environment The regional or local limitations of the flow development is particularly noted The production time previous approaches are overcome by extending the technique to the scale is a significant fraction of the time scale for mean flow global scale Attention is given to the description of the data type, development, this fraction increases with downstream distance As the geometric topography height, altimeter errors, discretization the flow develops, the advection term in the equation for turbulent errors, an approximate orbit determination problem, and a com- energy transfer increases S C S parison of differenced altimeter measurements for retrograde and prograde orbits G R A78-31838 // On the calculation of the incompressible flow past an aerofoil with a jet flap R O'Mahoney and F T Smith (Imperial College of Science and Technology, London, England) A78-31942 # Use of and experience with simulation in the Aeronautical Quarterly, vol 29, Feb 1978, p 44-59 20 refs. development of the VFM 614 and the VAK 191 (Emsatz und Research supported by the Science Research Council Erfahrungen der Simulation bei der Entwicklung der VFW 614 und The incompressible planar flow past a wing with a jet issuing der VAK 191) D Dey and K-H Unterremer (Veremigte Flugtechm- from the trailing edge is calculated by two separate methods, both sche Werke-Fokker GmbH, Bremen, West Germany) Deutsche adaptations of conformal mapping routines that are numerically Gesellschaft fur Luft- und Raumfahrt, Symposium uber Entwick- exact in the jet-free case These are the well-known circle mapping lungssimulation, Cologne, West Germany, Dec 5, 6, 1977, Paper method and the half-plane method The former is rendered inexact 77-083 39 p 5 refs In German by the jump conditions across the jet and an approximation is In the present paper, such aspects of simulation as its organiza- necessary The half-plane method, however, remains exact in tion, application, cost effectiveness, and the successes and achive- principle, and a range of results is presented The most accurate of ments are discussed in an attempt to put simulation in proper the previous calculations is verified, and comparisons between the perspective and thereby narrow the gap between the advocates of half-plane and circle methods are also made. The half-plane scheme simulation and the corporate management that has to pay for it The seems well suited for such wake-controlled flows and has been topics discussed are illustrated by the results obtained with simula- extended to transonic conditions in a related study (Author) tion in the development of aircraft V P

A78-31868 Sweden's latest- and last J Thmesen Airports A78-31943 it Simulation in the development of the training International, Feb-Mar 1978, p 8-11 and ground-attack aircraft Alpha Jet (Simulation bei der Entwick- A new airport Landvetter, for Gothenburg, Sweden, is described lung des Schul- und Erdkampfflugzeugs Alpha Jet) H Friednch with reference to its design and capacity, both for passengers and for (Dormer GmbH, Friednchshafen, West Germany) Deutsche Gesell- aircraft A passenger capacity of around 2 million per year (evenly schaft fur Luft- und Raumfahrt, Symposium uber Entwicklungssimu- divided between domestic and international) is available now, with lation, Cologne, West Germany, Dec 5, 6, 1977, Paper 32 p In growth to 3 million in 1985 and 6 million in 2000 foreseen The German airport's runway and ATC system are able to handle all types of The role of ground simulators in formulating the design criteria commercial passenger and freight aircraft currently in operation of the Alpha Jet is reviewed in terms of its unmanned and manned Attention is given to environmental considerations, both in the modes Tests conducted in the unmanned mode included evaluations construction and siting of the airport and in the design of terminal of aerodynamic stability and response to emergency situations, i e , facilities for passenger comfort It is noted that the Landvetter failure of major aircraft systems In the manned mode the tests facility is constructed to be (become) large enough to serve the major concentrated on mission simulation, with emphasis on new handling population centers of western Sweden, but is located far enough concepts Finally, the cost effectiveness of the simulator tests is from them to keep noise at an acceptable level D M W discussed DMW

A78-31944 ff The HFB 320 airborne simulator of DFVLR as test instrument for determining flight characteristics (Der Fliegende Simulator HFB 320 der DFVLR als Versuchsgerat zur Ermittlung A78-31869 Ground radar - Vital tool or luxury M Hirst von Flugeigenscnaften) D Hanke and H -H Lange (Deutsche Airports International, Feb-Mar 1978, p 24-26 Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut The disaster at Tenerife has underscored the necessity for fur Flugmechanik, Braunschweig, West Germany) Deutsche Gesell- ground radar, at least during conditions of poor visibility from the schaft fur Luft- und Raumfahrt, Symposium uber Entwicklungs- tower With the advent of MLS, the amount of air traffic in bad simulation, Cologne, West Germany, Dec 5, 6, 1977, Paper 77-082 weather is sure to increase Various ground radar systems are 19 p 9 refs In German described in terms of cost, and effectiveness in providing the tower The design principles and operation of the HFB 320 airborne with the exact position of aircraft on the ground Since the systems flight simulator and its test systems are described The model which are currently available can be prohibitively expensive, sur- sequence control concept and the control of the onboard computer veillance for single runways has also been tested, i e , Corail at are discussed Flight test results of the simulation of the B10 X Pans/Orly An Integrated Terminal Surveillance System (ITSS) using aircraft are presented to demonstrate the simulation quality Results SSR (secondary surveillance radar), under development in the United of studies of the influence of direct thrust control on an altitude States, has the ability to cover an entire airport at reduced cost maintenance problem as a function of the frequency of the short DMW period oscillation are given P T H

289 A78-31945

A78-31945 ft Proposal and construction of a hybrid flight- (Wehrtechnische Studienbeauftragte, Ottobrunn, West Germany) sight simulator with large picture projection (Entwurf und Aufbau Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium uber emer hybriden Flugsichtsimulationsanlage mit Grossbildprojektion) Entwicklungssimulation, Cologne, West Germany, Dec 5, 6, 1977, B Hechler (Darmstadt, Technische Hochschule, Darmstadt, West Paper 77-079 16 p In German Germany) Deutsche Gesellschaft fur Luft- und Raumlahrt, Sympo- Three basic questions must be answered about any new military sium uber Entwicklungssimulation, Cologne, West Germany, Dec 5, aircraft (1) What are the performance parameters of the aircraft as a 6, 197?', Paper 77-087 13 p In German whole, (2) What are the performance parameters (effectiveness) of The design of a synthetically produced, computer driven visual the weapons systems, and (3) How well can the pilot be integrated simulation operating in real time is presented. A digital system is into the total scheme In addition, questions pertaining to specific employed to transfer the geodetic coordinates onto the aircraft types of combat, both air superiority and ground attack, must be display system Attention is given to the development of a computer dealt with, and all questions, especially from the standpoint of a program designed to provide changing data profiles in the shortest government defense budget, must be considered in light of cost The possible time (an average of 4 ms for linear calculations) A Dual-Flight Simulator (DPS), in the service of the W German video-beam television projector supplies the image, which is linked to defense ministry since 1976, is evaluated in terms of its ability to the digital computer through a hybrid calculating unit D M W answer these questions by simulating the functioning of aircraft on the ground The cost of the DPS has been found to be high (due primarily to rts flexibility of program) However, the defense ministry is of the opinion that the cost of effective simulation is far cheaper than would be field tests of actual hardware D M W A78-31946 // Digital computer program maneuver pilot (Digitales Rechenprogramm Manoverpilot) L Platzoder and H J Munser (Dormer GmbH, Fnednchshafen, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium uber Entwick- lungssimulation, Cologne, West Germany, Dec 5, 6, 1977, Paper 23 A78-31950 tf New aspects in the movement simulation of p In German the research flight simulator of DFVLR (Neue Aspekte bei der A simulation of combat and flight situations for military aircraft Bewegungs-Simulation am Forschungsflugsimulator der DFVLR) F requires in addition to the use of an aircraft simulation model also a Erdmann (Deutsche Forschungs- und Versuchsanstalt fur Luft- und consideration of the actions of the pilot The use of an actual pilot Raumfahrt, Institut fur Flugfuhrung, Braunschweig, West Germany) involves an introduction of subjective and random effects These Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium uber effects have now been eliminated by developing a pilot model which Entwicklungssimulation, Cologne, West Germany, Dec 5, 6, 1977, can replace the actual pilot The pilot model can be employed in Paper 77-086 17 p In German connection with simple control tasks, air-ground maneuvers, and air To improve the simulation of movement in flight simulators, combat simulations In the case of composite maneuvers a decision suggestions for redesign of both the hydraulic servosystem as well as model for maneuver selection is also needed An additional tactical the computer software, e g , wash-out algorithms, are presented model, which determines and changes the control parameters in Attention is given to the simulation of translations! and rotational response to the given current situation, is required for air combat acceleration It is noted that long lasting acceleration can not be simulation Attention is given to the design of the controller, the adequately simulated mechanically, and that movement simulation in considered maneuvers, and the development of the tactical models general must be optimized to the type of aircraft being tested G R Standard linear wash-out systems are compared with the nonlinear system proposed D M W

A78-31951 H Simulation tests of anti-flak profiles (Simula- A78-31948 § The Dual-Fhght-Simulator on the evaluation tionsuntersuchungen zu Anti-Fla-Profilen) A Neubecker (Industrieanlagen-Betnebsgesellschaft mbH, Munich, West Germany), of air combat effectiveness (Der Dual-Flug-Simulator zur Bewertung H J Munser (Dormer GmbH, Fnednchshafen, West Germany), and der Luftkampftauglichkert) P Sepp (Industneanlagen- P Klonk Deutsche Gesellschaft fur Luft- und Raumfahrt, Sym- Betnebsgesellschaft mbH, Ottobrunn, West Germany) Deutsche posium uber Entwicklungssimulation, Cologne, West Germany, Dec Gesellschaft fur Luft- und Raumfahrt, Symposium uber Entwick- 5, 6, 1977, Paper 26 p In German lungssimulation, Cologne, West Germany, Dec 5, 6, 1977, Paper The tight air defense capability of the Warsaw Pact necessitates 77-080 19 p 5 refs In German Design and operating characteristics of the DPS are described the development of an effective penetration technique for ground- attack missions Of the various flight profiles available to advanced with attention to computer software The simulation of one-on-one NATO aircraft, an optimization scheme is presented which takes the dogfightsjs realized by analog and digital (HSI/SS-100 and CDC 6600, respectively) programs which control the projection of each following factors into account appropriate amplitude and frequency aircraft's position with respect to the other, and in terms of its own relations for the approach to target, pilot stress during approach, the built-in combat capability, i e , two different types of aircraft can be necessary recovery time for the pilot to orient himself to the pitched against each other in simulated combat An Evaluation ground-attack mode after approach, and the accuracy of the attack itself (including strafing) Methods of simulating a chosen flight Program System is described, which is designed to take virtually all profile are discussed with attention to cockprt display systems major simulation parameters into account in a 240 msec computer D MW tape D M W

A78-31955 U Catalytic flame stabilization for aircraft afterburners T J Rosfjord and B Eresman (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB, Ohio) Combustion Institute, Fall Meeting, Stanford, Calif, Oct 17, 18, 1977, Paper 10 p 10 refs The paper examines the application of catalytic flame stabiliza- A78-31949 § The Dual-Fhght-Simulator as an aid for a tion to aircraft afterburners A model was developed for the porous, government mission specialist (Der Dual-Flug-Simulator als Beur- catalytically-active flameholder in an effort to determine trade-offs teilungshilfsmittel fur emen offenthchen Auftraggeber) V Wenthe between flameholder blockage and imposed pressure loss for various

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honeycomb catalyst substrates A conventional J85 flameholder for the loss in payoff during transition due to the induced drag, the presents a 36% blockage and imposes a 3 2% pressure loss The model loss being of the order of epsilon to the 3/2 power (Author) predicts that a similarly-sized honeycomb with length-diameter ratio of 40 would impose only a 2% loss A 45%-blockage honeycomb would impose a loss equivalent to the conventional solid body A A78-32118 Joint ASD/AFWAL Combined Environment study was also made of the potential gam in combustion efficiency Reliability Test /CERT/ Evaluation Program D L Earls (USAF, versus the possible increased flameholder pressure loss P T H Flight Dynamics Laboratory, Wright Patterson AFB, Ohio) and P A McAdam (USAF, Aeronautical Systems Div , Wright-Patterson AFB, A78-31972 * It Terminal-area flight experience with the Ohio) In Environmental technology '77, Proceedings of the NASA Terminal Configured Vehicle S A Morello and L H Person. Twenty-third Annual Technical Meeting, Los Angeles, Calif, April Jr (NASA, Langley Research Center, Hampton, Va ) Flight Safety 25-27, 1977 Mount Prospect, III , Institute of Foundation, Annual Corporate Aviation Safety Seminar, 23rd, Environmental Sciences, 1977, p 203-206 Washington, D C, Apr 9-12, 1978, Paper 20 p 6 refs. The article discusses the U S Air Force Combined Environment Increases in the volume of air traffic around maior terminals, as Reliability Test (CERT) Evaluation Program which is aimed at well as the advent of MLS and other sophisticated ATC techniques, surveying the technical merit of combined environment reliability have prompted the development of aircraft specifically optimized for testing, determining cost-effectiveness, and providing implementation flight in terminal areas A modified Boeing 737, developed by NASA, planning The program is comprised of laboratory tests for avionics is presented as an illustration of a Terminal Configured Vehicle equipment in operational service Test chambers are used to simulate (TCV) Among the TCV systems discussed are the electronic attitude conditions such as random vibrations, humidity, temperature, alti- direction indicator (EADI) and the electronic horizontal situation tude, and airflow The program is also applicable to avionics indicator (EHSI), both of which are advanced display systems subsystems and various types of aircraft S C S capable of positioning the runway center line from a variety of glide slope paths, and with reference to time, i e , the on-board computer A78-32123 The error function of analytical structural can predict where the aircraft will be at a given number of seconds design H B Chenoweth (Rockwell International Corp , El Segundo, from the time of the analysis Thus, 4-D navigation (time path) can Calif) In Environmental technology '77, Proceedings of the be selected as a control mode, together with vertical and horizontal Twenty-third Annual Technical Meeting, Los Angeles, Calif, April path modes D M W 25-27, 1977 Mount Prospect, III , Institute of Environmental Sciences, 1977, p 231-234 10 refs A statistical analysis of structural static test failure data for A78-32037 ff Dynamic stability of a two blade rotor major components of aircraft is presented The data sample, based on (Stabilite dynamique d'un rotor bipale) C T Tran (ONERA, the Lustig data is compared with the basic Jablecki-Chenoweth data Chatillon-sous-Bagneux, Hauts-de-Seme, France) La Recherche The analysis results in the approximate determination of the specific Aerospatiale, Jan -Feb 1978, p 25-40 In French Research sup- statistical strength cumulative distribution as a function of rupture ported by the Centre d'Essais Aeronautiques de Toulouse strength Finally, the required factor of safety is computed for the An analytical method is presented in which Lagrange equations 'no static test' or analytical design case for the aforementioned are simplified to a system of ordinary differential equations with components over a wide range of unreliabilities It is concluded that constant coefficients in an evaluation of the dynamic stability of a components require factors of safety for the no static or analytical two blade rotor at high tip speeds with negligible aerodynamic design over three times above the usual standard and would be disturbance Attention is given to the parameterization of the prohibitive if implemented (Author) divergence velocity It is noted that the coupling of the degrees of freedom of the rotating arm and of the flexibility degrees of freedom A78-32126 A test using simulated mission profile environ- of the stand may provoke divergence D M W ments W D Everett (U S Navy, Pacific Missile Test Center, Point Mugu, Calif ) In Environmental technology '77, Proceedings of the A78-32058 Psychological Assessment of Aircraft Noise Twenty third Annual Technical Meeting, Los Angeles, Calif, April Index. C Hayashi (National Institute of Statistical Mathematics, 25-27, 1977 Mount Prospect, III , Institute of Tokyo, Japan), S Kondo (Hitachi, Ltd, Tokyo, Japan), and H Environmental Sciences, 1977, p 264-267 Kodama (Japan Women's University, Tokyo, Japan) Acoustical A Manufacturer's Run-in (MRI) test has been used for im- Society of America, Journal, vol 63, Mar 1978, p 815-822 11 refs proving the reliability of the Air-borne Instrumentation Subsystem The development and characteristics of the Psychological (AIS) pod The environmental stresses applied in this test were those Assessment of Aircraft Noise Index are described The index is based of a representative flight mission profile and were induced in the pod on an unfavorableness ratio variable which evaluates measurements by the thermo-acoustic facility at the Pacific Missile Test Center including maximum A-weighted noise level, duration of noise over 70 (PACMISTESTCEN) The test yielded realistic results in terms of the dB, and noise frequency spectra The method was tested at a location types and rate of failures that occurred in the pods (Author) 40 km west of Tokyo having a high level of aircraft noise and a low level of background noise during the day Thirty subjects were assigned to locations including those in the vicinity of the airdrome and those under flight paths Their sensory ratings, a social survey, and other sets of psychological ratings were transformed into Guttman scores S C S A78-32127 Unique test capabilities of the Eglm AFB McKmley Climatic Laboratory W Drake (USAF, Climatic Labora- tory, Eglm AFB, Fla ) In Environmental technology '77, Proceed- A78-32098 # More about fltght-path-angle transitions in ings of the Twenty-third Annual Technical Meeting, Los Angeles, optimal airplane climbs J V Breakwell (Stanford University, Calif, April 25-27, 1977 Mount Prospect, III , Stanford, Calif) Journal of Guidance and Control, vol 1, May-June Institute of Environmental Sciences, 1977, p 268-273 1978, p 205-208 The 328 million cubic foot Mam Chamber of the Climatic If the reciprocal of maximum L/D is treated as a small Laboratory is unique in that it is the largest and most complex parameter (epsilon) in various optimal airplane climb problems, climatic environmental test chamber in the world It employs an air flight-path-angle transitions between vertical climbs or dives and makeup system to cool or heat air to the test temperatures and ingest 'singular' climb arcs are found to follow a particular universal pattern this air into the chamber to allow the operation of jet engines during investigated previously in connection with minimum-time climbs climatic tests Other test chambers discussed are the 97,000 cubic with negligible mass loss The time scale of the transition is of the foot Engine and Equipment Test Cell and the 75,000 cubic foot Sun, order of the square root of epsilon, and universal formulas are given Wind, Ram, and Dust Facility (Author)

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A78-32129 An engine nozzle vibration phenomenon en- Standards Index (PSD was used to relate air quality predictions to countered in B-1 flight tests. S K Dobbs, J R Stevenson (Rockwell levels of health effects Aircraft contributions to the yearly International Corp , El Segundo, Calif ), and C L Arulf (General maximums at 5 km from the air bases were 2% or less of the PSI Electric Co , Aircraft Engine Group, Cincinnati, Ohio) In Environ- levels designated for initial health effects for carbon monoxide, mental technology '77, Proceedings of the Twenty-third Annual paniculate matter, and sulfur dioxide, but the nitrogen dioxide levels Technical Meeting, Los Angeles, Calif, April 25-27, 1977 were 5% The importance of reducing hydrocarbon emission is Mount Prospect, III , Institute of Environmental indicated M L Sciences, 1977, p 318-323 An engine nozzle vibratory instability encountered in B-1 flight A78-32257 # Basic problem of control of the motion of a tests is described Measured engine and engine nozzle ground and non-Newtonian fluid in a gap (Osnovnaia zadacha upravlenua flight vibration data were utilized to develop a theory that both dvizhemem ne-N'iutonovskoi zhidkosti v zazore) V I Elizarov explains the phenomenon and discloses a stable nozzle configuration Aviatsionnaia Tekhnika, vol 20, no 4, 1977, p 39-45 In Russian Flight and engine test cell data are presented demonstrating the The paper considers the problem of controlling the motion of a validity of the theory (Author) non-Newtonian fluid (including such aircraft structural materials as plastics, rubber and heat-insulating materials) in the gap between rotating cylinders The controls are parameters of a process in which A78-32134 Practical experience in vibration testing ex- are satisfied inequality constraints on values of functional charac- ternal avionics systems H Caruso (Westmghouse Electric Corp , terizing the pressure of flattening produced by the cylindrical rollers Aerospace and Electronic Systems Div , Baltimore, Md ) In En- and the deviation of temperature in the gap from a specified vironmental technology '77, Proceedings of the Twenty-third Annual temperature A minimax approach is taken to the problem of Technical Meeting, Los Angeles, Calif, April 25-27, 1977 determining controls B J Mount Prospect, III , Institute of Environmental Sciences, 1977, p 362-364 Two techniques for the vibration testing of large, externally- A78-32258 H The problem of choosing design parameters mounted avionics systems are discussed The test specimen is a for unpiloted flight-vehicles (K zadache vybora proektnykh paramet- 10-inch by 12 foot pod weighing 425 pounds In the first method the rov bespilotnykh letatel'nykh apparatov) N G Zaripov and T K setup employs two electrodynamic exciters for applying different Sirazetdinov Aviatsionnaia Tekhnika, vol 20, no 4, 1977, p 4652 random vibration profiles at the same time In the second setup a 6 refs In Russian single electrodynamic exciter is used to apply random vibration at The paper considers the analytical design of a hypothetical the pod's center of gravity It is suggested that combining the unpiloted flight-vehicle, the problem is posed in terms of a system of approaches yields an optimal technique The basic requirements are ordinary differential equations with inequality constraints on the (1) acquiring representative in-flight structural response data, (2) phase coordinates and controlling parameters The controlling comparing laboratory and flight responses and establishing acceler- parameters examined are initial thrust conditions, initial load on the ometer locations, (3) developing a preliminary input vibration vehicle and the operational time of the engine B J spectrum, and (4) refining the spectrum to yield structural responses which correspond to in-flight measured responses S C S A78-32262 # Analytical design of an automaton for the longitudinal control of an aircraft (Ob analiticheskom proektirovann avtomata prodol'nogo upravlenua samoletom) T K Sirazetdinov A78-32176 ff Dynamic response of lift fans subject to and V K Ivanov Aviatsionnaia Tekhnika, vol 20, no 4, 1977, p varying backpressure J M Durkm (U S Naval Material Command, 73-79 In Russian David W Taylor Naval Ship Research and Development Center, The paper considers the analytical design of a system for the Bethesda, Md ) and L H Luehr (Aerojet Liquid Rocket Co, automatic control of the longitudinal motion of an aircraft that has Sacramento, Calif ) American Institute of Aeronautics and Astro- feedback with respect to angular velocity of pitch and normal nautics and Society of Naval Architects and Marine Engineers, acceleration loading The analysis is based on examination of specific Advanced Marine Vehicles Conference, San Diego, Calif, Apr 17-19, technical constraints on the short-period longitudinal motion of the 1978, AIAA Paper 78-756 12 p Navy-supported research aircraft An algorithm for realizing the design of the control system is An analytical investigation of the dynamic performance of a presented B J centrifugal lift fan was conducted to provide an explanation for the behavior which occurred when the fan was subjected to a varying backpressure Analysis of test data shows that the fan response can A78-32264 # Theory of bendmg-torsional self-oscillations of be represented by a first order lag system An in-depth analysis of the an aircraft wing system (K teom izgibno-krutil'nykh avtokolebann v various elements of the lift fan system revealed that the inertia of the sisteme kryla samoleta) V I Safronov Aviatsionnaia Tekhnika, vol air within the fan was the primary contributor to the observed fan 20, no 4, 1977, p 87-91 8 refs In Russian behavior The analysis further showed that variations in fan speed Safronov's analytical imitation method (1972) is used to would not produce the behavior measured in the test and that the investigate the bendmg-torsional self oscillations of a wing system response due to the compliant properties of air within the fan occurs that has at least two degrees of freedom It is shown that wing-flutter at a frequency that is much higher than the frequency range of the self-oscillations may undergo synphase self-synchronization B J test A time-domain digital computer program has been developed which integrates the rate of change of fan flow with a varying A78-32267 # Quality assurance in the fabrication of prod- backpressure Good correlation is exhibited between test data and ucts in aviation technology (K obespechennu kachestva izgotovlenua the computer predictions at all frequencies (Author) izdelii aviatsionnoi tekhniki) A S Shevelev Aviatsionnaia Tekhnika, vol 20, no 4, 1977, p 103-108 In Russian A78-32222 Air quality impact of aircraft at ten U S Air The paper investigates the problem of establishing relationships Force bases D F Naugle, B C Grems, and P S Daley (USAF, Civil between geometrical and physicomechanical functional parameters and Environmental Engineering Development Office, Tyndall AFB, and technical factors during the machining of aircraft parts by means Fla ) Air Pollution Control Association, Journal, vol 28, Apr 1978, of allowance-removal from surfaces The allowance is considered p 370-373 7 refs under two aspects as a determinate design-variable and as a random The Air Quality Assessment Model (AQAM) was used in a study variable This allows refinement of structural formulas for the of the impact of aircraft emissions at 10 Air Force bases, and it was allowances as well as calculation of operational dimensions Con- found that the annual aircraft emissions contributed an average of sideration is given to the effect of nonumformity of the allowance on less than 1% to the regional emissions The EPA developed Pollutant part quality B J

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A78-32268 H Automatic sustamment of resonance con- The motion of an aircraft rolling on toroidal wheels along soft ditions in the multipoint excitation of flight-vehicle vibrations plastic ground is analyzed An expression for calculating the depth of (Avtomaticheskoe podderzhivanie uslovn rezonansa pri mnogo- penetration of the wheels, the resistance to rolling, and the take-off tochechnom vozbuzhdenn kolebanii letatel'nykh apparatov) E A distance as a function of the state of the ground and the load acting Zharov and V I Smyslov Aviatsionnaia Tekhnika, vol 20, no 4, on the wheels is derived within the framework of Babkov et al 1977, p 111-114 7refs In Russian (1959) theory of the motion of wheeled vehicles along unpaved Resonance tests involving multipoint excitation of flight vehicles ground V P are performed to measure the frequencies, natural modes, and damping coefficients required in dynamic-strength andaeroelasticity A78-32275 H Optimization of the structure of a multi- computations A specific feature of such tests is the sustamment of bulkhead large-aspect-ratio wing (Optimizatsna konstruktsn mnogo- resonance conditions In the present paper, a system which will stenochnogo kryla bol'shogo udlmenna) A P Timofeev Aviatsion- automatically sustain the resonance conditions is described, and the naia Tekhnika, vol 20, no 4, 1977, p 139-142 In Russian characteristics of the system's elements are examined Some test A method of minimum-weight design is proposed for the system results obtained with the system are reviewed V P of bulkheads in a large-aspect-ratio monocoque wing The optimal law for varying the thickness of the upper and lower panels is formulated The strength of the structure is analyzed within the A78-32269 # Optimization of the design parameters of framework of beam theory Stresses in structural members operating finned pilotless flight vehicles (Ob optimizatsii proektnykh para- m the plastic range are calculated, along with the permissible stresses metrov operennykh bespilotnykh letatel'nykh apparatov) N G in compressed elements A formal-search algorithm for solving the Zaripov Aviatsionnaia Tekhnika, vol 20, no 4, 1977, p 115-118 5 optimization problem is proposed V P refs In Russian The paper deals with the problem of optimizing the parameters A78-32296 j Lifting force of a plane H-polanzed electro- of fmnea rockets during the preliminary design phase, when the magnetic wave (Pod'emnaia sila ploskoi H-polianzovannoi elektro- dimensions of the airframe and the power characteristics of the magnitnoi volny) A I Nosich and V P Shestopalov (Khar'kovskii propulsion system have not been definitively established The Gosudarstvennyi Umversitet, Kharkov, Ukrainian SSR) Pis'ma v Droblem of minimizing the relative fuel mass is solved using a Zhumal Tekhnicheskoi Fiziki, vol 4, Jan 26, 1978, p 114 117 In minimax approach The limiting values of the control parameters are Russian determined for specific conditions at the end of the trajectory, which An incident electromagnetic wave generates in the body a are given in the form of inequalities V P mechanical force which acts in the direction of propagation of the incident wave It appears that for certain combinations of the body's A78-32270 ff Optimization of linear stabilization systems of configuration, the wavelength and the polarization of the incident flight vehicles on the basis of orthogonal filters (K optimizatsii plane wave, a lifting force is generated which acts perpendicularly to Imeinykh sistem stabilizatsn letatel'nykh apparatov na osnove opto- the propagating incident wave, and whose absolute value is drastical gonal'nykh fil'trov) A I Kaverin Aviatsionnaia Tekhnika, vol 20, ly increased by the specific high frequency resonance of the no 4, 1977. p 118-122 6 refs In Russian (scattering) body In the present paper, the lifting force is calculated Optimization of rocket stabilization systems involves difficulties which acts on an ideally conducting circular cylinder with a associated with satisfying the stability conditions for an optimal longitudinal slit, situated in the field of a plane H-polanzed wave system (factorization and separation of spectral characteristics and V P transfer functions) and with the actual implementation of optimal filters The problem is further aggravated when several disturbances A78-32308 On the possibility of classifying radar targets are applied to the system In the present paper, it is shown that these with a coherently measured echo signal (Liber erne Klassifizierungs- difficulties can be surmounted by approximating the required moglichkeit von Radarzielen mittels koharent gemessener Echo- optimal characteristics of the filter by known orthogonal functions signale). K von Schlachta Berlin, Technische Umversitat, Fach- with unknown coefficients, and determining the coefficients from bereich Elektrotechmk, Dr-lng Dissertation, 1977 96 p 38 refs In the condition of least rms error The rms error is minimized on a German digital computer Numerical calculations are carried out for a system A Neyman-Pearson test is used to classify radar targets by with a fourth-order filter, minimizing the rms error with respect to typical signal fluctuation differences with different surveillance six parameters V P radars Numerical calculations and stored radar signals were employed to evaluate the test results The radar signatures of aircraft A78-32272 H Optimal control of the longitudinal motion of (both |et and propeller) were described by optimal test functions a helicopter on the basis of an operational algorithm (Optimal'noe calculated from standard probability functions Attention is given to upravleme prodol'nym dvizhemem vertoleta na osnove operatsion- a binary fluctuation test, which was able to provide the correct nogo algonthma) B F Mishnev Aviatsionnaia Tekhnika, vol 20, classification of aircraft and bird echoes D M W no 4, 1977, p 128-131 In Russian For a helicopter, automatic pitch control during landing A78-32327 // An intermittent high Reynolds number wind approach is associated with difficulties arising due to considerable tunnel J L Stollery (Cranfield Institute of Technology, Cranfield, changes in the helicopter's aerodynamic performance during this Beds, England) and A V Murthy (National Aeronautical Labora maneuver Linear description of flight dynamics during landing tory. Bangalore, India) In Aerodynamic Testing Conference, 10th, approach does not provide a satisfactory agreement between the San Diego, Calif, April 19-21, 1978, Technical Papers model and the actual process In view of this, an attempt is made to New York, American Institute of Aeronautics and develop an automatic pitch control system on the basis of a Astronautics, I nc, 1978, p 1-5 (AIAA 78-766) sufficiently complete nonlinear description of helicopter dynamics The paper suggests a simple method of generating intermittent An operational algorithm for solving the synthesis problem for an reservoir conditions for an intermittent, cryogenic wind tunnel This optimal automatic pitch control system is proposed, and its can be done by operating some existing types of short-duration adaptation of an onboard digital computer is examined The tunnels 'in reverse' Two examples are considered (1) a modification transient response of the synthesized system is analyzed V P of the Ludwieg Tube, and (2) the Isentropic Light Piston Tunnel The sizes of tunnels required to meet the European and American A78-32273 # Aircraft takeoff from dirt airstrips (O vzlete specifications for a high Reynolds number tunnel with a 10 second samoletov s gruntovykh aerodromov) V I Pentiukhov Aviatsion- running time are given together with proposals for a more modest naia Tekhnika, vol 20, no 4, 1977, p 131-136 In Russian National or University facility with a one second test time (Author)

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A78-32328 ff The induction driven tunnel T2 at ONERA- Testing Conference, 10th, San Diego, Calif, April 19-21, 1978, CERT - Flow qualities, testing techniques and examples of results R Technical Papers New York, American Institute Michel, A Mignosi, and C Quemard (ONERA, Centre d'Etudeset de of Aeronautics and Astronautics, Inc, 1978, p 40-42 (AIAA ReCherches de Toulouse, Toulouse, France) In Aerodynamic 78-770) Testing Conference, 10th, San Diego, Calif, April 19-21, 1978, The article discusses the development and capabilities of the Technical Papers New York, American Institute National Transonic Facility which is planned for operation in 1981 of Aeronautics and Astronautics, Inc , 1978, p 6-13 (AIAA 78-767) The fan-drive, cryogenic-pressurized, closed-return facility will have A new transonic facility, conceived as a pilot unit by ONERA operating parameters of 01-12 Mach, 1-9 bars pressure, 78-340 K, for the large European High Reynolds Number Tunnel project, is 150 dB sound pressure, and plus or minus 0001 rms turbulence operating since 1975 at the ONERA Research Center in Toulouse intensity These operating conditions have been selected on the basis After a brief recall of the main characteristics of this wind tunnel T2, of several current and future aircraft and space transportation a description is given of the testing techniques which have been systems The facility will provide full-scale testing conditions for developed for studies of flows around models Two examples of calculating subsonic drag, airloads, and stability and control informa- applications are concerned with the definition of viscous and non tion Data for pre-test conditions, on-line information, and post-test viscous flows over an aerofoil and over a tapered swept wing model analysis will be computer-processed S C S Pressure measurements, wall flow visualizations, probing of boundary layers and wakes, bring detailed elements for controlling calculation A78-32332 * ff Design and subscale tests of a diffuser system methods involving a coupling between viscous and potential flows for a Mach 4 scramjet test facility E H Andrews, Jr (NASA, (Author) Langley Research Center, High-Speed Aerodynamics Div , Hampton, Va ) In Aerodynamic Testing Conference, 10th, San Diego, Calif , A78-32329 * # A critical examination of expansion tunnel April 19-21, 1978, Technical Papers New York, performance C G Miller (NASA, Langley Research Center, Space American Institute of Aeronautics and Astronautics, Inc , 1978, p Systems Div , Hampton, Va ) In Aerodynamic Testing Conference, 43-47 9 refs (AIAA 78-771) 10th, San Diego, Calif , April 19-21, 1978, Technical Papers A fixed-geometry ditfuser system was designed for use in Mach New York, American Institute of Aeronautics 4 free-jet tests of a hydrogen-burning modular scramjet engine The and Astronautics, Inc, 1978, p 14-29 20 refs (AIAA 78 768) scramjet engine has a rectangular cross section that blocks up to 33 An experimental study of the performance of the expansion percent of the existing tunnel nozzle exit area and swept leading tunnel for various test gases and range of quiescent acceleration edges of the scramjet produce an asymmetric downward flow that section and nozzle pressure, nozzle geometric area ratio, and nozzle sharply increases when the scramjet inlet unstarts Effects of these axial station has been performed Flow diagnostics used to examine conditions on the operation of the diffuser system are not accurately expansion tunnel flow characteristics were time histories and profiles predictable An experimental investigation has therefore been con- of pitot pressure and axial component of flow velocity The purpose ducted in unheated air using a subscale model of the tunnel-scramjet- of this study was to determine experimentally what limitations might diffuser system to substantiate the design Test results showed that restrict predicted operational flexibility and the advantages and the preliminary design had to be modified to obtain an acceptable disadvantages of this mode of operation as compared to the configuration of the nozzle exit, test cabin, and diffuser that would expansion tube Results are presented which demonstrate the provide shock-free flow at the scramjet inlet for simulated Mach 4 expansion tunnel offers several advantages over the expansion tube, flight at altitudes from 16,764 to 20,422 meters (Author) but the severity of the disadvantages of the tunnel makes the expansion tube mode of operation the more desirable for performing hypersomc-hypervelocity aerothermodynamic studies of proposed entry configurations (Author) A78-32333 ft Supersonic aerothermal testing - A new requirement L L Trimmer and R K Matthews (ARO, Inc, Arnold Air Force Station, Tenn ) In Aerodynamic Testing Conference, 10th, San Diego, Calif, April 1921, 1978, Technical Papers A78-32330 * ff The shock tube as a device for testing tran- New York, American Institute of Aeronautics sonic airfoils at high Reynolds numbers W J Cook (Iowa State and Astronautics, Inc , 1978, p 48-50 (AIAA 78 773) University of Science and Technology, Ames, Iowa), L L Presley, Aerothermal testing refers to the combination of aerodynamic and G T Chapman (NASA, Ames Research Center, Aerodynamics and thermodynamic effects on flight hardware Various available Research Branch, Moffett Field, Calif) In Aerodynamic Testing aerothermal test techniques are compared, including flight testing, Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical track tests, radiant heating tests, wind tunnel wedge techniques, Papers New York, American Institute of Aero- conventional wind tunnels, and high enthalpy facilities Salient nautics and Astronautics, Inc, 1978, p 30-39 16 refs Grant No features for an aerothermal test facility are identified as long or NsG-2152 (AIAA 78-769) continuous test times, duplicated flight conditions, the ability to A performance analysis of gas-driven shock tubes shows that accommodate full-scale flight hardware, high quality aerodynamic transonic airfoil flows with chord Reynolds numbers in the range of flow, extensive instrumentation, rapid test and data turnaround, and 100 million can be generated behind the primary shock in a large cost-effectiveness Optimal nozzle parameters for providing a wide shock tube A study of flow over simple airfoils has been carried out range of testing capabilities are proposed Mach number 40, test at low and intermediate Reynolds numbers to assess the testing technique Results obtained from schheren photos and airfoil section diameter 60 cm, and altitude duplication of 16,500-30,000 pressure measurements show that steady transonic flows similar to m SCS those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either A78-32334 # The AEDC Range K facility for erosion properly-contoured test section walls or a properly-designed slotted- testing C J Welsh, J R Blanks, and C P Ems (ARO, Inc , Arnold wall test section The study indicates that the shock tube is a useful Air Force Station, Tenn) In Aerodynamic Testing Conference, facility for studying two-dimensional high Reynolds number tran- 10th, San Diego, Calif, April 19-21, 1978, Technical Papers sonic airfoil flows (Author) New York, American Institute of Aeronautics and Astronautics, Inc, 1978, p 51-57 (AIAA 78-775) The AEDC Hyperbalhstic Range K facility, which was initially designed as an aerodynamic range, has been equipped with a model A78-32331 * ff Status and operational characteristics of the track guidance system This track system restricts a gun-launched test National Transonic Facility 0 W Nicks and L W McKmney article to a straight-line trajectory through different types of (NASA, Langley Research Center, Hampton, Va) In Aerodynamic controlled erosive test environments, followed by an intact recovery

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of the model The straight-line model trajectory decreases appre- A78-32344 ft Semispan wind tunnel test of a computer- ciably the problems of providing erosive fields and the required controlled self-optimizing flexible technology wing E S Levmsky quality of model photography associated with erosion testing The (General Dynamics Corp , Convair Div , San Diego, Calif ) and R L capability of model recovery is particularly significant in that Palko (ARO, Inc, Arnold Air Force Station, Tenn I In Aero- post-flight model inspection and measurements are permitted A dynamic Testing Conference, 10th, San Diego, Calif, April 19-21, description of the facility hardware and instrumentation is given 1978, Technical Papers New York, American along with a discussion of the types of erosion testing for which the Institute of Aeronautics and Astronautics, Inc, 1978, p 123-135 5 facility could be quite useful (Author) refs Research supported by the U S Air Force and ARO, Inc , Contract No N00014 76-C-0742 (AIAA 78-786) A closed loop, computer-controlled interactive testing technique has been demonstrated in the 16-foot Transonic Propulsion Wind A78-32340 ft Wind tunnel model and measuring techniques Tunnel at the Arnold Engineering Development Center using a for the investigation of three-dimensional turbulent boundary layers Self-Optimizing Flexible Technology (SOFT) wing semispan model H -P Kreplm, H. U Meier, and A Maier (Deutsche Forschungs- und that adapts its shape conformally to maximize or minimize various Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Stromungs- merit functions (eg , minimum drag) subject to both equality and mechanik, Gottingen, West Germany) In Aerodynamic Testing inequality constraints (e g , fixed lift, maximum twist, etc ) The Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical model, which employs twelve independent hydraulic actuator Papers New York, American Institute of Aero- systems to vary airfoil shape at two spanwise stations, was used for nautics and Astronautics, Inc , 1978, p 93-97 9refs (AIAA 78-781) both conventional and optimization testing Although six of seven A wind tunnel model and improved measuring techniques for optimization problems attempted were convergent, further improve- the investigation of three-dimensional laminar and turbulent bound- ment in reliability and skin smoothness is required Photogrammetric ary layers are described The tests will be carried out on an ellipsoid techniques were used to measure wing shape under airload (Author) model in the 3 m x 3 m Low Speed Wind Tunnel of the DFVLR-AVA Informations about hot wire and surface hot film probes for measuring the mean and fluctuating components of the A78-32345 ff Experiments on supercritical flows in a self- velocity as well as the magnitude and direction of the wall shear correcting wind tunnel R J Vidal and J C Enckson, Jr (Calspan stress are given To ensure that stationary boundary layers can be Corp, Buffalo, NY) In Aerodynamic Testing Conference, 10th, studied, the dynamic response of the model in the wind tunnel is San Diego, Calif, April 19-21, 1978, Technical Papers measured by means of accelerometers (Author) New York, American Institute of Aeronautics and Astronautics, Inc, 1978, p 136-141 8 refs Contracts No N00014-72-C-0102, No N00014-77 C0052, No F40600 76-C-0011 A78-32342 ft A constant aerodynamic parameter testing The Calspan Self-Correcting Wind Tunnel is a two-dimensional technique with automatic wind tunnel control R L Palko and A D facility in which the flow field in the vicinity of the walls is actively Lohr (ARO, Inc, Arnold Air Force Station, Tenn ) In Aero- controlled, and a theoretical evaluation is used in conjunction with dynamic Testing Conference, 10th, San Diego, Calif, April 19-21, flow-field measurements to confirm that wall interference has been 1978, Technical Papers New York, American minimized The facility is described and the results of experiments Institute of Aeronautics and Astronautics, Inc, 1978, p 105-115 with a 6% blockage model are presented to show that iterative (AIAA 78-784) application of wall control effectively eliminates the interference A constant aerodynamic parameter testing technique with Experiments were performed at conditions where the flow at the automatic wind tunnel control has been developed in the Propulsion walls was supercritical, and a new operating procedure is described Wind Tunnel Facility at the Arnold Engineering and Development for these conditions A method is reported for designing self- Center The technique was developed in the 1-ft transonic Aero correcting test sections This method is based upon a detailed dynamic Wind Tunnel (PWT-1T) to verify the feasibility of closed analysis of the flow in the auxiliary suction system and test section loop testing at constant aerodynamic parameters m the 4-ft transonic The results of the analysis illustrate the tradeoffs available in design Aerodynamic and the 16-ft transonic Propulsion Wind Tunnels The studies and in sizing models (Author) feasibility of setting constant lift coefficients and constant buffet intensities with variable Mach number was demonstrated over a Mach A78-32346 ff The Boeing Aerodynamic Labs data system number range from 0 4 to 1 1 The verification required development W F Hoffmann (Boeing Commercial Airplane Co , Seattle, Wash ) of an automatic pitch and Mach number control in PWT-1T In Aerodynamic Testing Conference, 10th, San Diego, Calif , April Description of the constant parameter technique, automatic Mach 19-21, 1978, Technical Papers New York, number control system, control algorithm, and the wind tunnel American Institute of Aeronautics and Astronautics, Inc , 1978, p verification of the closed-loop system operation are presented 142-144 (AIAA 78-789) (Author) An advanced data system is in development for the Boeing Aerodynamic Labs Functional modules support tasks of wind tunnel A78-32343 ff A computer-controlled video instrumentation testing, providing on-line interactive control of a test (man-m-the- technique for wind tunnel testing of full-scale lifting parachutes R loop), acquisition of raw test data, processing of the raw data to fully H Croll and C W Peterson (Sandia Laboratories, Albuquerque. N corrected standard forms, and analyzing of the data using a wind Mex ) In Aerodynamic Testing Conference, 10th, San Diego, Calif, tunnel oriented data analysis language for test time decisions and fast April 19-21, 1978, Technical Papers New York, reporting Graphical data are provided by high quality graphics American Institute of Aeronautics and Astronautics, Inc, 1978, p scopes, hardcopies, by electrostatic plotters The system, operational 116-122 Research supported by the US Department of Energy in 1979, will support the transonic tunnel and multiple test sites (AIAA 78-785) through two data systems having a total of 300 data channels A computerized video instrumentation method is developed for (Author) yielding time-resolved information on the relative motion between a lifting parachute and forebody located in a wind tunnel The instrumentation consists of a small television camera used to track A78-32356 § A technique for vorticity measurement in the positions of battery-powered lights located inside the parachute unsteady flow J E Keesee, M S Francis, and J D Lang (USAF, canopy The positions of the lights are processed by an on-line Frank J Seller Research Laboratory, Colorado Springs, Colo ) In minicomputer and transformed into yaw, pitch and roll angles Data Aerodynamic Testing Conference, 10th, San Diego, Calif, April are obtained at a rate of 30 times per second and stored in a disk 19-21, 1978, Technical Papers New York, memory along with values of the axial force and rolling movement American Institute of Aeronautics and Astronautics, Inc , 1978, p exerted on the forebody by the parachute S C S 239-248 8 refs USAF sponsored research (AIAA 78-801)

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A technique is described for determining spatial vorticity A78-32363 # Model support system interference on zero-lift distributions in non-stationary fluid flows exhibiting a periodic, time drag at transonic speeds. M S Swamy, S Ahmed, and G S Sreenath varying mean velocity field The method requires the integration of (National Aeronautical Laboratory, Bangalore, India) In Aero- velocity field data about a spatial array of closed contours to infer dynamic Testing Conference, 10th, San Diego, Calif, April 19-21, the distribution of vorticity using the generalized definition of 1978, Technical Papers New York, American circulation A digital data acquisition scheme is suggested for the Institute of Aeronautics and Astronautics, Inc, 1978, p 293-296 handling and processing of large quantities of data encountered in (AIAA 78-809) typical applications The method was used to determine the flow In this paper the support system interference on the zero-lift characteristics in portions of an unsteady separated region generated drag of an axisymmetric and an aircraft type models is discussed by an oscillating spoiler on an airfoil surface Several data display Two different techniques were adopted for the two models tested to alternatives are discussed (Author) evaluate the support sting interference It is found from these tests that the presence of a rear sting support would result in a reduction in the zero-lift drag of as much as 20 to 50 percent of the true value A78-32357 # Further experimental evaluation of the elec- This apparent reduction in drag is found to be a strong function of trostatic roll sensor at Mach 2 3 and 3 5 R E Lee, B Kann, and J the free stream Mach number close to unity Detailed pressure Knott (U S Naval Surface Weapons Center, Silver Spring, Md ) In measurements over the aft-body of the axisymmetric model suggests Aerodynamic Testing Conference, 10th, San Diego, Calif, April that due to the positive pressure field imposed by the sting over the 1921, 1978, Technical Papers New York, boat-tail region of the model the free stream Mach number at which American Institute of Aeronautics and Astronautics, Inc. 1978, p the shocks appear in the boat-tail region will be higher when the sting 249-252 NAVAIR Task AD3W-350D/004B, NAVSEA Task is present than that without it This will result in an increased drag SF32-399-592, NAVSEA Task SF32-302-41 B (AIAA 78-802) divergence Mach number for the model in the presence of the sting The electrostatic sensor is a radioactive alpha particle emitter It is argued that because of this reason the sting effect on zero-lift which ionizes the immediate air environment In the atmosphere the drag strongly depends on the Mach number close to unity (Author) lomzation produces a current which can be related to the orientation of the sensor and the earth's electrostatic field direction The current A78-32364 ff Determination of high attitude wall correc- is also affected by the air flow about the sensor This paper describes tions in a low speed wind tunnel F W Peitzman (Northrop Corp , the results of further supersonic wind-tunnel experiments to Hawthorne, Calif ) In Aerodynamic Testing Conference, 10th, San optimize the sensor cavity depth, to determine the effectiveness of Diego, Calif, April 19-21, 1978, Technical Papers high speed flow shielding, to determine the influence of free stream New York, American Institute of Aeronautics and Mach number and to evaluate a digital automatic gam control circuit Astronautics, Inc , 1978, p 297-300 (AIAA 78-810) for processing the sensor output signal for roll orientation determma An investigation was conducted to determine the validity of wall tion (Author) corrections currently in use at high angles of attack, and develop improved corrections when necessary Literature survey and theory study did not yield a method considered acceptable for use An A78-32359 * ff A parametric experimental study of the inter- experimental investigation was performed using models of identical ference effects and the boundary-condition coefficient of slotted configuration but different scale This investigation revealed that the wind-tunnel walls J L Everhart and R W Barnwell (NASA, conventional low attitude wall corrections are adequate at low Langley Research Center, Hampton, Va ) In Aerodynamic Testing attitudes (under alpha = 40 deg), and the continuity equation using Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical model planform area provides good correlation at alpha = 90 deg Papers New York, American Institute of Aero- Between 40 deg and 90 deg, correction techniques were developed to nautics and Astronautics, Inc. 1978, p 258-264 10 refs (AIAA provide correlation between the two models (Author) 78-805) An experimental study of slotted upper and lower walls in a two-dimensional transonic wind tunnel with solid sidewalls is reported Results are presented for several slot spacmgs and slot openness ratios The experimental data are pressure measurements which were made on an airfoil model and on a sidewall near one of A78-32365 * ff Condensation and its growth down the test- the slotted walls The slotted-wall boundary-condition coefficient, section of the Langley 0 3-m transonic cryogenic tunnel R M Hall which relates the pressure and streamline curvature near the wall, is (NASA, Langley Research Center, Subsonic-Transonic Aerodynamics determined from the wall pressure measurements The measured Div , Hampton, Va ) In Aerodynamic Testing Conference, 10th, wall-induced interference is correlated with the experimental values San Diego, Calif, April 19-21, 1978, Technical Papers for the boundary-condition coefficient This correlation is compared New York, American Institute of Aeronautics and with theory . (Author) Astronautics, Inc, 1978, p 301-304 6 refs (AIAA 78-811) Four total pressure probes were used to measure the growth of A78-32360 ff An empirical correction for wind tunnel wall condensation down the test section of the Langley 0 3-m tunnel, and blockage in two-dimensional transonic flow J A Blackwell, Jr the condensation data were employed to verify a mathematical (Lockheed-Georgia Co , Marietta, Ga ) In Aerodynamic Testing model which assumes condensation results from heterogeneous Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical nucleation on preexisting seed particles The onset of effects occurs Papers New York, American Institute of Aero- throughout the test section at the same total temperature but the nautics and Astronautics, Inc. 1978, p 265-275 12 refs (AIAA magnitude of the effects increases with increasing length down the 78-806) test section Condensation is important because it determines the An empirical method for correcting two-dimensional transonic minimum operating temperature of transonic cryogenic wind flow results for wind tunnel wall blockage effects has been tunnels M L developed The empirical method utilizes velocity calculations based on linear theory with free-air boundaries evaluated at vertical A78-32366 § Applications of wind tunnels to investigations positions representative of the wind tunnel walls and experimental of wind-engineering problems J E Cermak (Colorado State Uni- velocity data obtained near the tunnel walls above and below the versity, Fort Collins, Colo ) In Aerodynamic Testing Conference, model Derivation of the empirical method is presented in detail 10th, San Diego, Calif, April 19-21, 1978, Technical Papers Experimental results on 10% and 20% thick supercritical airfoils New York, American Institute of Aeronautics obtained at transonic speeds and over a wide range of wind tunnel and Astronautics, Inc, 1978, p 305-320 63 refs NSF Grant No wall porosities are used to establish the validity of the empirical ENG-76-03135 (AIAA 78-812) correction (Author) Physical modeling of the atmospheric boundary layer has been

296 A78-32381

made possible by design and construction of special low-speed wind from a conventional, Mach 5 nozzle and are compared with tunnels This development enables natural winds at a particular site measurements from a rapid-expansion, Mach 5 nozzle (Author) to be simulated for a wide range of meteorological conditions Through measurements on small-scale models and use of appropriate A78-32372 // The use of fluidtzed beds for heating air for similarity criteria the simulated natural winds can be used to obtain a wind tunnels V Zakkay, G Miller (New York University, Westbury, wide variety of wind-effect data for planning and design purposes N Y ), and S Panunzio In Aerodynamic Testing Conference, 10th, Techniques for determination of mean wind forces, fluctuating San Diego, Calif, April 19-21, 1978, Technical Papers pressures on exterior surfaces and dynamic response of structures are New York, American Institute of Aeronautics and described Applications to determination of air-pollutant concentra- Astronautics, Inc , 1978, p 365-375 Contract No EF-76-C-01-2256 tions near power-plant sites and methane concentrations resulting (AIAA 78-818) from LNG spills, to location of snow-drifts and to measurement of A method is presented herein whereby air passing through heat wind characteristics for improvement of pedestrian comfort, and for exchanger tubes is heated by the particles of a fluidized bed This evaluation of flight safety during landing and takeoff are also scheme, which has been used successfully in the coal industry for discussed and illustrated by specific examples (Author) generating steam in boilers, could be modified and adopted for the purpose of generating high temperature air for driving wind tunnels Fluidized bed combustion can utilize any fossil fuel and therefore A78-32367 # An experimental facility for wind engineering substantial cost saving can be derived if coal is utilized The analysis research P M Sforza, W Stasi, and L Gotkm (New York, presented indicates this method may be superior to regular pebble Polytechnic Institute, Farmmgdale, N Y ) In Aerodynamic Testing bed storage heaters which were developed for pre-heating air m the Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical early 50's This is due to the fact that such a process results in a Papers New York, American Institute of Aero- substantially higher film coefficient and a cleaner product (the nautics and Astronautics, Inc. 1978, p 321-329 12 refs Contract high-temperature air) (Author) No E(49-18)-2358 (AIAA 78-813) Experimental research in wind engineering must rely on testing in a controlled laboratory environment as well as field testing in the A78-32373 # Optimum design of wind tunnel contractions uncontrolled natural wind A facility for such research, developed in M N Mikhail and W J Rambird (Dilworth, Secord, Meagher and the Aerodynamics Laboratories of the Polytechnic Institute of New Associates, Ltd , Toronto, Canada) In Aerodynamic Testing Con- York, is described This facility includes both a field test station and ference, 10th, San Diego, Calif, April 19-21, 1978, Technical Papers a laboratory test station for atmospheric boundary layer research New York, American Institute of Aeronautics The utilization of this complex is discussed in terms of an ongoing and Astronautics, Inc , 1978, p 376-384 17 refs (AIAA 78-819) project on wind energy conversion to illustrate the various capa- A method of design of low speed wind tunnel contractions is bilities that have been developed Applications of this facility to presented An optimum contraction is considered to be the shortest other problems in wind engineering are also described (Author) one that satisfies flow quality requirements in the test section, i e , avoids any boundary layer separation and supplies flow to the test A78-32368 * # Moving ground simulation by tangential blow- section with a specified degree of uniformity For the solution of the ing J E Hackett and R A Boles (Lockheed-Georgia Co , Marietta, governing mviscid flow equations in an axisymmetric duct of Ga ) In Aerodynamic Testing Conference, 10th, San Diego, Calif , arbitrary shape, a numerical scheme has been developed based on the April 19-21, 1978, Technical Papers New York, method of lines The boundary-layer behavior is studied using both American Institute of Aeronautics and Astronautics, Inc, 1978, p Stratford's criterion for turbulent separation and a 'lag-entramment' 330-335 5 refs Contracts No NAS2-6690, No NAS2-8745, No integral method It is shown that by optimizing duct wall curvature NAS2-9155 (AIAA 78-814) distribution, it is possible to reduce contraction length to about one Belt-type moving ground equipment, used for ground-effect half of that presently used in practice for a given test section flow simulation in STOL and VTOL tests, can be inconvenient and costly, quality For example, a contraction with an area ratio of eight, for a especially in larger tunnels In most cases such difficulties may be large wind tunnel, can be as short as one inlet radius The present avoided by employing tangential blowing at the ground surface, from method relates the shape and length of the contraction closely to the a single slot The paper reviews several powered model tests using degree of flow quality required in the test section, to the contraction both moving ground and tangential blowing and describes the slot ratio, to the inlet flow Reynolds number, and to the viscous flow configuration, and the test techniques which were developed conditions in the settling chamber upstream of the contraction inlet Ground skin friction is monitored to set blowing levels and no (Author) model-dependent calculations are needed It is also shown that application to center-tunnel testing can delay tunnel flow breakdown very considerably (Author)

A78-32381 ft Sting effects as determined by the measure- A78-32371 • ff A new technique for reducing test section ment of pitch-damping derivatives and base pressures at Mach noise in supersonic wind tunnels J B Anders, P C Stamback, and I number 3 B L Uselton (ARO, Inc, Arnold Air Force Station, E Beckwith (NASA, Langley Research Center, High-Speed Aero- Tenn ) In Aerodynamic Testing Conference, 10th, San Diego, dynamics Div , Hampton, Va ) In Aerodynamic Testing Conference, Calif , April 19-21, 1978, Technical Papers New 10th, San Diego, Calif, April 19-21, 1978, Technical Papers York, American Institute of Aeronautics and Astronautics, Inc, New York, American Institute of Aeronautics 1978, p 451-466 41 refs (AIAA 78-830) and Astronautics, Inc, 1978, p 354-364 25 refs (AIAA 78-817) A research program was initiated for the purpose of investigating A new technique is presented for obtaining a low-noise test some of the problem areas in regard to support interference The environment in a high-speed wind tunnel This technique utilizes the critical sting length at alpha = 0 was determined by the measurement fact that the primary noise source for high supersonic/hypersonic of pitch-damping derivatives for laminar, transitional, and turbulent wind tunnels is radiated noise from the turbulent, tunnel-wall boundary layers at the model base Data were obtained at a boundary layer Because of the high directionality of sound in freestream Mach number of 3 on a blunted 7-deg cone The results supersonic flows this test section noise originates far upstream on the showed that the critical sting length with respect to sting interference walls of the nozzle at the 'acoustic origin' It is shown that tailoring on pitch-damping data was two model diameters and was in- the nozzle contour to reduce the acoustic origin Mach number dependent of the type of boundary layer at the model base The significantly reduces the noise level in the upstream half of the effects of sting length on base pressure and wedge plates on sting nozzle test rhombus Experimental noise measurements are presented interference were also investigated (Author)

297 A78-32386

A78-32386 * ff New rotation-balance apparatus for measuring airplane spin aerodynamics in the wind tunnel G N Malcolm (NASA, Ames Research Center, Moffett Field, Calif) In Aero- dynamic Testing Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1978, p 495-502 7 refs (AIAA 78-835) An advanced rotation-balance apparatus has been developed for the Ames 12-ft pressure tunnel to study the effects of spin rate, angles of attack and sideslip, and, particularly, Reynolds number on the aerodynamics of fighter and general aviation aircraft in a steady spin Angles of attack to 100 deg and angles of sideslip to 30 deg are possible with spin rates to 42 rad/sec (400 rpm) and Reynolds numbers to 30 million/m on fighter models with wing spans that are typically 07mA complete description of the new rotation-balance apparatus, the sting/balance/model assembly, and the operational capabilities is given (Author)

A78-32388 # Ejector-powered engine simulators for small- scale wind tunnel models of high performance aircraft R J Matz and G D Smith (ARO, Inc , Arnold Air Force Station, Tenn ) In Aerodynamic Testing Conference, 10th, San Diego, Calif, April 19-21, 1978, Technical Papers New York, American Institute of Aeronautics and Astronautics, Inc, 1978 10 p 12 refs (AIAA 78-826) Ejector-powered engine simulators (EPES), capable of simultaneously providing engine inlet and exhaust effects in small-scale wind tunnel models of high-performance aircraft, are being investigated at AEDC Experimental results obtained from EPES driven with high-pressure unheated air and analytical results obtained from a simple theoretical model are presented to show the relative importance of ejector system components on EPES performance The performance of two EPES units designed and calibrated for wind tunnel evaluation in an existing 0 06-scale B-1 model is discussed, along with problems encountered in application of EPES to existing wind tunnel models Preliminary results from the wind tunnel tests are presented which indicate that the EPES unit does a reasonable job of duplicating engine-induced flow effects The results indicate that application of EPES units for simultaneous inlet and exhaust simulation in high-performance aircraft wind tunnel models is a viable test technique, although additional development work is needed in several areas (Author)

A78-32396 * A spectroradiometer for airborne remote sensing H -Y Chin (NASA, Goddard Institute for Space Studies, New York, N Y ) and W Collins (NASA, Goddard Institute for Space Studies, Columbia University, New York, N Y ) Photogrammetric Engineering and Remote Sensing, vol 44, Apr 1978, p 507-517 11 refs NASA-supported research A remote sensing system for use in light aircraft is discussed with attention to its applications in measuring geologic zones of alteration, vegetation canopies, and the spectral properties of water bodies A parallel electro-optical input spectroradiometer configuration with 500 channels operating in the 400-1100 nm region is described A resolution of 18 meters square from an altitude of 600 m at 200 kmh is obtained with 4-digit spectral radiance data at 2 5 spectra/sec on a 9-track tape in computer compatible format D M W

298 N78-20065

The aerodynamic roll damping and the yawing moment due to roll rate characteristics were investigated at subsonic speeds for a model with either sweptback or swept forward wings The tests were made in the Langley high speed 7 by 10 foot tunnel for Mach numbers between 0 3 and 0 7 The configuration with a 60 deg sweptback wing had positive damping in roll up to the maximum test angle of attack of almost 20 deg The 32 deg swept forward wing configuration had positive damping in roll at the lower angles of attack, but there was a decrease in STAR ENTRIES damping and negative damping in roll was measured at the highest angles of attack Author

N78-20O63*# National Aeronautics and Space Administration N78-2005O*# National Aeronautics and Space Administration Langley Research Center Langley Station Va Langley Research Center Langley Station Va EFFECT OF WING LETS ON A FIRST-GENERATION JET SUMMARY OF NASA LANDING GEAR RESEARCH TRANSPORTWING 3 PRESSURE AND SPANWISE LOAD Bruce D Fisher Robert K Sleeper and Sandy M Stubbs Mar DISTRIBUTIONS FOR A SEMISPAN MODEL AT 1978 34 p refs MACH 030 (NASA-TM-78679) Avail NTIS HC A03/MF A01 CSCL 01C Lawrence C Montoya Peter F Jacobs and Stuart G Flechner The landing gear is summarized Research relative to tire Washington Jun 1977 102 p refs Prepared in cooperation tread powered wheel taxiing, air cushion landing systems and with NASA Dryden Flight Res Center crosswmd landing gear is discussed in some detail An airplane (NASA-TN-D-8478 L-11370) Avail NTIS HC A06/MF A01 ground-handling simulator was developed to provide a research CSCL 01A tool for investigating, in perfect safety directional control and Pressure and spanwise load distributions on a first-generation braking problems of airplanes on slippery runways in the jet transport semispan model at a Mach number of 0 30 are presence of crosswinds One example of its application is to given for the basic wing and for configurations with an upper explore airplane control problems during high speed turnoffs from winglet only, upper and lower winglets and a simple wing-tip mam runways onto taxiways The simulation development was extension To simulate second-segment-climb lift conditions performed in a visual-motion simulator A discussion of some of leading- and/or trailing-edge flaps were added to some configura- the significant developments is presented Author tions Author

N78-20068 Illinois Inst of Tech Chicago AN EXPERIMENTAL INVESTIGATION OF OSCILLATING FLOWS OVER AN AIRFOIL Ph D Thesis Lakshmendra Shanker Saxena 1977 225 p Avail Umv Microfilms Order No 7800881 N78-2O064*# National Aeronautics and Space Administration The basic features of unsteady flow fields generated by Langley Research Center Langley Station. Va smusoidally oscillating airstreams over a stationary airfoil at fixed EFFECT OF WINGLETS ON A FIRST-GENERATION JET angles of attack close to the angle of static stall were studied TRANSPORT WING 1 LONGITUDINAL AERODYNAMIC with focus on the dynamic stall of helicopter rotors Hot-wire CHARACTERISTICS OF A SEMISPAN MODEL AT SUB- surveys of the velocity field above the airfoil (NACA 0012 profile) SONIC SPEEDS and surface pressure measurements around the airfoil were used Peter F Jacobs, Stuart G Flechner and Lawrence C Montoya with data from heated surface film gages and flow visualization Washington Jun 1977 50 p refs Prepared in cooperation achieved through silk tufts Reduced frequencies of 0 18 and with NASA Dryden Flight Res Center 09 were used at amplitude ratios of 0 18 and Reynolds number (NASA-TN-D-8473 L-11354) Avail NTIS HC A03/MF A01 of 250 000 Periodic sampling and averaging techniques were CSCL 01A used to obtain instantaneous boundary layer and wake mean The effects of winglets and a simple wing-tip extension on velocity profiles and pressure coefficient distributions at different the aerodynamic forces and moments and the flow-field cross instants of the freestream oscillation cycle Dissert Abstr flow velocity vectors behind the wing tip of a first generation jet transport wing were investigated in the Langley 8-foot transonic pressure tunnel using a semi-span model The test was conducted N78-20O6O+ Societe Bertm et Cie. Villeurbanne (France) at Mach numbers of 030. 070 075 078. and 080 At a AERODYNAMIC FLUID-FIBER INTERACTIONS Final Report Mach number of 030 the configurations were tested with [ETUDE DES INTERACTIONS AERODYNAMIQUES FLUIDE- combinations of leading- and trailing-edge flaps Author FIL] B Biot and G Lovat Apr 1977 118p refs In FRENCH (Contract DGRST-74-7-0695) (NT-77-CN-1) Avail NTIS HC A06 The aerodynamic friction of textile fibers in a parallel uniform flow was studied at speeds up to 150 m/s The flow turbulence N78-2OO65*jjl National Aeronautics and Space Administration has a negligible influence on smooth fibers and an appreciable Langley Research Center Langley Station, Va influence on textured fibers Th,e confinement of the flow in a EFFECT OF WINGLETS ON A FIRST-GENERATION JET tube modifies the laws obtained for infinite vanes In the case TRANSPORTWING 2: PRESSURE AND SPANWISE LOAD of smooth fibers the tube tends to impose on the fiber the DISTRIBUTIONS FOR A SEMISPAN MODEL AT HIGH evolution of the friction law as a function of the Reynolds law SUBSONIC SPEEDS For textured fibers the friction augments with the confinement Lawrence C Montoya, Stuart G Flechner and Peter F Jacobs Translational motion of the fiber leads to an increase of the Washington Jul 1977 211 p refs Prepared in cooperation friction coefficient ESA with NASA Dryden Flight Res Center (NASA-TN-D-8474 L-11026) Avail NTIS HC A10/MF A01 CSCL 01A N78-20O61*# National Aeronautics and Space Administration Pressure and spanwise load distributions on a first-generation Langley Research Center Langley Station Va jet transport semispan model at high subsonic speeds are SUBSONIC ROLL DAMPING OF A MODEL WITH SWEPT- presented for the basic wing and for configurations with an BACK AND SWEPT-FORWARD WINGS upper winglet only upper and lower winglets. and a simple Richmond P Boyden Mar 1978 36 p refs wing-tip extension Selected data are discussed to show the (NASA-TM-78677) Avail NTIS HC A03/MF A01 CSCL 01A general trends and effects of the various configurations Author

299 N78-20067

N78-20067*# Virginia Univ . Charlottesville Dept of Mechanical N78-20070*# Virginia Univ , Charlottesville Dept of Mechanical and Aerospace Engineering and Aerospace Engineering UNSTEADY LOADS DUE TO PROPULSIVE LIFT CONFIGU- UNSTEADY LOADS DUE TO PROPULSIVE LIFT CONFIGU- RATIONS PART A INVESTIGATION OF SCALING LAWS RATIONS PART C DEVELOPMENT OF EXPERIMENTAL Final Report (MENTAL FACILITY FOR THE INVESTIGATION OF SCALING Jeffrey B Morton and John K Haviland Mar 1978 57 p EFFECTS ON PROPULSIVE LIFT CONFIGURATIONS refs J K Haviland and William W Herlmg Mar 1978 112 p (Grant NGR-47-005-219-03) refs (NASA-CR-156120. UVA/528095/MAE78/115-Pt-A) Avail (Grant NGR-47-005-219-03) NTIS HC A04/MF A01 CSCL 01A (NASA-CR-156123. UVA/528095/MAE78/114-Pt-D) Avail This study covered scaling laws, and pressure measurements NTIS HC A06/MF A01 CSCL 01A made to determine details of the large scale |et structure and The design and construction of an experimental facility for to verify scaling laws by direct comparison The basis of' the investigation of scaling effects in propulsive lift configurations comparison was a test facility at NASA Langley in which a' are described The facility was modeled after an existing full JT-15D exhausted over a boilerplater airfoil surface to reproduce size NASA facility which consisted of a coaxial turbofan jet upper surface blowing conditions A quarter scale model was engine with a rectangular nozzle in a blown surface configuration built of this facility using cold jets A comparison between full The flow field of the model facility was examined with and scale and model pressure coefficient spectra presented as without a simulated wing surface in place at several locations functions of Strouhal numbers showed fair agreement however, downstream of the nozzle exit plane Emphasis was placed on a shift of spectral peaks was noted This was not believed to obtaining pressure measurements which were made with static be due to Mach number or Reynolds number effects, but did probes and surface pressure ports connected via plastic tubing appear to be traceable to discrepancies in jet temperatures A to condenser microphones for fluctuating measurements Several correction for jet temperature was then tried similar to one pressure spectra were compared with those obtained from the used for far field noise prediction This was found to correct the NASA facility and were used in a preliminary evaluation of spectral peak discrepancy Author scaling laws Author

N78-20O68*# Virginia Univ Charlottesville Dept of Mechanical and Aerospace Engineering N78-20071*| National Aeronautics and Space Administration UNSTEADY LOADS DUE TO PROPULSIVE LIFT CONFIGU- Langley Research Center Langley Station Va RATIONS PARTS PRESSURE AND VELOCITY MEASURE- SUBSONIC LONGITUDINAL AND LATERAL-DIRECTIONAL MENTS IN A THREE DIMENSIONAL WALL JET STATIC AERODYNAMIC CHARACTERISTICS OF A Final Report GENERAL RESEARCH FIGHTER CONFIGURATION EM- G D Catalano. J B Morton and R R Humphns Mar 1978 PLOYING A JET SHEET VORTEX GENERATOR 34 p refs Sponsored in part by NSF Jarrett K Huffman Charles H Fox. Jr and Henry Ziegler (Northrup (Grant NGR-47-005-219-03) Corp) Jan 1978 189 p refs (NASA-CR-156121 UVA/526033/MAE78/101-Pt-B (NASA-TM-74049) Avail NTIS HC A09/MF A01 CSCL 01A UVA/528095/MAE78/115-Pt-B) Avail NTIS A configuration concept for developing vortex lift, which HC A03/MF A01 CSCL 01A replaces the physical wing strake with a jet sheet generated The effects of increasing the velocity ratio lambda sub j fluid strake was investigated on a general research fighter model were explored The quantities measured include the width of The vertical and horizontal location of the jet sheet with respect the mixing region the mean velocity field turbulent intensities to the wing leading edge was studied over a momentum coefficient and time scales In addition wall and static pressure velocity range from 0 to 0 24 in the Langley 7- by 10-foot high speed correlations and coherences are presented The velocity measure- tunnel over a Mach number range from 0 3 to 0 8 The angle ments were made using a laser Doppler velocimeter with a of attack range studied was from -2 to 30 deg at sideslip angles phase locked loop processor The fluctuating pressures were of 0, -5, and 5 deg Test data are presented without analysis monitored using condenser type microphones Author Author

N78-20O72*# National Aeronautics and Space Administration Langley Research Center Langley Station Va N78-20069*# Virginia Univ Charlottesville Dept of Mechanical TRANSONIC STATIC AND DYNAMIC STABILITY CHARAC- and Aerospace Engineering TERISTICS OF A FINNED PROJECTILE CONFIGURATION UNSTEADY LOADS DUE TO PROPULSIVE LIFT CONFIGU- Richmond P Boyden Cuyler W Brooks Jr and Edwin E RATIONS PART C DEVELOPMENT OF EXPERIMENTAL Davenport Apr 1978 84 p refs TECHNIQUES FOR INVESTIGATION OF UNSTEADY (NASA-TM-74058 L-11966) Avail NTIS HC A05/MF A01 PRESSURES BEHIND A COLD MODEL JET CSCL 01A J K Haviland and James C Schroeder Mar 1978 147 p Static and dynamic stability tests were made of a finned refs projectile configuration with the aft-mounted fins arranged in a (Grant NGR-47-005-219-03) cruciform pattern The tests were made at free stream Mach (NASA-CR-156122 UVA/528095/MAE78/113-Pt-C) Avail numbers of 0 7 0 9. 1 1 and 1 2 in the Langley 8-foot NTIS HC A07/MF A01 CSCL 01A transonic pressure tunnel Some of the parameters measured As part of an overall study of the scaling laws for the during the tests were lift drag pitching moment, pitch damping, fluctuating pressures induced on the wings and flaps of STOL and roll damping Configurations tested included the body with aircraft by jet engine impingement, an experimental investigation undeflected fins, the body with various fin deflections for control was made of the near field fluctuating pressures behind a cold and the body with fins removed Theoretical estimates of the circular jet both when it was free and when it was impinging stability derivatives were made for the fins on configuration on a flat plate Miniature static pressure probes were developed Author for measurements in the free jet and on the flat plate which were connected by plastic tubing to 1/8 inch microphones and N78-20073*| National Aeronautics and Space Administration acted as pressure transducers Using a digital correlator together Langley Research Center, Langley Station, Va with an FFT program on the CDC 6400 computer, spectral SUBSONIC LONGITUDINAL AND LATERAL-DIRECTIONAL densities, relative amplitudes phase lags and coherences were STATIC AERODYNAMIC CHARACTERISTICS FOR A also obtained for the signals from pairs of these probes and MODEL WITH SWEPT BACK AND SWEPT FORWARD were used to calibrate these probes directly against microphones WINGS This system of instrumentation was employed to obtain single Jarrett K Huffman and Charles H Fox. Jr Feb 1978 43 p point rms and third octave surveys of the static pressures in refs the free jet and on the surface of the plate Author (NASA-TM-74093) Avail NTIS HC A03/MF A01 CSCL 01A

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A general research fighter model was tested in the Langley G W Brune and J W Manke Mar 1978 204 p refs 7- by 10-foot high speed tunnel at a Mach number of 0 3 (Contract NAS1-14522) With a conventional empennage the model was tested with the (NASA-CR-145323 D6-45099) Avail NTIS wing in a 60 deg swept back configuration and in a 32 deg HC A10/MF A01 CSCL01A swept forward configuration The 32 deg swept forward An improved version of the NASA-Lockheed computer configuration was also tested with a strake Very limited data program for the analysis of multielement airfoils is described was obtained with a wing in a 50 deg swept back configuration The predictions of the program are evaluated by comparison and a 7 deg swept forward configuration The angle of attack with recent experimental high lift data including lift, pitching range was from approximately -4 deg to 48 deg at sideslip moment profile drag and detailed distributions of surface angles of 0 deg -5 deg. and 5 deg Author pressures and boundary layer parameters The results of the evaluation show that the contract objectives of improving program N78-20074*jf National Aeronautics and Space Administration reliability and accuracy have been met Author Langley Research Center Langley Station Va ONSET OF CONDENSATION EFFECTS WITH A NACA 0012-64 AIRFOIL TESTED IN THE LANGLEY 03-METER CRYOGENIC TUNNEL Robert M Hall Mar 1978 84 p refs N78-20O78*# National Aeronautics and Space Administration (NASA-TM-78666) Avail NTIS HC A05/MF A01 CSCL 01A Langley Research Center Langley Station Va A 0137m airfoil was tested in a 03m transonic cryogenic SIMPLIFIED SONIC-BOOM PREDICTION tunnel at free stream Mach numbers of 075. 085. and 095 Harry W Carlson Mar 1978 50 p refs over a total pressure range from 12 to 50 atmospheres The (NASA-TP-1122. L-11794) Avail NTIS HC A03/MF A01 onset of condensation effects were found to correlate more with CSCL 20A the amount of supercooling in the free stream than it did with Sonic boom overpressures and signature duration may be the supercooling in the region of maximum local Mach number predicted for the entire affected ground area for a wide variety over the airfoil Effects in the pressure distribution over the airfoil of supersonic airplane configurations and spacecraft operating were generally seen to appear over its entire length at nearly at altitudes up to 76 km in level flight or in moderate climbing the same total temperature Both observations suggest the or descending flight paths The outlined procedure relies to a possibility of heterogeneous nucleation occurring in the free great extent on the use of charts to provide generation and stream The potential operational benefits of the supercooling propagation factors for use in relatively simple expressions for realized are presented in terms of increased Reynolds number signature calculation Computational requirements can be met capability at a given tunnel total pressure reduced drive fan by hand-held scientific calculators or even by slide rules A power if Reynolds number is held constant and reduced liquid variety of correlations of predicted and measured sonic-boom nitrogen consumption if Reynolds number is again constant data for airplanes and spacecraft serve to demonstrate the Depending on total pressure and free stream Mach number, applicability of the simplified method Author these three benefits are found to respectively vary from 7 to 19%, 11 to 25%. and 9 to 20% Author

N78-20076*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va N78-20079*jjl National Aeronautics and Space Administration THEORETICAL ANALYSIS OF AERODYNAMIC CHARAC- Langley Research Center Langley Station Va TERISTICS OF TWO HELICOPTER ROTOR AIRFOILS WIND-TUNNEL INVESTIGATION AT MACH NUMBERS Charles E K Morris, Jr and William T Yeager Jr (USARTL FROM 1 90 TO 2 86 OF A CANARD-CONTROLLED MISSILE Hampton Va) Mar 1978 29 p refs WITH RAM-AIR-JET SPOILER ROLL CONTROL A B Blair Jr Mar 1978 104 p refs (NASA-TM-78680) Avail NTIS HC A03/MF A01 CSCL01A (NASA-TP-1124 L-11873) Avail NTIS HC A06/MF A01 An analytical study was conducted to predict the aerodynamic CSCL 01A characteristics of two helicopter rotor airfoils Documentation of The efficacy of using a ram-air-jet spoiler roll control device the predictive process covers the development of empirical factors on a typical canard-controlled missile configuration was investi- used in conjunction with computer programs for airfoil analysis gated For roll control comparisons, conventional aileron controls Tables of lift, drag and pitchmg-moment coefficient for each on the tail fins were also tested The results indicate that the airfoil were prepared for two dimensional, steady flow conditions roll control of the ram-air-jet spoiler tail fins at the highest at Mach numbers from 03 to 09 and Reynolds numbers of free-stream Mach number compared favorably with that of the 7.700.000 to 23000000. respectively Author conventional 11-70 area-ratio tail fin ailerons, each deflected 10 deg The roll control of the tail fin ailerons decreased while N78-20076*# Boeing Commercial Airplane Co Seattle. Wash that of the ram-air-jet spoiler increased with free-stream Mach A CRITICAL EVALUATION OF THE PREDICTIONS OF THE number The addition of the ram-air-jet spoiler tail fins or NASA-LOCKHEED MULTIELEMENT AIRFOIL COMPUTER flow-through tip chord nacelles on the tail fins resulted in only PROGRAM Final Report. Jul. 1976 - Jin 1978 small changes in basic missile longitudinal stability The axial G W Brune and J W Manke Mar 1978 67 p refs force coefficient of the operating ram-air-jet spoiler is significantly (Contract NAS1-14522) larger than that of conventional ailerons and results primarily (NASA-CR-145322, D6-45100) Avail NTIS from the total pressure behind a normal shock in front of the HC A04/MF A01 CSCL 01A nacelle inlets Author Theoretical predictions of several versions of the multielement airfoil computer program are evaluated The computed results are compared with experimental high lift data of general aviation airfoils with a single trailing edge flap and of airfoils with a leading edge flap and double slotted trailing edge flaps Theoreti- cal and experimental data include lift pitching moment profile N78-20O8O*# National Aeronautics and Space Administration Lewis Research Center Cleveland. Ohio drag and surface pressure distributions, boundary layer integral parameters skin friction coefficients and velocity profiles Author EFFECT OF COOUNG-HOLE GEOMETRY ON AERODYNAM- IC PERFORMANCE OF A FILM-COOLED TURBINE VANE TESTED WITH COLD AIR IN A TWO-DIMENSIONAL CASCADE N78-20077*# Boeing Commercial Airplane Co. Seattle Wash John F Kline Roy G Stabe and Thomas P Moffrtt Mar 1978 AN IMPROVED VERSION OF THE NASA-LOCKHEED 49 p refs MULTIELEMENT AIRFOIL ANALYSIS COMPUTER PRO- (NASA-TP-1136. E-9174) Avail NTIS HC A03/MF A01 CSCL GRAM Final Report 01A

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The effect of the orientation and cooling-hole size on N78-20087f Naval Ship Research and Development Center turbine-vane aerodynamic losses was evaluated The contribution Bethesda Md Aviation and Surface Effects Dept of individual vane regions to the overall effect was also ANALYSIS OF EMPIRICALLY DETERMINED AERODYNAM- investigated Test configurations were based upon a representative IC AND RAM COEFFICIENTS FOR A POWER AUGMENTED configuration having 45 spanwise rows of holes spaced about RAM WING-IN-GROUND EFFECT Final Report. Jun - Oct the entire vane profile Nominal hole diameters of 0 0254 and 1977 00356 cm and nominal hole orientations of 35 deg 45 deg David G Rousseau Oct 1977 22 p refs and 55 deg from the local vane surface and 0 deg 45 deg (AD-A049636. DTNSRDC/ASED-396) Avail NTIS 3nd 90 deg from the main-stream flow direction were investigated HC A02/MF A01 CSCL 01/3 Flow conditions and aerodynamic losses were determined by With the advent of a theory for power-augmented-ram vane-exit surveys of total pressure static pressure, and flow wing-m-ground-effect vehicle performance there is a need for angle Author detailed comparison with test data This report presents a comparison of test data with theory in particular the determina- N78-20081 *# National Aeronautics and Space Administration tion of the effects of changes in vehicle geometry and cruising Langley Research Center Langley Station Va height on flight performance Good correlation between theory EFFECT OF WING LETS ON A FIRST-GENERATION JET and experiment has been achieved for lift and pitching moment TRANSPORT WING 5 STABILITY CHARACTERISTICS and correlation with drag is promising for some geometries OF A FULL-SPAN WING WITH A GENERALIZED FUSELAGE Author (GRA) AT HIGH SUBSONIC SPEEDS Peter F Jacobs Mar 1978 71 p refs N78-20O88# Toronto Umv (Ontario) Inst for Aerospace (NASA-TP-1163 L-11982) Avail NTIS HC A04/MF A01 Studies CSCL 01A RESEARCH ON VARIOUS ASPECTS OF ATMOSPHERIC The effects of winglets on the static aerodynamic stability FLIGHT Final Technical Report, 1971 - 1976 characteristics of a KC-135A jet transport model at high subsonic J H Deleeuw and L D Reid Nov 1976 35 p refs speeds are presented The investigation was conducted in the (Grant AF-AFOSR-2091-71) Langley 8 foot transonic pressure tunnel using 0 035-scale wing (AD-A033681. AFOSR-76-1422TR) Avail NTIS panels mounted on a generalized research fuselage Data were HC A03/MF A01 CSCL 04/1 taken over a Mach number range from 0 50 to 0 95 at angles This research has studied aerodynamic problems in upper of attack ranging from -12 deg to 20 deg and sideslip angles atmospheric flight and the disturbed flight of aircraft due to low of 0 deg 5 deg and -5 deg The model was tested at two level turbulence during the approach phase Individual project Reynolds number ranges to achieve a wide angle of attack range summaries include (1) Calculations have been made for low and to determine the effect of Reynolds number on stability speed sphere drag in transition flow, experiments confirm the Results indicate that adding the winglets to the basic wing theoretical predictions (2) An electron beam Doppler profile configuration produces small increases in both lateral and apparatus has been used to delineate the shape of the distribution longitudinal aerodynamic stability and that the model stability function in a heat transfer problem indicating its progressive increases slightly with Reynolds number The winglets do increase nonequilibnum nature as the degree of rarefaction increased the wing bending moments slightly but the buffet onset (3) An electron beam fluorescence instrument has been designed characteristics of the model are not affected by the winglets for rocketborne use to measure upper atmospheric concentrations Author of nitrogen, molecular oxygen atomic oxygen, rotational and vibrational temperatures a number of launches have been made on Black Brant rockets from Fort Churchill (AD 033 680) (4) A laser-Doppler instrument has been constructed and checked N78-20083# Auburn Umv Ala Dept of Aerospace out as a means of remotely measuring turbulence in the Engineering atmospheric boundary layer, and (5) Wind tunnel measurements ANALYSIS AND COMPARISON OF SEVERAL METHODS in a controlled turbulent shear flow have been made along FOR COMPUTING AERODYNAMIC COMPRESSIBILITY representative flight paths for STOL vehicles to provide an input AND INTERFERENCE EFFECTS UP TO CRITICAL MACH to predict dispersions of the landing point GRA NUMBERS Final Report Fred W Martin James Purvis John E Burkhalter and Brent D N78-20091| Imperial Coll of Science and Technology London Martin Eghn AFB Fla AFAL Sep 1977 62 p refs (England) Dept of Aeronautics (Contract F08635-77-C-0002) ENGINEERING CALCULATION METHODS FOR TUR- (AD-A050267 AFATL-TR-77-112) Avail NTIS BULENT FLOW. VOLUME 1 HC A04/MF A01 CSCL 20/4 P Bradshaw. T Cebeci (Douglas Aircraft Comp Long Beach Analytical approaches are considered which might be used Calif) and J H Whitelaw Sep 1977 123 p refs 3 Vol to improve and extend current aerodynamic analysis to include HC-Aero-77-102-Vol-l) Avail NTIS HC A06/MF A01 the compressibility effects up to and including critical Mach Lecture notes for a short post-experience course held in numbers The Rayleigh-Janzen solution is considered for both October 1977 are presented The 16 lectures are intended as a small disturbance and exact potential flows A simple numerical general review of the state-of-the-art of designers and research method is presented and compared with both experimental results workers in aerospace mechanical and civil engineering and the and the results of other analytical methods for potential flow environmental sciences The lectures consider turbulence Author (GRA) phenomena exact equations empirical turbulence models numerical procedures and applications The 5 lectures in this volume following an introduction, deal with conservation N78-20066)P Avco Systems Div Wilmington Mass equations and boundary conditions for 2-D incompressible flow HYPERSONIC HEAT TRANSFER TEST PROGRAM IN THE zero-equation, 2-equation stress models, stress-equation modeling VKI LONGSHOT FACILITY Final Report. 1 Nov 1976 - and scalar models, introductory numerical methods for thin shear 31 Oct 1977 layer equations and their boundary and initial conditions and V DiCristma 21 Dec 1977 33 p inviscid/viscid interactions Author (ESA) (Contract F49620-77-C-0035 Grant AFOSR-2942-76) (AD-A050295 AVSD-0393-77-CR AFOSR-78-0111TR) Avail N78-20092# Imperial Coll of Science and Technology. London NTIS HC A03/MF ACM CSCL 20/4 (England) Dept of Aeronautics The purpose of these tests was to measure local pressure ENGINEERING CALCULATION METHODS FOR TUR- and heat transfer distributions on an ogive body configuration BULENT FLOW. VOLUME 2 over a range of Mach number and Reynolds number conditions P Bradshaw T Cebeci (Douglas Aircraft Comp Long Beach Both smooth and rough body data were obtained at three degrees Calif) and J H Whitelaw Sep 1977 104 p refs 3 Vol angle of attack Author (GRA) (IC-Aero-77-102-Vol-2) Avail NTIS HC A06/MF AO1

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Lecture notes for a short post-experience course held in The purpose of the study was to examine the time interval October 1977 are presented The 16 lectures are intended as a and associated discounted program costs of a government general review of the state-of-the-art of designers and research sponsored convertible aircraft Through the use of a computer workers in aerospace, mechanica) and civil engineering, and the model, the researchers examined the relationship of deflated Gross environmental sciences The lectures consider turbulence National Product growth, historical air commerce trends and phenomena exact equations empirical turbulence models simulated changes in the composition of the U S air carrier numerical procedures, and applications In this volume 6 lectures fleet resulting from the demand for air transportation Further, are collected on corner flows and slender shear layers recirculating the study examined the impact of wide-bodied aircraft lower flows, laser-Doppler anemometry, hot-wire anemometry standard hold cargo capability on attaining 100 wide-bodied cargo capable boundary layer problems for external 2-D and axisymmetric flows, aircraft by 1990 as well as reimbursement by airlines for initial and inverse boundary layer problems Author (ESA) government sponsorship costs when convertible aircraft are transitioned to a freighter mode GRA N78-2OO93# Imperial Coll of Science and Technology London (England) Dept of Aeronautics ENGINEERING CALCULATION METHODS FOR TUR- N78-20O98*# National Aeronautics and Space Administration BULENT FLOW. VOLUME 3 Ames Research Center Moffett Field Calif P Bradshaw, T Cebeci (Douglas Aircraft Comp, Long Beach FLIGHT TEST RESULTS OF THE STRAPDOWN HEX AD Calif), and J H Whitelaw Sep 1977 100 p refs 3 Vol INERTIAL REFERENCE UNIT (SIRU) VOLUME 3' AP- (IC-Aero-77-102-Vol-3) Avail NTIS HC A05/MF A01 PENDICES A-G Lecture notes for a short post-experience course held in Ronald J Hruby and William S Bjorkman (Analytical Mechanics October 1977 are presented The 16 lectures are intended as a Associates Inc Mountain View Calif) Jul 1977 104 p general review of the state-of-the-art of designers and research (NASA-TM-73224 A-6974) Avail NTIS HC A06/MF A01 workers in aerospace, mechanical and civil engineering, and the CSCL 17G environmental sciences The lectures consider turbulence Results of flight tests of the Strapdown Inertial Reference Unit phenomena exact equations empirical turbulence models (SIRU) navigation system are presented The fault tolerant SIRU numerical procedures and applications In this volume 4 lectures navigation system features a redundant inertial sensor unit and are presented on calculation of 2-D unsteady and 3-D steady dual computers System software provides for detection and flows stability and transition turbomachmery, and combustion isolation of inertial sensor failures and continued operation in Author (ESA) the event of failures Flight test results include assessments of the systems navigational performance and fault tolerance Selected facets of the flight tests are also described in detail N78-20O94*# American Airlines Inc , Tulsa Okla Maintenance and include some of the following (1) flight test plans and and Engineering Center ground track plots (2) navigation residual plots (3) effects of A NEW METHOD FOR ESTIMATING CURRENT AND approximations in navigation algorithms (4) vibration spectrum FUTURE TRANSPORT AIRCRAFT OPERATING ECONOM- of the CV-340 aircraft, and (5) modification of the statistical ICS Contractor Report. Jan. 1976 - Oct 1977 FDICR algorithm parameters for the flight environment Author Mar 1978 278 p refs Revised (Contract NAS1-14284) (NASA-CR-145190. D6-42877-Rev) Avail NTIS HC A13/MF A01 CSCL 05C A methodology was developed by which the operating cost N78-20099jj' Electromagnetic Compatibility Analysis Center associated with variations in aircraft design and technology Annapolis Md characteristics can be assessed The assessment method produced THE IMPACT OF A PROPOSED ACTIVE BCAS ON ATCRBS a base line estimate of the operating cost elements relating to PERFORMANCE IN THE WASHINGTON. D C. 1981 such design specification features as seat capacity avionic ENVIRONMENT Final Report equipment design range and design definition features such as Norman Theberge (ITT Res Inst Annapolis) Sep 1977 49 p maximum takeoff gross weight and number of engines The (Contract DOT-FA70WAI-175) methodology was applied to assess the operating cost of one (AD-A048589/6, ECAC-PR-77-037. FAA-RD-77-140) Avail potential future advanced technology transport aircraft An analysis NTIS HC A03/MF A01 CSCL 17/7 was included to show the relative sensitivity of the operating A computer model of the proposed active Beacon .Collision cost to design parameters Author Avoidance System (BCAS) was developed to investigate the impact of BCAS on the Air Traffic Control Radar Beacon System (ATCRBS) ground system Predictions were made for the early N78-20095| Air Force Civil Engineering Center Tyndall AFB 1981 Washington DC environment Two ground environments Fla were simulated, an all-ATCRBS environment and a 25%/75% AN EVALUATION OF THE BIRD/AIRCRAFT STRIKE Discrete Address Beacon System (DABS)/ATCRBS mix Airborne HAZARD. MALMSTROM AFB. MONTANA fruit rates and the effect of BCAS/DABS mode power program- Larry T Clark and Richard D Smedley. Jr Sep 1977 21 p ming on interference were also predicted Author refs (AD-A049637 AFCEC-M-9-77) Avail NTIS N78-20100*# Ohio Univ Athens Avionics Engineering HC A02/MF A01 CSCL 01/2 Center The bird/aircraft strike hazard (BASH) at Malmstrom Air STAND-ALONE DEVELOPMENT SYSTEM USING A KIM 1 Force Base. Montana, was surveyed during the period 26 MICROCOMPUTER MODULE August-2 September 1977 Special emphasis was placed on local James D Nickum Mar 1978 13 p refs gull activities which contribute significantly to the bird strike (Grant NGR-36-009-017) potential Recommendations aimed at reducing the airfield bird (NASA-CR-156067. NASA-TM-56) Avail NTIS strike potential are part of this report Author (GRA) HC A02/MF A01 CSCL 17G A small microprocessor-based system designed to contain N78-20096# Air Force Inst of Tech . Wright-Patterson AFB all or most of the interface hardware designed to be easy to Ohio Graduate Education Div access and modify the hardware to be capable of being strapped AN ECONOMIC ANALYSIS OF A GOVERNMENT SPON- to the seat of a small general aviation aircraft, and to be SORED. COMMERCIAL CONVERTIBLE AIRCRAFT independent of the aircraft power system is described The system MS Thesis is used to develop a low cost Loran C sensor processor but is Robert J Morgan and Stanley L Mead Sep 1977 236 p designed such that the Loran interface boards may be removed refs and other hardware interfaces inserted into the same connectors (AD-A047633 AFIT-LSSR-21-77B) Avail NTIS This flexibility is achieved through memory-mapping techniques HC A11/MF A01 CSCL 01/3 into the microprocessor Author

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N78-20101# Electromagnetic Compatibility Analysis Center as an essential part a collision protection system integrated Annapolis Md into the flight safety system This system autonomously recognizes INTERFERENCE ANALYSIS BETWEEN TRSB MICROWAVE collision hazards and calculates avoidance maneuvers taking into LANDING SYSTEM AND ADJACENT C-BAND RADARS account the flight safety situation occurring ESA Final Report Ved Nanda (ITT Res Inst Annapolis) Jan 1978 66 p (Contracts DOT-FA70WAI-175 F19628-76-C-0017 AF Pro) 649E) (AD-A049882 ECAC-PR-76-004 FAA-R D-77-1 10) Avail N78-20105 Techmsche Universitaet. Brunswick (West Germany) NTIS HC A04/MF A01 CSCL 01/5 PROGRAM FOR SIMULATION OF AIR TRAFFIC AND AIR The electromagnetic compatibility between the Time Refer- SPACE STRUCTURE OF THE FRANKFURT NEAR RANGE. ence Scanning Beam (TRSB) Microwave Landing System (MLS) A PLANNING CONTROL AND A COLLISION AVOIDANCE and adjacent C-band radar systems is investigated Distance SYSTEM WITH SITUATION DEPENDENT AVOIDANCE constraints required for compatible operation between these MANEUVERS [PROGRAMM ZUR SIMULATION DES systems were established for the three proposed MLS plans of LUFTVERKEHRS UND DER LUFTRAUMSTRUKTUR DES frequency assignment Author NAHBEREICHES FRANKFURT. EINER PLANUNGSKON- TROLLE UND EINES KOLUSIONSSCHUTZSYSTEMS MIT N78-20102*# Boeing Commercial Airplane Co Seattle Wash SITUATIONSBEDINGTEN AUSWEICHMANOEVER] COCKPIT DISPLAYED TRAFFIC INFORMATION STUDY. D Brunner In its Air Traffic Safety in the Airport Near Range PART 2 Mar 1977 p 23-53 In GERMAN Sep 1977 250 p refs Sponsored in part by FAA (Contract NAS1-13267) Avail NTIS HC A06/MF A01 (NASA-CR-156115 AD-A049870 D6-42968-PI-2 The computerized simulation of a flight safety system in an FAA-EM-77-18-Pt-2) Avail NTIS HC A11/MF A01 CSCL airport near range is discussed The underlying concept is based 01/5 on the present manual flight safety control of the intensively The planning base for conducting a flight test evaluation of used Frankfurt near range and comprises further developments an Electronic Horizontal Situation Indicator (EHSI) incorporating combining intricate control navigation and collision avoidance the position of other air traffic as derived from ground sensors The air traffic simulation covers both simulation of traffic in the was provided A system concept for an airborne information near range and components of the flight safety system mentioned display utilizing ground derived ATC and ATC related information The Frankfurt near range air space was selected in order to was defined and an outline of a simulation and flight test program permit comparison of real traffic with that simulated ESA which includes the NASA 515 aircraft the Langley Research Center traffic simulation and other aircraft and simulations were prepared Testing m a busy terminal area was also planned N78-20106 Techmsche Universitaet Brunswick (West Germany) Author DEVELOPMENT OF A BINARY FREQUENCY SYNTHESIS AS CONTROL ELEMENT FOR FREQUENCY CORRECTION IN TIME-SYNCHRONOUS COLLISION SYSTEMS WITHOUT N78-20103# Techmsche Universitaet, Brunswick (West ONBOARD ATOMIC FREQUENCY STANDARD AVOIDANCE Germany) Sonderforschungsbereich 58 Flugfuehrung [ENTWICKLUNG EINER BINAEREN FREQUENZSYNTHESE AIR TRAFFIC SAFETY IN THE AIRPORT NEAR RANGE ALS STELLGUED ZUR FREQUENZKORREKTUR IN ZEIT- [BEITRAEGE ZUR VERKEHRSSICHERUNG IM FLUGHAFEN- SYNCHRONEN KOLLISIONSSCHUTZSYSTEMEN OHNE NAHBEREICH] ATOMFREQUENZNORMAL AN BORD] Mar 1977 106 p refs In GERMAN P Plumeyer In its Air Traffic Safety in the Airport Near Range (TUBS/SFB58/M4) Avail NTIS HC A06/MF A01 Mar 1977 p 54-70 In GERMAN Topics in the field of airport near range air traffic safety are presented The computerized simulation of a flight safety Avail NTIS HC A06/MF A01 system for the near range is discussed, covering air traffic, The design of a frequency synthesizer for a quartz oscillator control, navigation and collision avoidance The design of a is reported to provide an onboard frequency standard in a frequency synthesizer for a quartz oscillator, to provide an onboard time-synchronous collision avoidance system The frequency frequency standard in a time-synchronous collision avoidance synthesis is binary controlled and allows correction of the quartz system is reported A model is described which was developed frequency The synthesis circuit satisfies two conditions high for representing the statistical selection and distance measurement spectral cleanliness of the output signal, and a fast response for process in the nonsynchronous SECANT collision avoidance commutation of the correction signal The combination of these system conditions was facilitated by the elaboration of optimal frequency plans for the individual circuit stages, allowing separation of signal and noise bounds by using relatively broadband filters ESA

N78-201O4 Techmsche Universitaet Brunswick (West Germany) N78-20107 Techmsche Universitaet, Brunswick (West Germany) SIMULATION AND DEVELOPMENT POSSIBILITIES OF THE DESIGN OF A COLLISION AVOIDANCE SYSTEM MODEL MANUAL CONTROL CONCEPT IN THE NEAR RANGE AND WITH STATISTICAL INTERROGATION [AUFBAU EINES CONTROL ZONE [UEBER DIE SIMULATION UND DIE MODELLS EINES KOLUSIONSSCHUTZSYSTEMS MIT ENTWICKLUNGSMOEGUCHKEITEN DES MANUELLEN STATISTISCHER ABFRAGE] KONTROLLKONZEPTES IN NAHVERKERHSBEREICH UND P Form. P Plumeyer and H -R Boecker In its Air Traffic KONTROLLZONE] Safety in the Airport Near Range Mar 1977 p 71-103 In D Brunner In its Air Traffic Safety in the Airport Near Range GERMAN Mar 1977 p 3-22 refs In GERMAN Avail NTIS HC A06/MF A01 A model was developed to represent the statistical selec- Avail NTIS HC A06/MF A01 tion and distance measurement processes in the nonsynchronous Possibilities for improving flight safety in the near range by SECANT collision avoidances system The relation, between traffic a stepwise tighter combination of flight safety control, navigation, density, warning time, and response range are analyzed The and collision avoidance were investigated The current short effect of two correlation modes on interference pulse rates is range traffic was reproduced by simulation of air space structure demonstrated A calculation is presented of the statistical air traffic, and manual control The effects of some control processes in the correlators, the most important result of which measures were examined and a system concept for safety and is the determination of the distribution function for readings of guidance of air traffic was developed The simulation comprises. the correlator counters ESA

304 N78-20114

N78-20108*# National Aeronautics and Space Administration Han Eijsmk and Mark Rice Apr 1978 165 p refs 2 Vol Langley Research Center Langley Station Va (Grant NsG-1421) TECHNICAL AND ECONOMIC EVALUATION OF AD- (NASA-CR-156143. KU-FRL-351-Pt-B) Avail NTIS VANCED AIR CARGO SYSTEMS HC A08/MF A01 CSCL 01C Allen H Whitehead. Jr Feb 1978 38 p refs Presented at Computer programs written in FORTRAN are given for time Forum on Airfreight Contribution in Securing Markets Abroad response calculations on pneumatic and linear hydraulic actuators Aeroport de Pans, France. 17-18 Nov 1977 The programs are self-explanatory with comment statements (NASA-TM-78672) Avail NTIS HC A03/MF A01 CSCL01C Program output is also included Author The current air cargo environment and the relevance of advanced technology aircraft in enhancing the efficiency of the N78-20112*| Boeing Commercial Airplane Co. Seattle. Wash 1990 air cargo system are discussed NASA preliminary design Preliminary Design Dept studies are shown to indicate significant potential gains in aircraft STUDY OF ADVANCED COMPOSITE STRUCTURAL efficiency and operational economics for future freighter concepts DESIGN CONCEPTS FOR AN ARROW WING SUPERSONIC Required research and technology elements are outlined to develop CRUISE CONFIGURATION, TASK 3 Final Report a better base for evaluating advanced design concepts Current Jan 1978 381 p refs studies of the market operation are reviewed which will develop (Contract NAS1-12287) design criteria for a future dedicated cargo transport Design (NASA-CR-145192. D6-42438-4) Avail NTIS features desirable in an all-freighter design are reviewed HC A17/MF A01 CSCL01C NASA-sponsored studies of large, distributed-load freighters are A structural design study was conducted to assess the relative reviewed and these designs are compared to current wide-body merits of structural concepts using advanced composite materials aircraft These concepts vary in gross takeoff weight from 0 5 Gg for an advanced supersonic aircraft cruising at Mach 2 7 The (one million Ibs) to 1 5 Gg (three million Ibs) and are found to configuration and structural arrangement developed during exhibit economic advantages over conventional design concepts Task I and II of the study was used as the baseline configuration Author Allowable stresses and strains were established for boron and advanced graphite fibers based on projected fiber properties available in the next decade Structural concepts were designed N78-20109*$ Michigan Univ . Ann Arbor Dept of Aerospace and analyzed using graphite polyimide and boron polyimide, Engineering applied to stiffened panels and conventional sandwich panels AEROELASTIC ANALYSIS AND GROUND VIBRATION The conventional sandwich panels were selected as the structural SURVEY OF THE NASA. GRUMMAN AMERICAN YANKEE concept to be used on the wing structure The upp°r and lower MODIFIED FOR SPIN TESTING Final Report. 7 Aug. surface panels of the Task I arrow wing were redesigned using 1976 - 30 Jun. 1977 high-strength graphite polyimide sandwich panels over the Richard A Kroeger Sep 1977 263 p refs titanium spars and ribs The ATLAS computer system was used (Grant NsG-1229) as the basis for stress analysis and resizing the surface panels (NASA-CR-156119) Avail NTIS HC A12/MF A01 CSCL using the loads from the Task II study without adjustment for 01C change in aeroelastic deformation The flutter analysis indicated A complete ground vibration and aeroelastic analysis was a decrease m the flutter speed compared to the baseline titanium made of a modified version of the Grumman American Yankee wing design The flutter analysis indicated a decrease in the The aircraft had been modified for four empennage configurations flutter speed compared to the baseline titanium wing design a wing boom was added, a spin chute installed and provisions The flutter speed was increased to that of the titanium wing, included for large masses in the wing tip to vary the lateral and with a weight penalty less than that of the metallic airplane directional inertia Other minor changes were made which have Author much less influence on the flutter and vibrations Neither static divergence nor aileron reversal was considered since the wing structure was not sufficiently changed to affect its static aeroelastic qualities The aircraft was found to be free from N7S-20113*||I National Aeronautics and Space Administration flutter m all of the normal modes explored in the ground shake Ames Research Center, Moffett Field, Calif test The analysis demonstrated freedom from flutter up to 214 A SIMPLE METHOD FOR ESTIMATING MINIMUM AUTO- miles per hour Author ROTATIVE DESCENT RATE OF SINGLE ROTOR HELICOP- TERS N78-20110*(C Kansas Univ Center for Research. Inc . Lawrence Peter D Talbot and Laurel G Schroers (Army R & T Labs A STUDY OF LOW-COST RELIABLE ACTUATORS FOR Moffett Field Calif) Mar 1978 17 p refs LIGHT AIRCRAFT PART A CHAPTERS 1-8 Final Report. (NASA-TM-78452. A-7134) Avail NTIS HC A02/MF A01 15 Jun 1977 - 15 Mar 1978 CSCL 01C Han Eijsmk and Mark Rice Apr 1978 162 p refs 2 Vol Flight test results of minimum autorotative descent rate are (Grant NsG-1421) compared with calculations based on the minimum power required (NASA-CR-156142) Avail NTIS HC A08/MF A01 CSCL for steady level flight Empirical correction factors are derived 01C that account for differences in energy dissipation between these An analysis involving electro-mechanical, electro-pneumatic, two flight conditions A method is also presented for estimating and electro-hydraulic actuators was performed to study which the minimum power coefficient for level flight for any helicopter are compatible for use in the primary and secondary flight controls for use in the empirical estimation procedure of autorotative of a single engine light aircraft Actuator characteristics under descent rate Author investigation include cost reliability weight force volumetric requirements, power requirements, response characteristics and N78-2O114*/C National Aeronautics and Space Administration heat accumulation characteristics The basic types of actuators Hugh L. Dryden Flight Research Center Edwards Calif were compared for performance characteristics in positioning a DEVELOPMENT OF SYSTEMS AND TECHNIQUES FOR control surface model and then were mathematically evaluated LANDING AN AIRCRAFT USING ONBOARD TELEVISION in an aircraft to get the closed loop dynamic response characteris- Shu W Gee Peter C Carr. William R Winter, and John A tics Conclusions were made as to the suitability of each actuator Manke Feb 1978 24 p refs type for use in an aircraft Author (NASA-TP-1171 H-9731 Avail NTIS HC A02/MF A01 CSCL QIC A flight program was conducted to develop a landing technique with which a pilot could consistently and safely land a remotely piloted research vehicle (RPRV) without outside visual N78-20111*# Kansas Univ Center for Research, Inc, Lawrence reference except through television Otherwise, instrumentation A STUDY OF LOW-COST RELIABLE ACTUATORS FOR was standard Such factors as the selection of video parameters, LIGHT AIRCRAFT PART B: APPENDICES Final Report the pilot s understanding of the television presentation, the pilqfs

305 N78-20115 ground cockpit environment, and the operational procedures for G W Kibbee Apr 1978 106 p refs landing were considered About 30 landings were necessary for (Contract NAS1-13981) a pilot to become sufficiently familiar and competent with the (NASA-CR-2970 MDC-J7727) Avail NTIS HC A06/MF A01 test aircraft to make powered approaches and landings with CSCL 01 C outside visual references only through television When steep The development, evaluation, and evaluation results of a approaches and landings were made by remote control the pilot s DC-9-10 runway directional control simulator are described An workload was extremely high The test aircraft was used as a existing wide bodied flight simulator was modified to this aircraft simulator for the F-15 RPRV, and as such was considered to configuration The simulator was structured to use either of two be essential to the success of landing the F-15 RPRV Author antiskid simulations (1) an analog mechanization that used aircraft hardware, or (2) a digital software simulation After the N7S-20116*f National Aeronautics and Space Administration simulation was developed it was evaluated by 14 pilots who Langley Research Center, Langley Station Va made 818 simulated flights These evaluations involved landings GROUND DISTANCE COVERED DURING AIRBORNE rejected takeoffs and various ground maneuvers Qualitatively HORIZONTAL DECELERATION OF AN AIRPLANE most pilots evaluated the simulator as realistic with good potential William H Phillips Apr 1978 13 p refs especially for pilot training for adverse runway conditions Author (NASA-TP-1157 L-12008) Avail NTIS HC A02/MF A01 CSCL 01C N78-20119# Air Force Flight Dynamics Lab. Wright-Patterson The distance an airplane floats with respect to the ground AFB. Ohio during deceleration at constant altitude is analyzed taking into PRESSURE CYCLING FATIGUE TESTS OF F 111 CREW account the effects of a constant wind By use of suitable MODULE GLASS TRANSPARENCIES Final Report. 1 Jun nondimensionalizing parameters data applicable to all airplanes 1969 - 1 Jun 1971 are presented by means of a single family of curves Author George R Holderby Mar 1977 49 p (AD-A049625 AFFDL-TR-77-12) Avail NTIS HC A03/MF A01 CSCL 01/3 The F-111 Crew Module Transparencies Fatigue Test Program N78-20116*)C Boeing Commercial Airplane Co Seattle. Wash was initiated to resolve questions on the effects of complete STUDY OF ADVANCED COMPOSITE STRUCTURAL pressure reversals combined with thermal cycling on the fatigue DESIGN CONCEPTS FOR AN ARROW WING SUPERSONIC life of the transparencies A ship-set of transparencies was CRUISE CONFIGURATION Final Report mounted in a crew escape module and subjected to a simulated M J Turner and D L Grande Apr. 1978 122 p refs flight heating, cooling and pressure environment The test (Contract NAS1-12287) specimens successfully completed four lifetimes of testing and (NASA-CR-2825, D6-42438-5) Avail NTIS HC A06/MF A01 had residual static strength in excess of the design ultimate CSCL 01C load of the escape module An ambient temperature fatigue test Based on estimated graphite and boron fiber properties, was added to the program to investigate the propagation allowable stresses and strains were established for advanced characteristics of debonded areas in the transparency edge composite materials Stiffened panel and conventional sandwich members which were occurring in service A ship-set of panel concepts were designed and analyzed using graphite/ transparencies with debonded areas large enough to require polyimide and boron/polyimide materials The conventional sandwich panel was elected as the structural concept for the replacement under applicable technical orders was mounted in modified wing structure Upper and lower surface panels of the an escape module and subjected to simulated subsonic flight arrow wing structure were then redesigned, using high strength usage The test specimens successfully completed four life times graphtte/polyimide sandwich panels retaining the titanium spars of testing with no failures of the glass and only very small and ribs from the prior study The ATLAS integrated analysis growth of some of the debonded areas Author (GRA) and design system was used for stress analysis and automated resizing of surface panels Flutter analysis of the hybrid structure showed a significant decrease in flutter speed relative to the titanium wing design The flutter speed was increased to N78-20120# Brooks and Perkins Inc Livonia Mich that of the titanium design by selective increase in laminate GONDOLA SYSTEM FOR HELICOPTER TRANSPORT OF thickness and by using graphite fibers with properties intermedi- EXTERNAL CARGO Final Report. Now 1975 - Jun 1977 ate between high strength and high modulus values Author Sep 1977 41 p refs (Contract DAAJ02-76-C-0007) (AD-A047560, USAAMRDL-TR-77-28) Avail NTIS N78-20117*# McDonnell-Douglas Corp St Louis. Mo HC A03/MF A01 CSCL 15/5 THERMAL DESIGN FOR AREAS OF INTERFERENCE This report covers the design the development and the HEATING ON ACTIVELY COOLED HYPERSONIC AIRCRAFT static testing of 8x8x10- and 20-foot gondolas The technical Final Report feasibility and performance data provided will permit further study R L Herring and J E Stone Jan 1978 169 p refs of the transportation of these systems by helicopter The maximum (Contract NAS1-14140) gross weights of the 10- and 20-foot units are 15,000 and (NASA-CR-2828) Avail NTIS HC A08/MF A01 CSCL 01C Numerous actively cooled panel design alternatives for 30 000 pounds respectively The structure has a rigid porous floor, an open superstructure and I SO corner fittings It is designed application in regions on high speed aircraft that are subject to to be acquired and released by container handling devices or interference heating effects were studied Candidate design handled by forklifts The gondola system is intermodal and consists concepts were evaluated using mass producibility reliability and of a basic center unit (8x8x20 feet ) and two end units mspectability/maintainability as figures of merit Three design (8x8x10 feet) that are all modules that can be coupled to approaches were identified as superior within certain regimes of make 8x8x40-foot and 8x8x20-foot assemblies Author (GRA) the matrix of design heating conditions considered Only minor modifications to basic actively cooled panel design are required to withstand minor interference heating effects Designs incorporating internally finned coolant tubes to augment heat transfer are recommended for moderate design heating conditions N78-20121# Boeing Vertol Co Philadelphia Pa At severe heating conditions an insulated panel concept is LIMITATIONS OF THE UTTAS HELICOPTER IN PERFORM- required Author ING TERRAIN FLYING WITH EXTERNAL LOADS Final Report. Jul 1976 - Apr 1977 Irvm B Alansky James M Davis and Theodore S Garnett. Jr N78-20118"# Douglas Aircraft Co Inc Long Beach. Calif Sep 1977 113 p refs EXPANSION OF FLIGHT SIMULATOR CAPABILITY FOR (Contract DAAJ02-76-C-0027) STUDY AND SOLUTION OF AIRCRAFT DIRECTIONAL (AD-A047568 D210-11226-1 USAAMRDL-TR-77-22) Avail CONTROL PROBLEMS ON RUNWAYS Final Report NTIS HC A06/MF A01 CSCL 01/2

306 N78-20128

Quantitative limitations of the UTTAS helicopter performing N78-20124| United Technologies Corp Stratford Conn terrain flying with external loads have been developed using a Sikorsky Aircraft Div fully coupled total force and moment simulation math model of HELICOPTER FREEWHEEL UNIT DESIGN GUIDE the helicopter and external load Load sway motion and Final Report. 1974 - Mar 1977 susceptibility to PIO in night/instrument meteorological conditions J Kish Oct 1977 239 p refs were identified as the prime source of these limitations Masking (Contract DAAJ02-74-C-0028) requirements were determined for various external load configura- (AD-A047559. USAAMRDL-TR-77-18) Avail NTIS tions including a 105mm howitzer and an A-22 ammo bag HC A11/MF A01 CSCL 01/3 Incorporation of a dual hook suspension or load stabilization This report is intended to aid the transmission designer in coupled with a shortened sling suspension offers the best selecting an overrunning clutch for use in a helicopter transmission potential for alleviating the limits identified, while providing Preliminary sizing as well as detailed stress analysis procedures improved masking requirements and reduction in pilot workload are presented for all aspects of spring, sprag, and ramp roller In addition, the levels of maneuverability possible with the present clutch designs An example of the procedure for each clutch is state-of-the-art visionic systems (including FUR and NVG). were included Operation up to 20 000 rpm is feasible if the design defined for terrain flying during night operations Author (GRA) procedures presented herein are followed Author (GRA)

N78-20122# Kaman Avidyne, Burlington Mass N78-20125# Naval Postgraduate School Monterey Calif CORRELATION STUDY OF THE UH-18 HEUCOPTER BLAST THE FEASIBILITY OF THE JET-FLAP ROTOR AS A LIFT TEST RESULTS FROM THE DICE-THROW EVENT Final GENERATOR FOR VERTICAL TAKEOFF AND LANDING Report. 1 Oct 1970-31 M.y 1977 AIRCRAFT M S Thesis Garabed Zartanan. Eldme L Cole, and William N Lee 1977 John Charles Ball Dec 1977 134 p refs 222 p refs (AD-A050214) Avail NTIS HC A07/MF A01 CSCL 01/3 (Contract DAAD05-76-C-0772) The objectives of this study were first to determine the (AD-A050463 KA-TR-138, BRL-352) Avail NTIS effectiveness of the jet-flap rotor relative to other lift generators HC A10/MF A01 CSCL 01/3 and second to examine the potential effectiveness of the This report summarizes the results of a correlation study jet-flap rotor in a tactical VTOL aircraft It was found that the conducted in conjunction with the UH-1B helicopter blast test jet-flap rotor has a high theoretical potential, but at present is during the DICE THROW event The processed structural and the least-developed of the lift generators considered The jet-flap motion response data from the hovering and droned helicopter rotor was found to be unattractive as a means of providing are presented They are correlated with corresponding analytical vertical lift except when a long hover duration is necessary predictions based primarily on the helicopter code HELP and With regard to weight considerations alone the jet-flap rotor the aircraft structural code NOVA-2 The monitored blast-induced was found to be inadvisable for use in a tactical VTOL aircraft responses include 11) the flapwise bending moments and the However, its benign downwash characteristics could make the flapping angles of both the tail and main rotor blade systems, jet-flap rotor advantageous if high downwash velocities and (2) the lateral bending moments at two fin and two tail boom temperatures could not be tolerated Author (GRA) stations (3) the overall rigid-body motions of the vehicle consisting of the altitude variations, the attitude and angular N78-20127| Dormer-System GmbH Friednchshafen (West rate variations in the yaw, pitch, and roll degrees-of-freedom, Germany) and (4) the strains at selected points on a tail boom panel, a MODERN WING TECHNOLOGY FOR GENERAL AVIATION stiffener and a longeron Considering the qualities of the available AIRCRAFT Final Report input data for the analyses and of the measurements the M Lotz, B Hummk W Haberland E Hoffmann, and W Staeudlm experimental results are generally in reasonable agreement with Bonn Bundesmin fuer Forsch u Techno! Nov 1977 135 p the predictions from the HELP code The NOVA-2 predictions refs In GERMAN ENGLISH summary for panel stiffener, and longeron strains fare poorly when compared (Contract BMFT-LFK-7530) with experiment In some instances significant differences are (BMFT-FB-W-77-14) Avail NTIS HC A07/MF A01. 2LDI found between experiment and analysis Whenever possible, the Munich DM 28.35 reasons for the disagreements are identified and discussed The design and construction of a wing of modern technology Author (GRA) (MWT) for general aviation aircraft is reported as well as testing of this wing on a modified Dormer Skyservant The results of N78-20123| Bell Helicopter Co. Fort Worth. Tex investigations of aerodynamic and structural design and trade-off AH-1S HIGH SURVIVABLE TRANSMISSION SYSTEM concerning the application of the MWT on general aviation aircraft Final Report. Oct. 1975 - Aug. 1977 are presented The aerodynamic design of the test-wing shows David J Richardson Oct 1977 143 p refs the clear superiority of the MWT wing section compared to (Contract DAAJ02-76-C-0006. DA Proj 1F2-63208-DB-52) conventional NACA-wing sections mainly with regard to maximum (AD-A047558, BHT-699-099-059, USAAMRDL-TR-77-30) lift and L/D at high lift coefficients Wind tunnel investigations, Avail NTIS HC A07/MF A01 CSCL 01/3 made with the complete experimental model aircraft, partly The objective of the work performed on this program was exceeded theoretical expectations The result of the flight to demonstrate that the AH-IS main transmission system modified mechanics investigations shows that in comparison with the with internal component improvements but without an emergency original Skyservant version, limitations of the flight-envelope will lubrication system could operate for 30 minutes following the be necessary because of the modified wing, more powerful loss of lubrication The internal component improvements were engines and the use of the original empennage The effect of based upon work done under a previous Eustis Directorate program applying MWT to general aviation aircraft was demonstrated on conducted by Bell Helicopter Textron Four different, modified two basic production aircraft Results showed remarkable versions of the AH-IS transmission configuration were tested improvements of flight and mission performance (take-off run, under this program All loss-of-lube testing was conducted at climb, and range), relatively small improvements in initial costs 950 input horsepower (84 percent of maximum continuous power and an obvious reduction of direct operational costs rating of the AH-1S) and 6600 input rpm The first transmission Author (ESA) configuration tested ran 7 minutes under loss-of-lube conditions before failure of the main input spiral bevel pinion occurred N78-20128*# National Aeronautics and Space Administration The second transmission configuration ran 21 minutes before Langley Research Center Langley Station Va the lower planetary stage failed The third transmission configura- A ROTOR-MOUNTED DIGITAL INSTRUMENTATION tion ran 19 minutes before a lower planetary stage failure occurred •YCTEM FOR HELICOPTER BLADE FLIGHT RESEARCH The fourth transmission configuration ran 26 5 minutes before MEASUREMENTS again a lower planetary stage failure occurred It appears that Vernie H Knight. Jr. William S Haywood. Jr and Milton L a 30-mmute loss-of-lube capability has been achieved for all Williams Apr 1978 49 p refs transmission components except the lower planetary stage (NASA-TP-1146. L-11956) Avail NTIS HC A03/MF A01 Author (GRA) CSCL 01D

307 N78-20130

A rotor mounted flight instrumentation system developed Herman W Prust, Jr Apr 1978 23 p refs for helicopter rotor blade research is described The system (NASA-TP-1204 E-9342) Avail NTIS HC A02/MF A01 CSCL utilizes high speed digital techniques to acquire research data 21E from miniature pressure transducers on advanced rotor airfoils Published experimental aerodynamic efficiency results were which are flight tested on an AH-1G helicopter The system compared with results predicted from two published analytical employs microelectronic pulse code modulation (PCM) multiplexer methods This is the second of two such comparisons One of digitizer stations located remotely on the blade and in a hub the analytical methods was used as published, the other was mounted metal canister As many as 25 sensors can be remotely modified for certain cases of coolant discharge from the blade digitized by a 2 5 mm thick electronics package mounted on suction surface The results show that for 23 cases of single the blade near the tip to reduce blade wiring The electronics row and multirow discharge covering coolant fractions from 0 contained in the canister digitizes up to 16 sensors, formats to about 9 percent the difference between the experimental these data with serial PCM data from the remote stations and and predicted results was no greater than about 1 percent in transmits the data from the canister which is above the plane any case and less than 1/2 percent in most cases Author of the rotor Data are transmitted over an RF link to the ground for real time monitoring and to the helicopter fuselage for tape N78-20134# Naval Air Propulsion Test Center, Trenton, NJ recording The complete system is powered by batteries located EFFECTIVENESS OF THE REAL TIME FERROGRAPH AND in the canister and requires no slip rings on the rotor shaft OTHER OIL MONITORS AS RELATED TO OIL FILTRA- Author TION N78-20130*# National Aeronautics and Space Administration Daniel Popgoshev and Raymond Valon Nov 1977 69 p refs Lewis Research Center Cleveland, Ohio (AD-A049334 NAPC-PE-2) Avail NTIS HC A04/MF A01 TWO-DIMENSIONAL COLD-AIR CASCADE STUDY OF A CSCL 11/8 FILM-COOLED TURBINE STATOR BLADE 4 COMPAR- A development model of an oil monitor known as the Real ISON OF EXPERIMENTAL AND ANALYTICAL AERODY- Time (RT) Ferrograph was evaluated on a bench tester to NAMIC RESULTS FOR BLADE WITH 12 ROWS OF determine its effectiveness m detecting rolling contact fatigue or 0076-CENTIMETER-(0 030-INCH-) DIAMETER HOLES scoring type failures, especially as influenced by various levels HAVING STREAMWISE EJECTION ANGLES of oil filtration Comparisons of the R T Ferrograph are made Herman W Prust, Jr Mar 1978 30 p refs with spectrometnc oil analysis a light scattering and attenuation (NASA-TP-1151 E-9187) Avail NTIS HCA03/MFA01 CSCL device an X-ray fluorescence device a particle counter and the 21E analytical Ferrograph Results of the testing showed the R T Previously published experimental aerodynamic efficiency Ferrograph to be effective in detecting failures when the oil results for a film cooled turbine stator blade are compared with filtration level was above 40 micrometers In addition it correlates analytical results computed from two published analytical methods well with the other oil monitors at these filtration levels Below the 40 micrometer oil filtration level the R T Ferrograph was One method was used as published the other was modified for certain cases of coolant discharge from the blade suction found to be ineffective Author (GRA) surface For coolant ejection from blade surface regions where the surface static pressures are higher than the blade exit pressure N78-20136# RAND Corp, Santa Monica, Calif both methods predict the experimental results quite well However, LIFE-CYCLE ANALYSIS OF AIRCRAFT TURBINE ENGINES for ejection from regions with surface static pressures lower Interim Report J R Nelson Nov 1977 122 p refs than the blade exit pressure, both methods predict too small a (Contract F49620-77-C-0023) change in efficiency The modified method gives the better (AD-A050349, R-2103-AF) Avail NTIS HC A06/MF A01 prediction Author CSCL 21/5 The .report presents a methodology enabling the weapon N78-20132*$ National Aeronautics and Space Administration system planner to acquire early visibility of cost magnitudes, Lewis Research Center Cleveland Ohio proportions and trends associated with a new engine s life cycle, SIMULATED FLIGHT EFFECTS ON NOISE CHARACTERIS- and to identify drivers' that increase cost and can have the TICS OF A FAN INLET WITH HIGH THROAT MACH effect of lowering capability Later in the life cycle, logistics NUMBER managers can use the methodology and the feedback it produces Howard L Wesoky Donald A Dietrich and John M Abbott for more effective system management The procedure followed Apr 1978 45 p refs was to develop a theoretical framework for each phase of the (NASA-TP-1199 E-9253) Avail NTIS HC A03/MF A01 CSCL life cycle, collect and analyze data for each phase, develop 21E parametric cost-estimating relationships (CERs) for each phase, An anechoic wind tunnel experiment was conducted to use the CERs in examples to ascertain behavior and obtain insights determine the effects of simulated flight on the noise characteris- into cost magnitudes proportions and trends, and to identify tics of a high throat Mach number fan inlet Comparisons were cost-drivers and their effects and examine commercial experience made with the performance of a conventional low throat Mach for cost data and operational and maintenance practices that number inlet with the same 50 8 cm fan noise source Simulated could be profitable for the Air Force Author (GRA) forward velocity of 41 m/sec reduced perceived noise levels for both inlets the largest effect being more than 3 db for the high throat Mach number inlet The high throat Mach number inlet N78-20136*# Lockheed-California Co Burbank was as much as 7 5 db quieter than the low throat Mach number ROTORCRAFT LINEAR SIMULATION MODEL VOLUME 1: inlet with tunnel airflow and about 6 db quieter without tunnel ENGINEERING DOCUMENTATION Final Report. Nov airflow Effects of inlet flow angles up to 30 deg were seemingly 1976 - Jan 1978 irregular and difficult to characterize because of the complex J S Reaser Jan 1978 185 p ref 3 Vol flow fields and generally small noise variations Some modifications (Contract NAS2-9374) of tones and directivity at blade passage harmonics resulting (NASA-CR-152079-Vol-1 LR-28200-Vol-1) Avail NTIS from inlet flow angle variation were noted Author HC A09/MF A01 CSCL 01C A rotorcraft small perturbation linear model is described N78-20133*)P National Aeronautics and Space Administration Rotor flap inplane and feathering degrees of freedom as well Lewis Research Center, Cleveland, Ohio as control and augmentation systems are defined in addition to TWO-DIMENSIONAL COLD-AIR CASCADE STUDY OF A the classical vehicle six degrees of freedom The primary FILM-COOLED TURBINE STATOR BLADE 5 COMPAR- application was intended to be an analytic tool to assess the ISON OF EXPERIMENTAL AND ANALYTICAL AERODY- handling qualities of a dynamically combined main rotor and NAMIC RESULTS FOR BLADE WITH 12 ROWS OF body The modeling method retained the higher frequency response 0.038-CENTIMETER-(0015 INCH) DIAMETER COOLANT properties which aided in evaluating control and stability HOLES HAVING STREAMWISE EJECTION ANGLES augmentation systems Author

308 N78-20144

N78-20137*# Lockheed-California Co Burbank A technique was developed which provides reliable failure ROTOBCRAFT UNEAR SIMULATION MODEL VOLUME 2: detection and identification (FDD for a dual redundant subset of COMPUTER IMPLEMENTATION Final Report. Nov 1976 - the flight control sensors onboard the NASA F-8 digital fly by Jan 1978 wire (DFBW) aircraft The technique was successfully applied to J S Reaser and 0 H Saiki Jan 1978 77 p ref 3 Vol simulated sensor failures on the real time F-8 digital simulator (Contract NAS2-9374) and to sensor failures injected on telemetry data from a test (NASA-CR-152079-Vol-2 LR-28200-Vol-2) Avail NTIS flight of the F-8 DFBW aircraft For failure identification the HC A05/MF A01 CSCL QIC technique utilized the analytic redundancy which exists as A computer program used to process the equations is presented, functional and kinematic relationships among the various quantities and a full description of equation implementation is given The being measured by the different control sensor types The model was implemented in the IBM 360 and CDC series computer technique can be used not onfy in a dual redundant sensor systems M V system but also in a more highly redundant system after FDI by conventional voting techniques reduced to two the number N78-20138*# Lockheed-California Co Burbank of unfailed sensors of a particular type In addition the technique ROTORCRAFT UNEAR SIMULATION MODEL VOLUME 3 can be easily extended to the case in which only one sensor of USER'S MANUAL Final Report. Nov 1976 - Jan 1978 a particular type is available Author J S Reaser Jan 1978 68 p ref 3 Vol (Contract NAS2-9374) (NASA-CR-152079-Vol-3 LR-28200-Vol-3) Avail NTIS HC A04/MF A01 CSCL 01C N78-20142*# National Aeronautics and Space Administration For abstract see N78-20137 Langley Research Center. Langley Station, Va STUDY OF THE USE OF A NONLINEAR. RATE-LIMITED N78-20139*# National Aeronautics and Space Administration FILTER ON PILOT CONTROL SIGNALS Langley Research Center, Langley Station Va James J Adams Apr 1978 41 p refs SIMULATOR EVALUATION OF A FLIGHT-PATH-ANGLE (NASA-TP-1147. L-11762) Avail NTIS HC A03/MF A01 CONTROL SYSTEM FOR A TRANSPORT AIRPLANE WITH CSCL 01C DIRECT LIFT CONTROL The use of a nonlinear, rate limited filter for rejecting the Wendell W Kelley Mar 1978 33 p refs remnant (noise) in a pilot's control signal was studied through (NASA-TP-1116. L-11947) Avail NTIS HC A03/MF A01 both an analytical study using pilot models and a simulation CSCL 01C study using experienced test pilots The nonlinear filter was A piloted simulator was used to evaluate the flight path compared with a linear filter and with no filter for both attitude angle control capabilities of a system that employs spoiler direct and altitude control tasks The results show that the nonlinear lift control The system was designated the velocity vector control filter does promote rapid, steady maneuvering better than either system and was compared with a baseline flight path angle the linear filter or the no filter condition In addition, if the rate control system which used elevator for control The simulated limit in the nonlinear filter is set so that it is too restrictive a airplane was a medium jet transport Research pilots flew a pilot induced unstable altitude oscillation can result Author manual instrument landing system glide slope tracking task and a variable flight path angle task in the landing configuration to N78-20143*# National Aeronautics and Space Administration obtain comparative performance data Author Langley Research Center Langley Station. Va PILOT-MODEL ANALYSIS AND SIMULATION STUDY OF EFFECT OF CONTROL TASK DESIRED CONTROL RE- N78-20140*# National Aeronautics and Space Administration SPONSE Hugh L Dryden Flight Research Center. Edwards, Calif James J Adams Joseph Gera. and Joel B Jaudon Apr 1978 FLIGHT EVALUATION OF THE TRANSONIC STABILITY AND 46 p refs CONTROL CHARACTERISTICS OF AN AIRPLANE INCOR- (NASA-TP-1140) Avail NTIS HC A03/MF A01 CSCL 01C PORATING A SUPERCRITICAL WING A pilot model analysis was performed that relates pilot control Neil W Matheny and Donald H Gatlm Feb 1978 61 p refs compensation, pilot aircraft system response, and aircraft response (NASA-TP-1167. H-916) Avail NTIS HC A04/MF A01 CSCL characteristics for longitudinal control The results show that a 01C higher aircraft short period frequency is required to achieve superior A TF-8A airplane was equipped with a transport type pilot aircraft system response in an altitude control task than is supercritical wing and fuselage fairings to evaluate predicted required in an attitude control task These results were confirmed performance improvements for cruise at transonic speeds A by a simulation study of target tracking It was concluded that comparison of aerodynamic derivatives extracted from flight and the pilot model analysis provides a theoretical basis for determining wind tunnel data showed that static longitudinal stability, effective the effect of control task on pilot opinions Author (GRA) dihedral, and aileron effectiveness, were higher than predicted The static directional stability derivative was slower than predicted The airplane's handling qualities were acceptable with the stability augmentation system on The unaugmented airplane exhibited some adverse lateral directional characteristics that involved low N78-20144*|jl National Aeronautics and Space Administration Dutch roll damping and low roll control power at high angles of Langley Research Center, Langley Station. Va attack and roll control power that was greater than satisfactory TESTPLT. INTERACTIVE COMPUTER PROCEDURE FOR for transport aircraft at cruise conditions Longitudinally, the aircraft WIND-TUNNEL-DATA MANAGEMENT. RETRIEVAL. exhibited a mild pitchup tendency Leading edge vortex generators COMPARISON. AND PLOTTING delayed the onset of flow separation moving the pitchup point Harry H Hey son Feb 1978 89 p to a higher lift coefficient and reducing its severity Author (NASA-TM-78663) Avail NTIS HC A05/MF A01 CSCL 14B A method of maintaining retrieving, comparing and plotting N78-20141*# Draper (Charles Stark) Lab. Inc Cambridge wind-tunnel data by means of an interactive remote computer Mass terminal is described The software associated with the method RELIABLE DUAL-REDUNDANT SENSOR FAILURE DETEC- consists of two procedure files, three computer programs, and a TION AND IDENTIFICATION FOR THE NASA F-8 DFBW submittal file, all of which are discussed The procedure was AIRCRAFT Final Report. Jun 1976 - May 1977 based on maintaining the basic wind-tunnel data files in the James C Deckert. Mukund N Desai John J Deyst. Jr. and Langley standard interface tape (SIFT) format The SIFT format Alan S Willsky (MIT. Cambridge) Feb 1978 216 p refs was not part of the present development Those features of the (Contract NAS1-13914) format essential to the present use were described The entire (NASA-CR-2944. R-1077) Avail NTIS HCA10/MFA01 CSCL method was illustrated by sample executions from a remote 01C terminal Author

309 N78-20147

N78-20147# Army Construction Engineering Research Lab Parameters for a Weibull distribution of times to failure must Champaign III be estimated from a finite set of test points Much effort has DEVELOPMENT OF A PAVEMENT MAINTENANCE SYSTEM been expended identifying the shape parameter for different VOLUME 1 AIRFIELD PAVEMENT CONDITION RATING materials This report investigates determining probabilities of Final Report. Jul 1974 - Jul 1976 early failures when estimating the scale parameter from a finite Mohamed Y Shahm Michael I Darter and Starr D Kohn Dec number of tests Author (GRA) 1977 232 p refs Supersedes AFCEC-TR-76-27 2 Vol (MIPR FQ-8952-76-66005) N78-20534*# Kansas Univ Center for Research, Inc Lawrence (AD-A048884. CERL-TR-C-76-Vol-1 CEEDO-TR-77-44-Vol-1 EXPERIMENTAL AND FINITE ELEMENT INVESTIGATION AFCEC-TR-76-27) Avail NTIS HCA11/MFA01 CSCL 01/5 OF THE BUCKLING CHARACTERISTICS OF A BEADED This report describes the development and verification of a SKIN PANEL FOR A HYPERSONIC AIRCRAFT PhD Thesis. pavement condition index (PCI) for rating the condition of jointed Final Report concrete and asphalt-or tar-surfaced airfield pavements The William H Siegel Apr 1978 139 p refs PCI, which measures airfield pavement structural integrity and (Grant NsG-4006) surface operational condition is calculated based on measured (NASA-CR-144863) Avail NTIS HC A07/MF A01 CSCL pavement distress types severities, and densities obtained during 20K an inspection of the pavement GRA As part of NASA s continuing research into hypersonics and 85 square foot hypersonic wing test section of a proposed N78-20148*# Air Force Civil and Environmental Engineering hypersonic research airplane was laboratory tested The project Office. Tyndall AFB Fla reported on in this paper has carried the hypersonic wing test SMOKE ABATEMENT FOR DOD TEST CELLS Final Report, structure project one step further by testing a single beaded 20 Nov 1976 - 30 May 1977 panel to failure The primary interest was focused upon the Bradford C Grems, III Jul 1977 109 p refs buckling characteristics of the panel under pure compression (AF Proj 2103) with boundary conditions similar to those found in a wing mounted IAD-A050223, CEEDO-TR-77-40) Avail NTIS condition Three primary phases of analysis are included in the HC A06/MF A01 CSCL 06/6 report These phases include experimental testing of the beaded The Department of Defense owns and operates nearly 200 |et panel to failure, finite element structural analysis of the beaded engine test cells Occasionally visible exhaust smoke is emitted panel with the computer program NASTRAN, a summary of the from these structures Several pollution control agencies, most semiclassical buckling equations for the beaded panel under purely notably the state of California have expressed interest in compressive loads Comparisons between each of the analysis limiting test cell smoke emissions A review committee composed methods are also included Author of various Air Force and Navy representatives recommended further study of fuel additives as a means of achieving this goal They recognized additives as the most promising near term N78-20551# Stuttgart Univ (West Germany) Inst fuer Statik solution to the test cell smoke problem Ferrocene appeared to und Dynamik der Luft- und Raumfahrtkonstruktionen be the best of existing additives Studies were undertaken to ANALYSIS AND SYNTHESIS OF OPERATIONAL LOADS determine the environmental impact lexicological hazards and [ANALYSE UND SYNTHESE VON BETRIEBSBELASTUN- engine effects associated with routine ferrocene use Four types GEN] of Navy turbine engines were tested for ten hours each using J H Argyris, W Aicher. and H J Ertelt Feb 1976 71 p ferrocene These tests indicated that engines suffered no harm refs In GERMAN attributable to ferrocene but that the additive must be certified (ISD-193) Avail NTIS HC A04/MF A01 for each engine type on a individual basis Emission measurements The method for the analysis and synthesis of operational made during the tests showed that most pollutants are virtually loads dealt with is based on the possibility of subjecting the unchanged in quantity and character by ferrocene use and that test piece to a practically arbitrary load sequence This method paniculate matter is actually reduced GRA was proposed for the basis for standardization of aircraft structure fatigue tests using microcomputers In order to obtain this standardization system-dependent errors were eliminated from N78-2O481 *|C National Aeronautics and Space Administration available flight data, a data reduction was carried out. matrices Langley Research Center Langley Station Va of transition probabilities were drawn up and synthetic max- INVESTIGATION OF A HIGH SPEED DATA HANDLING imum load sequences were produced on punched tape and SYSTEM FOR USE WITH MULTISPECTRAL AIRCRAFT magnetic tape respectively for test facilities without direct SCANNERS computer control ESA W Lane Kelly and Barry D Meredith Mar 1978 42 p (NASA-TM-78689) Avail NTIS HC A03/MF A01 CSCL 14B A buffer memory data handling technique for use with N78-20631# Defence Research Establishment. Ottawa (Ontario) multispectral aircraft scanners is presented which allows digital Electrical Power Sources Div data generated at high data rates to be recorded on magnetic NICKEL/CADMIUM AIRCRAFT BATTERIES BATTERY tape A digital memory is used to temporarily store the data for ALARM UNIT subsequent recording at slower rates during the passive time of K Feldman and R M Hayashi Apr 1977 19 p refs the scan line, thereby increasing the maximum data rate recording (AD-A039521. DREO-TN-77-7) Avail NTIS capability over real-time recording Three possible implementations HC A02/MF A01 CSCL 10/3 are described and the maximum data rate capability is defined Malfunctions in nickel/cadmium aircraft batteries which may in terms of the speed capability of the key hardware compo- lead to dangerous thermal problems are usually preceded by nents The maximum data rates can be used to define the small atypical decreases in voltage of a single failing cell Early maximum ground resolution achievable by a multispectral aircraft detection of this decrease can provide time for suitable measures scanner using conventional data handling techniques Author to be taken before other cells are damaged and catastrophic consequences occur Also detection during battery shop operations can facilitate the screening out of defective cells The battery alarm unit described in this paper was developed at N78-20524f Air Force Flight Dynamics Lab Wright-Patterson DREO and is a simple device which monitors the cell voltages AFB. Ohio by comparing the voltage in one half of the battery with that of ESTIMATING TIMES TO EARLY FAILURES USING FINITE the other half Only three connections to the battery are required DATA TO ESTIMATE THE WEIBULL SCALE PARAMETER Atypical voltage changes in a single cell, of the order of 50 mV Final Report. Sep 1976 - Mar 1977 may be detected The precise sensitivity may be varied by Robert L Neulieb Sep 1977 22 p refs varying resistor values in the input network The instrument has (AD-A050263 AFFDL-TR-77-89) Avail NTIS been found useful in the battery shop both for warning of failing HC A02/MF A01 CSCL 14/4 cells in batteries being charged and for attracting attention to

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cells which show low capacity while being discharged Presumably The thickness noise theory is discussed Two full-scale rotors the instrument could be equally useful as an early warning device were tested in a wind tunnel with several tips involving changes on aircraft For such applications consideration must be given in chord thickness and sweep Impulsive noise data reduction to questions of procedure, configuration and airworthy mechani- procedures used are described The calculated and measured cal design Also experience in the field is required on which to impulsive noise peak pressures as a function of advancing tip base decisions on the optimum sensitivity and whether aircraft Mach number are compared showing good correlation for all and battery shop applications require the same sensitivities rotors considered Author Author (GRA)

N78-20632# Defence Research Establishment Ottawa (Ontario) N78-20918*# Beam Engineering Inc. Sunnyvale. Calif Electrical Power Sources Div ACOUSTICAL EFFECTS OF BLADE TIP SHAPE CHANGES NICKEL/CADMIUM AIRCRAFT BATTERIES: RAPID ON A FULL SCALE HELICOPTER ROTOR IN A WIND ELECTROLYTE EXCHANGE TECHNIQUE TUNNEL K Feldman and R M Hayashi Apr 1977 15 p refs Albert Lee Apr 1978 59 p refs (AD-A039335 DREO-TN-77-8) Avail NTIS (Contract NAS2-9399) HC A02/MF A01 CSCL 10/3 (NASA-CR-152082) Avail NTIS HC A04/MF A01 CSCL The potassium hydroxide electrolyte in nickel/cadmium aircraft 20A batteries may become increasingly more contaminated by Four tip shapes were tested They were rectangular swept, carbonate with battery use When the carbonate concentration tapered, and swept-tapered The measured data covered a wide exceeds certain limits it is advisable to exchange the electrolyte range of operating conditions The range of advancing tip Mach However, most of the electrolyte in a cell is soaked into the numbers were between 072 to 096. and the advance ratios separator materials and plate pores, and is held in the pack, so were from 0 2 to 0375 At low and moderate advancing tip only a small portion of it may be poured out Repeated removal Mach number, the data in the dbA scale appear to indicate the and replacement of these small amounts can accomplish the swept tip is the quietest swept tapered the second, tapered desired exchange if the clean added electrolyte is adequately third and rectangular the most noisy Above an advancing tip mixed with the contaminated electrolyte each time In the Mach number of about 089, a distinct acoustical pulse can be normal procedures, mixing is accomplished by discharging and observed, which dominates the acoustical waveform The pulse recharging the battery after each small exchange and hence is shape is symmetric at moderate tip Mach number, changing to very time consuming This paper discusses the various factors a sawtooth shape at high advancing tip Mach numbers Based involved and presents a vacuum technique for mixing the added on the amplitude of the impulsive noise it appears the swept- with the retained electrolyte in each cell The method presented tapered tip is the quietest tapered tip the second swept tip reduces the time required for the above operation from a week third and square tip the most noisy The data presented in this or more to a day or two Author (GRA) report should be useful as data bases for modeling and evaluating helicopter impulsive noise Author N78-20636# Defence Research Establishment. Ottawa (Ontario) Electrical Power Sources Div N78-20919*# National Aeronautics and Space Administration NICKEL/CADMIUM AIRCRAFT BATTERIES SINGLE Langley Research Center, Langley Station Va SENSOR TEMPERATURE MONITORING CONCORDE NOISE-INDUCED BUILDING VIBRATIONS. Kerva Feldman and Robert M Hayashi Mar 1977 12 p refs JOHN F KENNEDY INTERNATIONAL AIRPORT (AD-A037722 DREO-TN-77-3) Avail NTIS W H Mayes R DeLoach D G Stephens J M Cawthorn. H HC A02/MF A01 CSCL 10/3 K Holmes R B Lewis B G Holliday W T Miller, and D W Most of the failures of nickel/cadmium batteries in aircraft Ward Feb 1978 67 p refs are triggered by the development of a short circuit in a single (NASA-TM-78676 Rept-2) Avail NTIS HC A04/MF A01 cell in the battery An experiment was conducted to determine CSCL 20A whether the use of a single temperature sensor on an mtercell The outdoor/indoor noise levels and associated vibration levels link would be adequate to warn of a short circuit in a cell resulting from aircraft and nonaircraft events were recorded at located elsewhere in the battery The results indicate that this eight homesites and a school In addition, limited subjective tests would not be adequate GRA were conducted to examine the human detection/annoyance thresholds for building vibration and rattle caused by aircraft N78-20636# Defence Research Establishment, Ottawa (Ontario) noise Presented herein are the majority of the window and NICKEL/CADMIUM AIRCRAFT BATTERIES MULTICHAN- wall vibration data recorded during Concorde and subsonic aircraft NEL GASSING-RATE METER overflights Author Keiva Feldman and Ronald L Hames Mar 1977 24 p ref (AD-A039735, DREO-TN-77-5) Avail NTIS HC A02/MF A01 CSCL 10/3 N78-20920*# United Technologies Research Center, East The instrument described is used to assess the state of Hartford. Conn health of separators in nickel/cadmium aircraft batteries and thus A METHOD FOR CALCULATING EXTERNALLY BLOWN to permit removal from service of those cells which may be FLAP NOISE Final Report expected to fail catastrophically in the near future Twenty Martin R Fink Mar 1978 130 p refs channels are provided to permit simultaneous observation of all (Contract NAS3-17863) cells in a complete battery Each channel measures the rate of (NASA-CR-2954 R77-911739-17) Avail NTIS emission of gas from one cell during overcharge by means of HC A07/MF A01 CSCL 20A the pressure build up in a chamber from which the gas escapes Several basic noise components were described These via a suitable orifice Construction, calibration, and cleaning are components are (1) compact lift dipoles associated with the discussed Author (GRA) wing and flaps. (2) trailing edge noise associated with the last trailing edge and (3) quadrupole noise associated with the undeflected exhaust jet and the free jet located downstream of N78-2O917*# National Aeronautics and Space Administration the trailing edge These noise components were combined to Ames Research Center Moffett Field Calif allow prediction of directivity and spectra for under the wing COMPARISON OF MEASURED AND CALCULATED (UTW) slotted flaps with conventional or mixer nozzles UTW HELICOPTER ROTOR IMPULSIVE NOISE slotless flaps upper surface blowing (USB) slotless flaps, and Wayne Johnson and Albert Lee (Beam Eng Inc) Mar 1978 engine in front of the wing slotted flaps A digital computer 29 p refs program listing was given for this calculation method Directivities (Contract NAS2-9399) and spectra calculated by this method were compared with free (NASA-TM-78473 A-7355) Avail NTIS HC A03/MF A01 field data for UTW and USB configurations The UTRC method CSCL 20A best predicted the details of the measured noise emission, but

311 N78-21045

the ANOP method best estimated the noise levels directly below N78-21050*! National Aeronautics and Space Administration these configurations Author Langley Research Center. Langley Station. Va A VECTORIZATION OF THE JAMESON-CAUGHEY NYU TRANSONIC SWEPT-WING COMPUTER PROGRAM N78-21O45jjl Naval Postgraduate School Monterey Calif FLO-22-V1 FOR THE STAR-TOO COMPUTER A UFE CYCLE COST STUDY OF CONTRACTOR VERSUS Robert E Smith Joan I Pitts, and Jules J Lambiotte Mar ORGANIC SUPPORT OF AIRCRAFT PROGRAMS 1978 32 p refs MS Thaws (NASA-TM-78665) Avail NTIS HC A03/MF A01 CSCL 01A John Joseph McMenamm Jr Dec 1977 54 p refs The computer program FLO-22 for analyzing inviscid transonic (AD-A049438) Avail NTIS HC A04/MF A01 CSCL 05/3 flow past 3-D swept-wmg configurations was modified to use This thesis conducts a cost comparison between contractor vector operations and run on the STAR-100 computer The and organic support for the CH-53 Aircraft in two major operating vectorized version described herein was called FLO-22-V1 cost areas training and aircraft overhaul A life cycle cost approach Vector operations were incorporated into Successive Line is used and cost differentials are found for the twenty year life Over-Relaxation in the transformed horizontal direction Vector expectancy of the CH-53 system The intent of the study was relational operations and control vectors were used to implement not to criticize or change the existing system but rather to upwind differencing at supersonic points A high speed of provide cost data and planning insight for future aircraft computation and extended grid domain were characteristics of systems Author (GRA) FLO-22-V1 The new program was not the optimal vectonzation of Successive Line Over-Relaxation applied to transonic flow, N78-21047*jf McDonnell-Douglas Corp Long Beach, Calif however it proved that vector operations can readily be A THREE-DIMENSIONAL POTENTIAL-FLOW PROGRAM implemented to increase the computation rate of the algorithm WITH A GEOMETRY PACKAGE FOR INPUT DATA Author GENERATION Technical Report. 7 May 1976 - 22 Aug 1977 N Douglas Halsey Mar 1978 67 p refs N78-21051*# National Aeronautics and Space Administration (Contract NAS1-14402) Langley Research Center Langley Station, Va (NASA-CR-145311 MDC-J7733) Avail NTIS EFFECT OF LEADING-EDGE CONTOUR AND VERTICAL- HC A04/MF A01 CSCL 01A TAIL CONFIGURATION ON THE LOW-SPEED STABILITY Information needed to run a computer program for the CHARACTERISTICS OF A SUPERSONIC TRANSPORT calculation of the potential flow about arbitrary three dimensional MODEL HAVING A HIGHLY-SWEPT ARROW WING lifting configurations is presented The program contains a Vernard E Lockwood Mar 1978 53 p refs geometry package which greatly reduces the task of preparing (NASA-TM-78683) Avail NTIS HC A04/MF A01 CSCL 01A the input data Starting from a very sparse set of coordinate A low-speed investigation was made on a highly-swept data the program automatically augments and redistributes the arrow-wing model to determine the effect of wing leading-edge coordinates, calculates curves of intersection between compo- contour and vertical-tail configuration on the aerodynamic nents and redistributes coordinates in the regions adjacent to characteristics in pitch and sideslip The investigation was made the intersection curves in a suitable manner for use in the potential with the trading-edge flaps deflected over a range of angles of flow calculations A brief summary of the program capabilities attack from 8 deg to 32 deg The tests were made at a Mach and options is given as well as detailed instructions for the number of 013. which corresponds to a Reynolds number of data input a suggested structure for the program overlay, and about 3,000,000 based on the wing reference chord Author the output for two test cases Author

N78-21O48*# National Aeronautics and Space Administration N78-21052*# National Aeronautics and Space Administration Washington D C Langley Research Center, Langley Station Va AIRFOIL PROFILE IN A NONUNIFORM FLOW COMPARISON OF AERODYNAMIC DATA MEASURED IN Jan Polasek Mar 1978 53 p refs Transl into ENGLISH AIR AND FREON-12 WIND-TUNNEL TEST MEDIUMS from Rev Roum Sci Tech Ser Mecan Appl (Romania) v 9 William H Welter (Army Res and Technol Labs) Mar 1978 no 3 1964 p 617-666 Transl by Scientific Translation Service 56 p refs Santa Barbara Calif Original doc prep by Government Research (NASA-TM-78671) Avail NTIS HC A04/MF A01 CSCL 01A Inst for Heat Technology, Prague (Czechoslovakia) An experimental investigation was carried out to measure (Contract NASw-2791) two dimensional static aerodynamic characteristics of a 65 sub (NASA-TM-75272) Avail NTIS HC A04/MF A01 CSCL 01A 1-213 airfoil in air and Freon-12 (dichlorodifluoromethane) test A theory of airfoil section past two dimensional nonuniform mediums at corresponding test conditions The purpose of the flow is developed The theory is based on representation of tests was to compare measurements in the two test mediums airfoil section by vortex and source distributions and it can be and to evaluate reported methods of converting Freon-12 data used for calculation of aircraft wings in homogeneous and to equivalent air values The test article was a two dimensional mhomogeneous flow as well as for calculation of straight and wing instrumented to measure chordwise surface pressure radial blade and vane-cascades Author distributions The parameters considered were Mach numbers from 0 6 to 10. angles of attack of zero deg and 1 deg. and N78-21049*# National Aeronautics and Space Administration Reynolds numbers based on model chord from 2.000,000 to Langley Research Center Langley Station Va 21.000,000 The agreement between data measured in the two SUBSONIC LONGITUDINAL AND LATERAL-DIRECTIONAL test mediums is further improved by application of the transonic STATIC AERODYNAMIC CHARACTERISTICS FOR A or area ratio similarity laws Where flow conditions are char- CLOSE-COUPLED WING-CANARD MODEL IN BOTH SWEPT acterized by surface shocks or stall, the effects of flow separation BACK AND SWEPT FORWARD CONFIGURATIONS may not be identically reflected in the Freon-12 data, even when Jarrett K Huffman and Charles H Fox Jr Feb 1978 60 p converted in accordance with existing similarity laws Author refs (NASA-TM-74092) Avail NTIS HC A04/MF A01 CSCL 01A N78-21053*# Vought Corp , Hampton, Va Technical Center A general research fighter model was tested in the Langley LOW-SPEED AERODYNAMIC CHARACTERISTICS FROM 7 by 10-foot high speed tunnel at a Mach number of 0 3 The WIND-TUNNEL TESTS OF A LARGE-SCALE ADVANCED close-coupled wing-canard combination was tested with both ARROW-WING SUPERSONIC-CRUISE TRANSPORT lifting surfaces in a 60 deg swept back configuration and in a CONCEPT 32 deg swept forward configuration The angle-of-attack range Paul'M Smith Apr 1978 102 p refs was from approximately -4 deg to 48 deg at sideslip angles of (Contract NAS1-13500) zero deg, -5 deg The data is presented without analysis in (NASA-CR-145280) Avail NTIS HC A06/MF A01 CSCL order to expedite publication Author 01A

312 N78-21062

Tests have been conducted to extend the existing low speed The effect of light on the mean flow and turbulence properties aerodynamic data base of advanced supersonic-cruise arrow wing of a 0056 m circular jet were determined in a free jet wind configurations Principle configuration variables included wing tunnel The nozzle exit velocity was 122 m/sec and the wind leading-edge flap deflection wing trailmg-edge flap deflection, tunnel velocity was set at 0 12 37 and 61m/sec Measurements horizontal tail effectiveness and fuselage forebody strakes A of flow properties including mean velocity, turbulence intensity limited investigation was also conducted to determine the low and spectra and eddy convection velocity were carried out using speed aerodynamic effects due to slotted trailmg-edge flaps two linearized hot wire anemometers Normalization factors were Results of this investigation demonstrate that deflecting the wing determined for the mean velocity and turbulence convection leading-edge flaps downward to suppress the wing apex vortices velocity Author provides improved static longitudinal stability, however, it also results in significantly reduced static directional stability The N78-21059*# Nevada Univ. Las Vegas use of a Selected fuselage forebody strakes is found to be effective UNSTEADY TWO DIMENSIONAL AIRLOADS ACTING ON in increasing the level of positive static directional stability OSCILLATING THIN AIRFOILS IN SUBSONIC VENTILATED Drooping the fuselage nose which is required for low-speed WIND TUNNELS pilot vision, significantly improves the lateral-directional tnm Joseph Fromme and Michael Golberg May 1978 139 p refs characteristics Author (Grant NsG-2140) (NASA-CR-2967) Avail NTIS HC A07/MF A01 CSCL 01A N78-21054I Aeronautical Research Labs Melbourne (Australia) The numerical calculation of unsteady two dimensional A BRIEF EXAMINATION OF THE FLOW EXTERNAL TO airloads which act upon thin airfoils in subsonic ventilated wind AN F-111 INTAKE AT MACH 1 6 tunnels was studied Neglecting certain quadrature errors Bland's Murdoch Culley Jul 1975 39 p refs collocation method is rigorously proved to converge to the (ARL/ME-Note-357) Avail NTIS HC A03/MF A01 mathematically exact solution of Bland s integral equation and A one-thirtieth scale wind tunnel model of the forward fuselage a three way equivalence was established between collocation, and intakes of an F-111 aircraft was used to investigate Galerkin s method and least squares whenever the collocation qualitatively, at Mach 1 6, the interference flows which occur in points are chosen to be the nodes of the quadrature rule used the vicinity of the intakes The intake configuration employed for Galerkin s method A computer program displayed convergence was based on the SWIP design, pre-cursor to the Triple Plow I with respect to the number of pressure basis functions em- configuration fitted to the Australian F-111c aircraft The intake ployed, and agreement with known special cases was demon- mass flow was varied between supercritical and subcntical, with strated Results are obtained for the combined effects of wind the model attitude varying between 0 and 9 degrees incidence tunnel wall ventilation and wind tunnel depth to airfoil chord and plus or minus 4 5 degrees of yaw The test Reynolds number, ratio and for acoustic resonance between the airfoil and wind based on the model's intake diameter, was 80.000 The fuselage tunnel walls A boundary condition is proposed for permeable boundary layer was observed to be distorted by cross flows walls through which mass flow rate is proportional to pressure established through model incidence and yaw. causing it to thicken jump Author locally upstream of the intakes The fuselage boundary-layer splitter plate fitted to prevent the fuselage boundary-layer interacting N78-21060# Naval Ship Research and Development Center, with the intake shock system as well as to prevent its mgestion Bethesda Md Aviation and Surface Effects Dept by the intakes was unable to digest the model boundary-layer EFFECT OF TURBULENT JET MIXING ON THE STATIC This caused a severe three dimensional separation upstream of LIFT PERFORMANCE OF A POWER AUGMENTED RAM the splitter plate which interfered with the wing flow because WING of a shock generated at the fuselage separation Author William J H Smithey. Basil S Papadales Jr, and Harvey R Chaplin Sep 1977 19 p refs N78-21065*# National Aeronautics and Space Administration (AD-A049620. DTNSRDC/ASED-389) Avail NTIS Langley Research Center Langley Station. Va HC A01/MF A01 CSCL 20/4 NUMERICAL STUDY OF TRANSONIC FLOW OVER Calculation procedures are developed using axisymmetnc and OSCILLATING AIRFOILS USING THE FULL POTENTIAL two dimensional turbulent jet theory for predicting the static lift EQUATION performance of a two dimensional power augmented ram wing KOJI Isogai Apr 1978 41 p refs The resulting lift prediction is found to be in good agreement (NASA-TP-1120 L-11984) Avail NTIS HC A03/MF A01 with experimental data Author (GRA) CSCL 01A The behavior of unsteady aerodynamic loadings on airfoils oscillating in transonic flow has been investigated numerically N78-21061jjl Naval Postgraduate School Monterey Calif with particular attention given to supercritical airfoil sections A UNSTEADY. SURFACE PRESSURE AND NEAR-WAVE previously developed finite difference method, which is based HOTWIRE MEASUREMENTS OF A CIRCULATION CON- on the full potential equation and which uses a quasi- TROL AIRFOIL M S Thesis conservative scheme for proper capture of a shock wave motion, Karl Aurel Kail IV Sep 1977 142 p refs was employed for the present study The unsteady aerodynamic (AD-A050025) Avail NTIS HC A07/MF A01 CSCL 20/4 pressure and load distributions on several different airfoil sections The large lift coefficient changes attainable with Circulation are presented with particular emphasis on the effects of Control Airfoils through small changes in boundary layer blowing free-stream Mach number, reduced frequency, and mean angle suggest rotary wing cyclic control can be obtained through of attack These parameters are demonstrated to have a significant modulation of the blowing Static pressure distributions were effect on the behavior of the unsteady aerodynamic loadings obtained to assess the unsteady behavior of a Circulation Comparisons of the present calculations with the exact mviscid Control Rotor in a two-dimensional flow A constant-radius hotwire solution and with the experimental results are also presented wake traversing mechanism was constructed to augment the Author pressure data and to study the flow phenomena occurring in the region of Coanda jet separation Through correlation of N78-21068*# Pratt and Whitney Aircraft Group East Hartford turbulence intensity data with pressure data it was discovered Conn that the point of Coanda jet separation could be located using MEAN VELOCITY. TURBULENCE INTENSITY AND TURBU- the hotwire The objective of these tests was accordingly expanded LENCE CONVECTION VELOCITY MEASUREMENTS FOR A to include correlation of the location of separation with flow CONVERGENT NOZZLE IN A FREE JET WIND TUNNEL parameter variation GRA Final R«port C J McColgan and R S Larson Apr 1978 31 p refs N78-21062# Aeronautical Research Inst of Sweden Stockholm (Contract NAS3-17866) Aerodynamics Dept (NASA-CR-2949 PWA-5506) Avail NTIS HC A03/MF A01 TRANSONIC WIND TUNNEL TESTS ON TWO- CSCL 01A DIMENSIONAL AEROFOIL SECTIONS. DETERMINATION

313 N78-21063

OF PRESSURE DISTRIBUTION AND DRAG FOR AN F Crum K Haspert S Koualski N Sullivan and J Underwood AEROFOIL WITH A MODIFIED NACA 65 SU82-21S Oct 1977 105 p refs SECTION IN FFA WIND TUNNEL S5. PART 2 Interim (Contract F09603-77-A-3104) Report (AD-A049743 ASD-TR-77-76 Rept-1942-01-1-1676) Avail Goeran Ehn 1977 138 p refs NTIS HC A06/MF A01 CSCL 01/2 (Contracts F-INK-11-12-83343 F-INK-11-12-02871 The objectives of the study presented in this report were F-INK-07-11966/02871. F-INK-07-21898 to further define USAF requirements and objectives in reducing F-INK-82223-76-001-21-001) midair collisions establish organizational relationships and (FFA-TN-AU-725) Avail NTIS HC A07/MF A01 participation in midair prevention efforts investigate possible A two-dimensional airfoil model was investigated in FFA alternative methods to reduce USAF midair collisions and further S5 025 sq m wind tunnel with a modified NACA 652-215 define follow-on phases of the Midair Prevention Systems (MAPS) section The modifications consisted of a decrease in the mean program that the USAF could undertake to reduce midair collision line chamber and a change of the thickness distribution over potential This report provides background information and analysis the rear part of the airfoil compared to the nominal section on the midair collision experiences of the USAF from 1968 The Reynolds number based on the airfoil chord length was in through June 1977 and the near midair collision experiences the range 2 million < or = Re < or = 2 3 million Models from 1975 through June 1977 The midair and near midair with the same section were tested earlier at the National collision information is analyzed from many different aspects such Aeronautical Establishment Canada at Reynolds numbers in the as altitude type flight plan category of aircraft mission activity range 5 million < or = Re < or = 35 million By means of commands and phase of flight Midair collision programs were tests with different locations of transition trips it was attempted identified and actions that could bf taken bv the USAF to reduce to establish to what degree a simulation of these high Reynolds' midair collision potential are specified This report also identifies number flow conditions could be achieved in wind tunnel S5 various organizations that would be involved with the USAF The test program included airfoil pressure distribution measure- midair problem and identifies their relationships in attempting to ments and wake drag measurements in the Mach number range reduce the midair potential The report also discusses the FAA 0 6 < or = free stream Mach < or = 075 for angles of and civilian viewpoints and activities as they relate to midair attack of alpha = 0 deg 1 5 deg 20 deg and 40 deg Sublimation collision prevention Author (GRA) tests and flow visualization tests were also performed Author (ESA)

N78-21068| Radio Corp of America Van Nuys Calif N78-21063# National Transportation Safety Board Washington. Electromagnetic and Aviation Systems Div D C BEARING STUDY PROGRAM Final Report SPECIAL STUDY EMERGENCY LOCATOR TRANSMIT- Ernest Jelhnek Walter Kram M Levmsen O M Woodward, TERS. AN OVERVIEW and Bernard Case Apr 1974 429 p refs 26 Jan 1978 33 p refs (Contract N62269-73-C-0906) (NTSB-AAS-78-1) Avail NTIS HC A03/MF A01 (AD-A049767 RCA-EASD-TP-2146) Avail NTIS A review of emergency locator transmitter (ELT) problems HC A19/MF A01 CSCL 01/2 and efforts to solve these problems, and a survey of the current A study was conducted to assess the feasibility and define situation was conducted Statistical data from the National the system accuracy and equipment required to add a bearing Transportation Safety Board and the Air Force Rescue Coordination measurement subsystem to the SECANT Collision Avoidance Center for 1975 and 1976 is used in this study Numerous System (CAS) The results indicate the feasibility of achieving discussions were held with a substantial segment of the ELT the accuracy required to serve useful functions Equipment and search and rescue community including those organizations configurations required for Proximity Warning Indicator and CAS specifically addressing the current ELT problems Further an applications were evolved and are presented in detail in this intensive review of the ELT resource literature was completed study The approach utilizes a ring array antenna consisting of including technical papers general articles, and communications vertical monopoles interconnected by stnplme It has a high from many of those organizations concerned with the ELT and accuracy outer ring of 16 monopoles, an inner ring of 4 monopoles search and rescue Author for resolving ambiguities and a central reference monopole The array receives the signals transmitted by any of the equipment N78-21064# National Transportation Safety Board, Washington types in the SECANT family and the relative bearing is determined D C by measuring the phase difference between the signals in the AIRCRAFT ACCIDENT REPORT SOUTHERN AIRWAYS reference monopole and in the rings Random errors are minimized INC. DC-9-31. N1335U, NEW HOPE. GEORGIA. APRIL 4. by integration of the high pulse rate, frequency hopped signals 1977 Predicted overall error is 1 degree one Sigma with a bias 26 Jan 1978 109 p component of 0 8 degree and a random component of 0 5 degree (NTSB-AAR-78-3) Avail NTIS HC A06/MF A01 An antenna array was constructed and tests in an anechoic The National Transporation Safety Board determined that chamber confirmed the validity of the design approach GRA the probable cause of this accident was the total and unique loss of thrust from both engines while the aircraft was penetrating an area of severe thunderstorms The loss of thrust was caused by the ingestion of massive amounts of water and hail which in combination with thrust lever movement induced severe stalling N78-21071|jl Advisory Group for Aerospace Research and in and major damage to the engine compressors Ma)or Development. Pans (France) contributing factors included the failure of the company s APPLICATIONS OF ADVANCES IN NAVIGATION TO dispatching system to provide the flightcrew with up-to-date GUIDANCE AND CONTROL severe weather information pertaining to the aircraft's intended Feb 1978 279 p refs Partly in ENGLISH and FRENCH route of flight, the captain's reliance on airborne weather radar Presented at the 24th Technical Meeting of the Guidance and for penetration of thunderstorm areas, and limitations in the Control Panel Stuttgart, 10-13 May 1977 Federal Aviation Administration s air traffic control system which (AGARD-CP-220, ISBN-92-835-0211-6) Avail NTIS precluded the timely dissemination of real-time hazardous weather HC A13/MF A01 information to the flightcrew Author Conference proceedings on the application of advances in navigation to guidance and control are reported Topics discussed include (1) improvements in mertial navigation systems and their N78-21066# Anne Research Corp Annapolis Md applications (2) improvements in radar and radio navigation aids INVESTIGATION TO SUPPORT PHASE 1 OF THE USAF and their applications (3) specific functions and system concepts MIDAIR PREVENTION SYSTEMS PROGRAM (MAPS) (4) new major systems, and (5) system improvements and Final Report. Jun - Oct 1977 concepts

314 N78-21083

N78-21073# Singer Co Little Falls N J Kearfott Div information The signal format is the key element of the system, NEW TECHNIQUES FOR LOW COST STRAPDOWN allowing for simplicity of airborne equipment and flexibility of INERTIAL SYSTEMS ground stations Basic error considerations show that errors due P M Brodie and C R Giardina In AGARD Appl of Advan in to airborne signal processing can be neglected and that the Navigation to Guidance and Control Feb 1978 13 p refs ground system can be adapted to a large extent to the special multipath environment This allows the deployment of ground Avail NTIS HC A13/MF A01 stations tailored to a special site leading to very economic A number of techniques which can be employed to make a solutions also on the ground Implementation of airborne redundant strapdown configuration feasible is addressed The equipment is described followed by a more detailed presentation major topics discussed are concept of sett contained redundancy, of ground station design (DME transponder, antenna array receiver and modular reliability comparisons J C S multiple, processing method, transmitter and data encoder calibration and monitoring) Author N78-21074| Societe Nationals Industnelle Aerospatiale. Toulouse (France) INERTIAL SMOOTHING AND EXTRAPOLATION OF ILS N78-21081|P Deutsche Forschungs- und Versuchsanstalt fuer BEAMS APPLICATION TO THE AIRBUS A 300 B Luft- und Raumfahrt Brunswick (West Germany) Inst fuer J Irvoas, D Buisson, P Uoret (SAGEM Pans), and X Lagarde Flugfuehnng (SAGEM, Pans) In AGARO Appl of Advan in Navigation to ACCURACY CONSIDERATIONS ON NEW MICROWAVE Guidance and Control Feb 1978 49 p refs In ENGLISH and LANDING SYSTEMS (MLS) FROM AN OPERATIONAL FRENCH POINT OF VIEW Avail NTIS HC A13/MF A01 Alfred Becker In AGARO Appl of Advan in Navigation to The hybrid radio mertial guidance system described in this Guidance and Control Feb 1978 15 p refs report performs the following functions (1) smoothing of the aircraft's flight path during an ILS automatic approach, (2) a Avail NTIS HC A13/MF A01 very marked reduction in the lateral movements of the aircraft Some selected problems are dealt with related to the accuracy around its canter of gravity and in the deflection of the control of the different systems from an operational point of view Some surface due to LOC beam noise (3) the continuance of guidance general remarks to the International Civil Aviation Organization in the event of failure of the LOC receiver. (4) in the event of (ICAO) Microwave Landing Systems (MLS) competition are serious or sudden failures which interfere with guidance of the presented, along with ICAO Accuracy Requirements on the new aircraft, the LISS system dispenses with the need for LOC signals MLS Also presented are discussions on the performance of the and reduces any deviation movements of the aircraft The system and flare guidance problems Some perspective considera- system requires only a relatively low performance mertial unit, tions are given as an indication of possible future performance although one with a higher performance would improve the overall improvements Author system Author

N78-21082# Lear Siegler. Inc Grand Rapids Mich Instrument N78-21077# Rohde and Schwartz Munich (West Germany) Div UHF OF TRIANGULATION SYSTEM FOR CONTROL AND A MULTI-SENSOR IMPLEMENTATION FOR NAVIGATION. GUIDANCE OF MILITARY AIRCRAFT POSITION LOCATION. POSITION UPDATE. RECONNAIS- Bernhard F Ernst In AGARD Appl of Advan in Navigation to SANCE. AND WEAPON DELIVERY AN/ARN-10KV) Guidance and Control Feb 1978 7 p F E Pickel In AGARD Appl of Advan in Navigation to Guidance and Control Feb 1978 9 p Avail NTIS HCA13/MFA01 A system for the guidance of aircraft from ground stations Avail NTIS HC A13/MF A01 is discussed The system consists essentially of a network of The AN/ARM-101 (V) is a digital system developed to replace direction finders and is intended to complement rather than and/or functionally improve the present avionics in the USAF replace conventional radars and other landing aids normally F-4E and RF-4C aircraft It upgrades the operational capability installed at airports As a guidance technique a network of of the total weapon system through a multi-sensor implementa- direction finders offers the advantage of surface coverage or it tion for navigation, offset aim point and target location weapon permits a form of surface_navigation The system has a further delivery and reconnaissance The navigation position locating, advantage of particular significance in emergency situations such and position updating capabilities utilize a digital Inertial as may follow an error in navigation or a loss of fuel nothing Measurement Unit (IMU) loran, fire control or mapping radar. more than an operational radio set need be available on board Pave Tack TISEO (Electro-Optical Target Identification System), the aircraft before use can be made of the DF guidance network and Lead Computing Optical Sight System (LCOSS) interfaces This feature can also be useful in the guidance of military aircraft Performance features include long-range and tactical navigation since as practice has shown, maneuvers at low level can often all-weather blind bombing adverse weather landing approach, take the aircraft outside the airspace covered by ground-based uncanned weapon delivery profiles and automatic reconnaissance radars Author steering Author

N78-21078# Standard Electrik Lorenz A G Stuttgart (West N78-21O83| Rockwell International Corp, Cedar Rapids Iowa Germany) Collins Avionics Div PRECISE ENROUTE NAVIGATION BASED ON GROUND- A 4D APPROACH CONTROL USING VOR/DME/ILS DERIVED TECHNIQUES GUIDANCE G Blaschke and G Peuker In AGARD Appl of Advan in Juergen M H Bruckner and Thomas G Sharps In AGARD Navigation to Guidance and Control Feb 1978 13 p refs Appl of Advan in Navigation to Guidance and Control Feb 1978 15 p Avail NTIS HCA13/MFA01 Avail NTIS HCA13/MFA01 A solution is offered by a ground-derived concept for azimuth A study is presented to design, develop and implement a measurement It is based on the standard L-band DME using 4D approach control system using conventional aircraft sensors also the existing airborne DME set The DME interrogation pulses and displays augmented with area navigation capability The goal of the aircraft are received at the ground via a special antenna was to arrive at a system capable of retrofit with most air array by DF equipment that allows immediate determination of transport aircraft Multifunction CRT (MAP) displays and mertial angle of incidence This angle is sent back to the aircraft by a complementation were to be avoided The only equipment item third pulse synchronized with the according DME reply In the required in the final design is a Mark 2 type RNAV system aircraft a search and track system extracts the 'angle reply. the capability used specifically to automatically define the nominal time delay of which relative to the DME reply, represents angle multiple-ordered-leg 4D RNAV approach path The capability for

315 N78-21087 close-in ILS captures (including those from above) was also A brief historical background of the technology and economics included to allow for diverse aircraft separation and noise of aircraft replacement and retirement in the prejet era is presented abatement requirements Author to see whether useful insights can be obtained applicable to the jet era Significant differences between the two periods N78-21087| Deutsche Forschungs- und Versuchsanstalt fuer were demonstated Current technological and operational Luft- und Raumfahrt Brunswick (West Germany) Inst fuer economic perspectives were investigated in detail Some Flugfuehrung conclusions are drawn to aircraft retirement policies Author IMPROVED AIRCRAFT TRACKING USING MANEUVER STATISTICS ENROUTE AND IN THE TERMINAL AREA N78-21093*# Boeing Vertol Co Philadelphia Pa Ulrich Brokof In AGARO Appl of Advan in Navigation to RESEARCH REQUIREMENTS TO IMPROVE RELIABILITY Guidance and Control Feb 1978 9 p refs OF CIVIL HELICOPTERS John J Dougherty III and Lawrence D Barrett Apr 1978 Avail NTIS HC A13/MF A01 114 p refs By means of radar tracking it is possible to estimate (Contract NAS1-13624) continuously the dynamic state of an aircraft from discrete radar (NASA-CR-145335) Avail NTIS HC A06/MF A01 CSCL data This is necessary, for instance, when investigating collision 01C risks In this paper autocorrelation functions have been computed The major reliability problems of the civil helicopter fleet as from acceleration data The autocorrelation function could be reported by helicopter operational and maintenance personnel approximated by a model which corresponds to a periodic random are documented An assessment of each problem is made to variable The model itself as well as the model parameters gives determine if the reliability can be improved by application of an indication of how to improve radar tracking algorithm (additional present technology or whether additional research and develop- parameters) A simple and an extended model are practically ment are required The reliability impact is measured in three tested in view of predicting properties The same example is ways (1) The relative frequency of each problem in the fleet used to show how it is possible to improve radar tracking by (2) The relative on-aircraft manhours to repair, associated with each fleet problem (3) The relative cost of repair materials or aiding lateral acceleration with the roll angle information of the replacement parts associated with each fleet problem The data aircraft via a data link between the control centre and the reviewed covered the period of 1971 through 1976 and covered aircraft Author only turbine engine aircraft Author N78-21O90JJI Ferranti Ltd , Edinburgh (Scotland) NAVIGATION. GUIDANCE AND CONTROL FOR HIGH N78-21094*# National Aeronautics and Space Administration PERFORMANCE MILITARY AIRCRAFT Ames Research Center Moffett Field Calif W H McKmlay In AGARD Appl of Advan in Navigation to EFFECT OF HIGH LIFT FLAP SYSTEMS ON THE CONCEP- Guidance and Control Feb 1978 12 p refs TUAL DESIGN OF A 1985 SHORT-HAUL COMMERCIAL STOL TILT ROTOR TRANSPORT Avail NTIS HC A13/MF A01 Michael D Shovlin and Bruno J Gambucci Apr 1978 29 p The paper discusses some of the factors involved in applying refs advanced navigation to an aircraft operating at low altitude for (NASA-TM-78474 A-7364) Avail NTIS HC A03/MF A01 reconnaissance or to locate and attack ground targets It considers CSCL QIC the distinctions between navigation accuracy and the accuracy The performances of a derivative concept of a 1985 STOL with which a pilot can follow a given flight profile There are tilt rotor transport and of a second concept having a complex references to target acquisition and the need to pre-plan the mechanical flap system similar to a short field B737 aircraft profile Recent Ferranti developments in the display of naviga- were compared for a 370 kilometer (200 nautical mile) short tion information coupled with a level of automatic pre-planning haul mission The flap system of the latter allowed lift to be are discussed Author shifted from the rotor system to the wing, permitting a 26 percent reduction in dynamic component weight while also permitting the use of a smaller wing The wing and disc loading of this N78-21O91# Systems Control. Inc. West Palm Beach, Fla concept were 5746 (120 psf) and 1915 (40 psf) newtons per AREA NAVIGATION SYSTEMS AND PROCEDURES square meter respectively while the wing and disc loading of Donald W Richardson and James S Tyler In AGARD Appl the derivative concept were 4788 (100 psf) and 1197 (25 of Advan in Navigation to Guidance and Control Feb 1978 psf) newtons per square meter respectively The high lift wing 9 p refs tilt rotor showed slightly improved fuel usage over its entire Avail NTIS HC A13/MF A01 operating range and about 6 to 8 percent improvement in direct An attempt to identify, in pragmatic user-related terms the ope ctiag costs resulting from its improved cruise efficiency and operational significance of the overall concept of area navigation reduced weight Other advantages include improved reliability (RNAV) is presented Its purpose is to explore, over a range of with potentially reduced maintenance and better riding quality users and missions, the spectrum of functions and capabilities Author that this generic navigation technique offers Starting with a summary of the correlation between current navigation systems both civilian and military and the concept of area navigation, N78-21095*# Lockheed-California Co Burbank Commercial the main content of the paper deals with two major issues, the Advanced Design Div current status of RNAV research, and future applications of RNAV FUEL CONSERVATION MERITS OF ADVANCED TUR- The current status is reviewed in the light of the results of BOPROP TRANSPORT AIRCRAFT Final Report. Jan - Aug extensive operational and cost benefit studies Two illustrative 1977 examples of RNAV operational applications are discussed, namely J D Revell and R H Tullis Aug 1977 154 p refs the use of RNAV to facilitate complex noise abatement profiles, (Contract NAS2-8612) and the application of RNAV techniques to improve the efficiency (NASA-CR-152096. LR-28283) Avail NTIS of airborne search and rescue operations Author HC A08/MF A01 CSCL 01C The advantages of a propfan powered aircraft for the N78-21092*# Northwestern Univ , Evanston III Transportation commercial air transportation system were assessed by the Center comparison with an equivalent turbofan transport Comparisons FACTORS AFFECTING THE RETIREMENT OF COM- were accomplished on the basis of fuel utilization and operating MERCIAL TRANSPORT JET AIRCRAFT Progress Report costs, as well as aircraft weight and size Advantages of the Frank A Spencer and Joseph A Swanson 15 Feb 1978 propfan aircraft, concerning fuel utilization and operating costs, 209 p refs were accomplished by considering (1) incorporation of propfan (Grant NsG-2149) performance and acoustic data (2) revised mission profiles (longer (NASA-CR-152115. PR-2) Avail NTIS HC A10/MF A01 CSCL design range and reduction in, and cruise speed), and (3) utilization QIC of alternate and advanced technology engines Author

316 N78 21102

N78-21096*# Old Dominion Univ. Norfolk. Va Research aeroelastic stability boundaries is indicated through plots of actual Foundation measured boundaries Where available the alternating strap loads EXPERIMENTAL INVESTIGATION OF EFFECT OF JET for these configurations are presented A limited amount of analysis DECAY RATE ON JET-INDUCED PRESSURES ON A FLAT was conducted and seemed to correlate with the test results PLATE Final Report GRA John M Kuhlman. Don S Ousterhout, and Ronald W Warcup Washington NASA Apr 1978 81 p refs N78-21099# Raytheon Co . Sudbury Mass (Grant NGL-47-003-039) A REVIEW OF METHODOLOGIES AND CONCEPTS TO (NASA-CR-2979) Avail NTIS HC A05/MF A01 CSCL01C MEASURE AND EVALUATE AIRCRAFT SURVIVABIUTY/ An experimental study of the interaction between a lift jet VULNERABILITY Final Report and an aircraft wing for a jet VTOL aircraft was performed for R Smith A S Soltes, J K Wetzel and L R Doyon Jan the simplified model of an unheated, subsonic, circular jet exiting 1978 109 p refs at right angles to a flat plate into a uniform subsonic crosswind (Contract F33615-73-C-0678) The effects of jet dynamic pressure decay rate upon the jet (AD-A050152. ER74-4435 JTCG/AS-75-S-002) Avail NTIS location and jet induced pressure distribution on the plate were HC A06/MF A01 CSCL 01/3 studied over a range of jet to crossflow velocity ratios of 2 2 This report is a summary of all significant studies performed fuel tank ullage may contain a mixture of fuel vapor GRA in air that presents a fire and explosion hazard This hazard can be eliminated if the air is replaced by an inert gas containing N78-2110Of Naval Air Development Center. Warmmster Pa insufficient oxygen to allow ignition Fuel tank merting systems Aircraft and Crew Systems Technology Directorate using onboard storage of liquid nitrogen to supply the inert gas A-4F BLUE ANGEL FLIGHT USAGE DATA. 1976 have been demonstrated by the FAA and others and have been Final Report retrofitted into some U S Air Force transport aircraft Tests by K I Leikach and G A Bohannon 15 Oct 1977 70 p refs NAFEC and the Air Force have shown that fuel ullage oxygen (AD-A050164. NADC-77287-60) Avail NTIS concentration must be reduced to 9 percent or less to protect HC A04/MF A01 CSCL 01/3 against ignition sources The use of hollow fiber permeable This report presents flight usage data which is used for membranes in an onboard inert gas generator (IGG) fuel tank monitoring individual Blue Angel aircraft structural fatigue life merting system has been shown to be a feasible alternative to Data identify operational trends that are beneficial/detrimental systems using stored liquid nitrogen which must be periodically to prolonging aircraft fatigue life A total of 2700 4 hours of replenished A program to optimize the permeable membrane counting accelerometer data and 363 2 hours of oscillograph geometry generate data required for system design and to design, data were processed and are presented This data provides the fabricate and test full-scale breadboard permeable membrane basis for flight spectra development of Blue Angel mission air separation modules was conducted using the McDonnell- utilizations as well as information concerning point in the sky Douglas DC-9 aircraft as a design baseline Results of membrane assumptions required for fatigue analyses Author (GRA) development, full-scale breadboard module design and testing are reported a preliminary design is presented for a hollow fiber permeable membrane IGG system for the DC-9, and ownership considerations for the airborne system design, including N78-21101# Douglas Aircraft Co Inc. Long Beach Calif a life cycle cost analysis are discussed Author (GRA) EVALUATION OF WINDSHIELD MATERIALS SUBJECTED TO SIMULATED SUPERSONIC FLIGHT Final Report. Jun N78-21098j|l Boeing Vertol Co. Philadelphia. Pa 1976 - Aug 1977 BEARINGLESS TAIL ROTOR LOADS AND STABILITY J B Hoffman Sep 1977 150 p refs Final Report Mar 1976 - Jan 1976 (Contract F33615-75-C-3105) W T Edwards and W Miao Nov 1977 289 p refs (AD-A049981. MDC-J7171 AFFDL-TR-77-92) Avail NTIS (Contract DAAJ02-75-C-0017. DA Proj 1F2-62209-AH-76) HC A07/MF A01 CSCL 01/3 (AD-A049579. D210-11025-1. USAAMRDL-TR-76-16) Avail Candidate laminated and monolithic transparent plastic mate- NTIS HC A13/MF A01 CSCL 01/3 rials for aircraft windshields subjected to supersonic aerodynamic Four wind tunnel model tests were conducted on a model heating and pressure are evaluated by wind tunnel testing at flex-strap bearmgless tail rotor for aeroelastic stability characteris- realistic Mach numbers and altitudes for high performance tics and loads In all. 12 individual rotor parameters were aircraft The reliability of the face-ply material is ascertained investigated to determine their effect on aeroelastic stability All and the transparency optical effects are assessed during flight data required to define the structural and aerodynamic characteris- operating conditions and as a result of these conditions tics of the basic model and structural data required to define Author (GRA) the test stand and drive system are presented In addition the physical properties required to describe the various parameters N78-21102j|l Naval Postgraduate School. Monterey. Calif are documented, thus providing a complete description of each REPORT ON AIRCRAFT FATIGUE STUDIES Interim Report. configuration tested The effect of each test parameter on the 1 Jul. 1976 - 30 Sep 1977

317 N78-21103

Gerald H Lmdsey 30 Sep 1977 36 p refs by the method of streamline tracing The high pressure and (AD-A049876. NPS-67LI77091) Avail NTIS temperature regions of the combustor were almost circular in HC A03/MF A01 CSCL 01/3 shape and thus the benefits of hoop stresses in relation to This report summarizes a year of research activity on aircraft structural weight could be utilized to reduce combustor and engine fatigue in three areas (1) The influence of minimum load levels, weights The engine had a center body consisting of a 20 deg ground loads, order of loading and counting method on the included angle cone followed by a constant diameter cylinder damage calculation. (2) The method of calculating local stress Fuel injection struts were arranged in a radial array and were in the plastic range at the stress concentration site from the swept 54 deg from the center body to the inlet inner surface recorded m-flight strain monitor and (3) The measurement of and had values of length to maximum average thickness between relaxation of residual stresses after they are produced locally at 5 6 and 6 6 which were felt to be structurally reasonable the point of stress concentration Substantial progress was made Combustor wetted areas were shown to be less than those of in all three areas and especially the first two Author (GRA) the present fully rectangular engine concept Author

N78-21103jjl Hindustan Aeronautics Ltd Bangalore (India) N78-21109*# National Aeronautics and Space Administration MULTI VARIATE OPTIMIZATION PROBLEMS OF FLIGHT Lewis Research Center Cleveland, Ohio VEHICLE SYNTHESIS GAS PATH SEALING IN TURBINE ENGINES Sndhar M Ramachandra Jan 1978 42 p refs Lawrence P Ludwig 1978 44 p refs Presented at AGARD (PB-276123/7) Avail NTIS HC A03/MF A01 CSCL QIC Power Energetics and Propulsion Panel Meeting on Seal Technol Attempts were made to delineate the multitechnology. in Gas Turbine Engines London. 6-7 Apr 1978 multi-vanate nature of the flight vehicle and the complex (NASA-TM-73890 E-9505) Avail NTIS HC A03/MF A01 interactions between the various areas involved in its synthesis CSCL 21E Considerations arising in the choice and configuration layout of A survey of gas path seals is presented with particular the hardware for tactical aircraft are outlined A brief mathematical attention given to sealing clearance effects on engine component formulation of a system oriented approach to design is proposed efficiency The effects on compressor pressure ratio and stall for optimizing the flight vehicle parameters GRA margin are pointed out Various case-rotor relative displacements, which affect gas path seal clearances are identified Forces produced by nonuniform sealing clearances and their effect on N78-21104*# National Aeronautics and Space Administration rotor stability are discussed qualitatively, and recent work on Langley Research Center Langley Station. Va turbme-blade-tip sealing for high temperature is described The RESULTS OF A SIMULATOR TEST COMPARING TWO need for active clearance control and for engine structural analysis DISPLAY CONCEPTS FOR PILOTED FLIGHT-PATH-ANGLE is discussed The functions of the internal-flow system and its CONTROL seals are reviewed Author Wendell W Kelley Mar 1978 23 p refs (NASA-TM-78692) Avail NTIS HC A02/MF A01 CSCL 01D Results of a simulator experiment which was conducted in N78-21112*# National Aeronautics and Space Administration order to compare pilot gamma-control performance using two Lewis Research Center Cleveland Ohio display formats are reported Pilots flew a variable flight path AIRFLOW AND THRUST CALIBRATION OF AN FIDO angle tracking task in the landing configuration Pilot and airplane ENGINE. S/N P680059. AT SELECTED FLIGHT CONDI- performance parameters were recorded and pilot comments TIONS noted for each case Author Thomas J Biesiadny, Douglas Lee and Jose R Rodriguez Apr 1978 27 p refs N78-21105# Rockwell International Corp Los Angeles Calif (NASA-TP-1069. E-9257) Avail NTIS HC A03/MF A01 Aircraft Div CSCL 21E FIBER OPTICS COST ANALYSIS PROGRAM (FOCAP) An airflow and thrust calibration of an F100 engine. S/N Final Report. 30 Jun 1976 - 30 Jun 1977 P680059 was conducted to study airframe propulsion system C C Zelon J E Cassidy and R G Shipley Sep 1977 255 p integration losses in turbofan-powered high-performance aircraft refs The tests were conducted with and without thrust augmenta- (Contract F33615-76-C-1260) tion for a variety of simulated flight conditions with emphasis (AD-A049859 NA-77-729 AFAL-TR-77-190) Avail NTIS on the transonic regime The resulting corrected airflow data HC A12/MF A01 CSCL 20/6 generalized into one curve with corrected fan speed while corrected The significance of this research is that it establishes methods gross thrust increased as simulated flight conditions increased for comparing the life cycle cost of fiber optics and wire data Overall agreement between measured data and computed results transfer systems on large military aircraft, and uses those methods was 1 percent for- corrected airflow and -1 1/2 percent for to perform cost analyses on the data transfer subsystems gross thrust The results of an uncertainty analysis are presented Using the B-1 as an example the applicability of fiber optics to for both parameters at each simulated flight condition Author the B-1 avionics/electrical systems was identified Conceptual fiber optics data transfer systems were designed The present wire and the conceptual fiber optics designs formed a basis for computerized life cycle cost comparisons Sensitivity analyses N78-21114*# National Aeronautics and Space Administration and cost trade-offs were performed to determine cost drivers in Lewis Research Center Cleveland Ohio the application of fiber optics Results show significance cost THEORETICAL FLOW CHARACTERISTICS OF INLETS FOR benefits can be gained by the implementation of fiber optics in TILTING NACELLE VTOL AIRCRAFT data transfer subsystems having data rates in excess of 2 to Michael A Boles Rogers W Luidens and Norhert 0 Stockman 3 megabits per second GRA Apr 1978 31 p refs (NASA-TP-1205 E-9387) Avail NTIS HC A03/MF A01 CSCL 21E N78-21107*# National Aeronautics and Space Administration The results of a theoretical investigation of geometric variables Langley Research Center Langley Station Va for lift-cruise-fan tilting nacelle inlets operating at high incidence RECTANGULAR CAPTURE AREA TO CIRCULAR COMBUS- angles are presented These geometric variables are investigated TOR SCRAMJET ENGINE for their effects on surface static to free stream pressure ratio, S Zane Pmckney Mar 1978 45 p refs and the separation parameters of maximum to diffuser exit surface (NASA-TM-78657) Avail NTIS HC A03/MF A01 CSCL21E velocity ratio and maximum surface Mach number for low speed A new concept for a scramjet engine design was presented operating conditions The geometric parameters varied were the The inlet transformed a rectangular shaped capture stream into internal lip contraction ratio, external forebody to diffuser exit a cross section which was almost circular in shape at the inlet diameter ratio external forebody length to diameter ratio and throat or combustor entrance The inlet inner surface was designed internal lip major to minor axis ratio Author

318 N78-21126

N78-21116*# Rao and Associates Inc Palo Alto Calif The design and operation of gas turbines at high turbine USE OF LEANING VANES IN A TWO STAGE FAN inlet temperatures are considered Emphasis is placed on turbine G V R Rao and R V Digumarthi Nov 1975 53 p refs cooling techniques high temperature materials and coatings (Contract NAS2-8680) combustors afterburners and nozzles the effect of cooling on (NASA-CR-152134) Avail NTIS HC A04/MF A01 CSCL aerodynamic performance and prediction methods 21E The use of leaning vanes for tone noise reduction was examined in terms of their application in a typical two-stage high pressure ratio fan In particular for stages designed with N78-2112O# Rolls-Royce Ltd Bristol (England) Aero Div outlet guide vanes and zero swirl between stages leaning the PROJECT OPTIMISATION OF MILITARY GAS TURBINES vanes of the first stage stator was studied since increasing the WITH RESPECT TO TURBINE LIFE number of vanes and the gap between stages do not provide E A White and M J Holland In AGARD High Temp Probl the desired advantage It was shown that noise reduction at in Gas Turbine Eng Feb 1978 17 p higher harmonics of blade passing frequency can be obtained by leaning the vanes Author Avail NTIS HC A25/MF A01 Computerized analytical techniques developed for examining the characteristics of high pressure turbine blades under the various stresses of operation are considered Emphasis is placed N78-21116*# Massachusetts Inst of Tech Cambridge on turbine service life and cooling requirements for military aircraft NITRIC OXIDE FORMATION IN GAS TURBINE ENGINES in terms of and developing a cost effective weapon system A THEORETICAL AND EXPERIMENTAL STUDY J M S Ph D Thesis - Nov 1975 Final Report Thomas Mikus. John B Heywood. and R Edward Hicks N78-21121# Turbomeca S A - Brevets Szydlowski. Bizanos Washington NASA Apr 1978 106 p refs (France) (Gram NGR-22-009-378) PROBLEMS CONCERNING HIGH TEMPERATURES IN (NASA-CB-2977) Avail NTIS HC A06/MF A01 CSCL 21E SMALL TURBOMACHINES [PROBLEMES DES HAUTES A modified Zeldovich kinetic scheme was used to predict TEMPERATURES DANS LES PETITES TURBOMACHINES] nitric oxide formation in the burned gases Nonumformmes in P Belaygue In AGARD High Temp Probl in Gas Turbine fuel-air ratio in the primary zone were accounted for by a Eng Feb 1978 12 p In FRENCH distribution of fuel-air ratios This was followed by one or more dilution zones in which^ Monte Carlo calculation was employed Avail NTIS HC A25/MF A01 to follow the mixing and dilution processes Predictions of NOX The power of small aeronautical turbomachmery is discussed emissions were compared with various available experimental in detail Problems arising from elevating temperature and pressure data and satisfactory agreement was achieved In particular at the turbine entrance which affect components such as the the model is applied to the NASA swirl-can modular combustor compressor as well as the combustion chamber and the turbine The operating characteristics of this combustor which can be were examined The aerodynamic and thermodynamic limita- inferred from the modeling predictions are described Parametric tions that occur due to this rise in temperature and pressure studies are presented which examine the influence of the modeling are also summarized in relation to the small dimensions of the parameters on the NOX emission level A series of flow components Transl by B B visualization experiments demonstrates the fuel droplet breakup and turbulent recirculation processes A tracer experiment N78-21125# Motoren- und Turbmen-Umon Muenchen GmbH quantitatively follows the jets from the swirler as they move (West Germany) downstream and entrain surrounding gases Techniques were HOT CASCADE TEST RESULTS OF COOLED TURBINE developed for calculating both fuel-air ratio and degree of BLADES AND THEIR APPLICATION TO ACTUAL ENGINE nonumformity from measurements of CO2 CO 02 and CONDITIONS hydrocarbons A burning experiment made use of these techniques H Koehler D K Hennecke. K Pfaff. and R Eggebrecht In to map out the flow field in terms of local equivalence ratio AGARD High Temp Probl in Gas Turbine Eng Feb 1978 and mixture nonumformity Author 12 p refs Avail NTIS HC A25/MF A01 N78-21117# Air Force Systems Command Wright-Patterson Experimental results of the cooling performance of various AFB Ohio convection and film cooled turbine blade models in a two FUEL PRESSURE INCREASE LIMITER dimensional stationary cascade are presented The Reynolds Yu M Akhmetov V I Bolshagm. A A Ryzhov V S Dyakonov number and the cooling air/ main stream mass flow ratio were and M A Medvedeva 26 Jul 1977 10 p Transl into ENGLISH varied within a range which is typical for turbine rotor blades in from Patent (USSR) no 339672 24 May 1972 p 1-2 let engines From the analysis of the test results basic under- (AD-A049393 FTD-ID(RS)T-1249-77) Avail NTIS standing about the characteristics of cooling effectiveness and HC A02/MF A01 CSCL 01/3 about the distribution of the hot gas side heat transfer coefficient The invention belongs to the field of the automatic control was obtained In applying model test results to a real engine of turbojet engines in particular to fuel pressure increase Irmiters the differences between cascade and engine conditions for Known are fuel pressure increase limiters predominantly for a example the rotation and the changed radiation environment turbojet engine which contain a spring-opposed servopiston with are taken into account Some engine phenomena, such as free a rod, the cavities of which are connected by channels with a stream turbulence which still have a largely unknown influence constant pressure valve and a control slid valve The purpose on heat transfer processes, are discussed Blade temperature of the invention is to provide the optimal rate of pressure from engine tests are compared with cascade test results and increase To do this made in the rod are additional channels theoretical temperature distributions For a simulated engine connected to both cavities of the servodnve by means of holes acceleration process the temperature and the stress distribu- which are provided in its body GRA tions in the mid-section of a turbine blade was computed using a time dependent finite element program The results which serve as a basis for a comparative blade live assessment show that, N78-21118# Advisory Group for Aerospace Research and during the transient phase the mechanical loading of the blade Development. Pans (France) by far exceeds the steady state valves Author HIGH TEMPERATURE PROBLEMS IN GAS TURBINE ENGINES Feb 1978 585 p refs Presented at the 50th Meeting of the N78-21126# Technische Hochschule. Aachen (West Germany) AGARD Propulsion and Energetics Panel Ankara 19-23 Sep Inst fuer Strahlantnebe und Turboarbeitsmaschmen 1977 INVESTIGATIONS OF THE LOCAL HEAT TRANSFER (AGARD-CP-229 ISBN-92-835-0209-4) Avail NTIS COEFFICIENT OF A CONVECTION COOLED ROTOR HC A2S/MF A01 BLADE

319 N78-21127

W Kuehl In AGARD High Temp Probl in Gas Turbine Eng The external boundary layer and the heat transfer distribution Feb 1978 11 p refs of a film cooled turbine blade are calculated Results are used Avail NTIS HC A25/MF A01 to determine the necessary film injection rate when the airfoil Temperature measurements made within the convection air shape the external gas and the desired blade temperature are cooled rotor blade of a gas turbine during operation are used to specified JMS determine the local heat transfer coefficients of turbine blades The analytical method is described along with results which include the local gas side heat transfer and the complete temperature N78-21131| National Gas Turbine Establishment. Pyestock field within the blade Unsteady flow effects are discussed (England) JMS EXPERIMENTAL EVALUATION OF A TRANSPIRATION COOLED NOZZLE GUIDE VANE W H Morns J B Bullard and L D Wigg In AGARD High N78-21127# Deutsche Forschungs- und Versuchsanstalt fuer Temp Probl in Gas Turbine Eng Feb 1978 15 p refs Luft- und Raumfahrt. Cologne (West Germany) Inst fuer Antnebstechnik Avail NTIS HC A25/MF A01 INVESTIGATION ON TEMPERATURE DISTRIBUTION NEAR The design and experimental evaluation of a transpiration FILM COOLED AIRFOILS cooled nozzle guide vane is described The thermal evaluation H Kruse In AGARD High Temp Probl in Gas Turbine Eng of the coolant system design at gas temperature up to 1615 K Feb 1978 13 p indicated achievment of design effectiveness levels and good Avail NTIS HC A25/MF A01 uniformity of temperature distribution However the effect of Using a practically adiabatic airfoil as a simple model of a transpiring flow on turbine stage efficiency was to bring about turbine blade some typical film cooling configurations were a significant loss in performance relative to an uncooled nozzle investigated The dimensions and operating conditions were a loss of about 5 per cent in efficiency at a coolant mass flow chosen so that both the Reynolds numbers and the ratio of ratio of 3 per cent was observed Application of the experimen- hole diameter to boundary layer thickness would correspond to tal data to transpiration cooling of nozzle guide vanes is realistic values in the turbine The temperature ratio between discussed Author the mainstream and the coolant was in the range of 1 25 in order to get reasonable temperature differences The temperature distributions within the gas and on the adiabatic wall were N78-21132| Technische Hogeschool Delft (Netherlands) Lab voor Verbrandingsmotoren en Gas-turbines measured by means of miniaturized thermocouples Information is given on the distribution of film cooling effectiveness and on HEAT TRANSFER CHARACTERISTICS OF THE CLOSED the distribution of temperature in the near region downstream THERMOSYPHON SYSTEM R W Stuart-Mitchell and J Andnes In AGARD High Temp of the blowing point To point out the influence of curvature Probl in Gas Turbine Eng Feb 1978 13 p refs near the nose of the airfoil some typical results were compared with those from flat plate measurements Author Avail NTIS HC A25/MF A01 A closed thermosyphon system of gas turbine blade cooling N78-21128# Middle East Technical Univ , Ankara (Turkey) Dept using liquid metals and a secondary cooling circuit in a blade of Mechanical Engineering root_was studied Experimentally determined heat transfer EROSION PREVENTION AND FILM COOLING ON VANES characteristics were determined for a 106 mm diameter cylindrical M Saryal I M Chantous and A Citici In AGARD High closed thermosyphon with a length diameter ratio 1161 and a Temp Probl in Gas Turbine Eng Feb 1978 8 p refs heated-to cooled-length ratio of 1 1 using water and mercury under a uniform heat flux hot wall boundary condition Results Avail NTIS HC A25/MF A01 were obtained with the thermosyphon stationary and variously A preliminary research on the behavior of solid particles angled to the vertical between 0 deg and 45 deg and mounted approaching a cascade of leaf nozzles having air injected through in a rotating arm apparatus at rotational speeds between a slit at the leading edge, was carried out The results showed 500 rpm and 1000 rpm The results from the rotating a definite prevention of erosion of solid particles at the leading experiments were correlated using a Grashof Number based on edge region and the blade shoulder The only vulnerable region the gravitational acceleration while the centrifugal acceleration was the pressure side trailing edge region The ability of this was included in a third dimensionless parameter Comparison of method to provide means for effective cooling of gas turbine the results from the stationary and rotating experiments shows blades and possibilities of pulverized coal direct firming were that angling the stationary thermosyphon to the vertical does studied Results are summarized Author not simulate the heat transfer in the rotating thermosyphon Author N78-21129jjl Sussex Univ. Brighton (England) Dept of Mechanical Engineering N78-21134# Centre de Villaroche Moissy (France) Dept PERFORMANCE AND DESIGN OF TRANSPIRATION- Combustion-Pollution-Rechauffe COOLED TURBINE BLADING A REVIEW OF TECHNIQUES FOR THE THERMAL PROTEC- F J Bayley In AGARD High Temp Probl in Gas Turbine TION OF THE WALLS OF THE COMBUSTION CHAMBER Eng Feb 1978 15 p refs AND REHEATING DUCTS OF TURBOREACTORS [REVUE DES TECHNIQUES DE PROTECTION THERMIQUE DES Avail NTIS HC A25/MF A01 PAROIS DES FOYER PRINCIPAUX ET DE RECHAUFFE DES Experimental and theoretical studies of transpiration cooled TURBOREACTEURS] turbine blades are reviewed and a design method for such cooling M Buisson, J P Gaillac. and B Deroide In AGARD High system is proposed An integral boundary layer method of analysis Temp Probl in Gas Turbine Eng Feb 1978 15 p refs In is shown to produce good agreement between observed and FRENCH predicted heat transfer coefficients over most of the blade section Avail NTIS HC A25/MF A01 where the effect of the coolant flow is significant while a simple Techniques and limitations involved in the recooling of the momentum-mixing theory appears adequate for assessing the combustion chamber in turboreactors were reviewed A critical effect of the coolant on the blade profile loss Author analysis of classical solutions such as forced convection and film recooling showed the necessity for the utilization for more elaborate procedures, which include more simplified calcula- N78-21130# Ohio State Univ. Columbus tions Transl by B B THE INFLUENCE OF TRANSPIRATION COOLING ON TURBINE BLADE BOUNDARY LAYER Lit S Han and Leon Wmget In AGARD High Temp Probl in N78-21136# Lucas Aerospace Ltd Burnley (England) Fabrica- Gas Turbine Eng Feb 1978 14 p refs Sponsored in part by tions Div AF PRACTICAL SOLUTIONS TO THE COOLING OF COMBUS- Avail NTIS HC A25/MF A01 TORS OPERATING AT HIGH TEMPERATURES

320 N78-21143

J Winter and H Todd In AGARD High Temp Probl in Gas N78-21139# Office National d Etudes et de Recherches Turbine Eng Feb 1978 14 p Aerospatiales Paris (France) NEW MATERIALS FOR HIGH TEMPERATURE TURBINES Avail NTIS HC A2S/MF A01 ONERA'S OS COMPOSITES CONFRONTED WITH THE Flame tube life potential for small gas turbine engine BLADE PROBLEMS applications where high temperature operating conditions occur Herve Bibrmg In AGARD High Temp Probl in Gas Turbine was studied A small annular reverse flow combustion chamber Eng Feb 1978 12 p refs In FRENCH ENGLISH summary was developed which utilizes a high proportion of the incoming air for wall film cooling purposes prior to the redirection of the Avail NTIS HC A25/MF A01 cooling air for combustion and mixing The concept is shown to The needs required for a blade material in aircraft turbines minimize the cooling difficulties encountered on conventional small operating at higher temperatures are compared with the actual annular chambers particularly when operating at elevated turbine performance as found on Cotac DS composites testing The entry temperatures A combustor developed for a regenerative structure and the properties of the more fully developed 74 and gas turbine engine where impingement cooling liners are employed 741 types are discussed In particular the high temperature to overcome problems of high metal temperatures on a low structural stability, the impact of thermal and mechanical fatigue cost unit is described Author the oxidation resistance and the coating capability are thoroughly evaluated The great benefit in operational temperature of these materials can be immediately exploited in the field of uncooled N78-21136# Technische Hochschule Darmstadt (West Ger- solid blades The problem of cooling passages in DS eutectic many) Inst fuer Technische Thermodynamik blades is also outlined Author THE INFLUENCE OF COOLANT TURBULENCE INTENSITY ON FILM COOLING EFFECTIVENESS R Best In AGARD High Temp Probl in Gas Turbine Eng Feb 1978 14 p refs N78-21141# Office National d Etudes et de Recherches Avail NTIS HC A25/MF A01 Aerospatiales. Pans (France) In pipe flow experiments cold air was injected tangentially PROTECTION OF COOLED BLADES OF COMPLEX INTER- to the tube wall of the test section through an annular slot into NAL STRUCTURE a hot fully developed turbulent pipe flow The adiabatic wall Philippe Galmiche /" AGARD High Temp Probl in Gas Turbine temperature was measured along the pipe length for different Eng Feb 1978 9 p refs In FRENCH ENGLISH summary velocity ratios injection slot heights, and degrees of turbulence of coolant and main streams Simultaneously the velocity and Avail NTIS HC A25/MF A01 the temperature profiles as well as the distribution of the turbulent The problem of the general protection of cooled blades of fluctuation velocities were measured The measurements indicate complex internal structure was studied A corresponding method that an increasing turbulence intensity of the coolant can called the SF technique, permits the realization in a single operation significantly reduce film cooling effectiveness By means of of the protection of both external and internal surfaces, as well turbulent fluctuation velocity measurements and a physical model as those of the orifices of cooling air, whatever their diameter the film cooling effectiveness can be calculated The derived In a general way, the respective thickness of external and internal correlations reveal cooling effectiveness with increasing turbulence coatings may be precisely predetermined, with no parasitic particle There is good agreement between experiments and theoretical being able to remain inside the parts after application of the predictions Author protecting treatment Results obtained by application of the SF method are illustrated by the presentation and examination of N78-21137# Centra per I Automatica E Piaggio Pisa (Italy) various parts of advanced turbomachmes which were handed HIGH TEMPERATURE H2-AIR VARIABLE GEOMETRY over for treatment followed by tests or operational use by engine COMBUSTOR AND TURBINE TEST FACILITY AND manufacturers or airlines Author MEASUREMENTS L Martorano and D Dim In AGARD High Temp Probl in Gas Turbine Eng Feb 1978 10 p refs N78-21142# Advisory Group for Aerospace Research and Development. Paris (France) Avail NTIS HC A25/MF A01 COBALT-BASE ALLOYS FOR HOT CORROSION PROTEC- A design concept for gas turbine H2-air combustor is TIVE COATINGS presented and its potential verified by experimental data The A Davm (CRM Liege Belgium). J M Drapier (CRM, Liege combustor performance with a view to the use of H2-air in Belgium) D Coutsouradis (CRM. Liege Belgium), and L Habraken conventional variable geometry gas turbines was emphasized In its High Temp Probl in Gas Turbine Eng Feb 1978 12 p Proposals and development for varying and controlling the air refs flow distribution characteristics appeal feasible Results are given Avail NTIS HC A25/MF A01 of the first high temperature tests carried out on variable geometry In the field of gas turbine applications the severe requirements combustor and turbine bladmg Author of extended operation in marine environments or an increase in the inlet temperature limit the life of the diffusion alummide N78-21138# Air Force Aero Propulsion Lab Wright-Patterson base coatings for nickel and cobalt superalloys Protective overlay AFB Ohio coatings such as Co/Ni-Cr-AI-Y-Ta were developed in order to LOW FREQUENCY COMBUSTION INSTABILITY IN AUG- satisfy the requirements of the gas turbine designers and showed MENTORS an exceptional hot corrosion resistance They were optimized to F N Underwood J P Rusnak (Pratt and Whitney Aircraft West obtain an acceptable compromise between hot corrosion and Palm Beach Fla I R C Ernst (Pratt and Whitney Aircraft. West thermal shock resistance Experience gained with the develop- Palm Beach. Fla). E A Petrmo (Pratt and Whitney Aircraft. ment of such cobalt base and particularly Co-AI-Cr-Ta-Ni-Y alloys West Palm Beach Fla ) P L Russell (Pratt and Whitney Aircraft. and corresponding coatings were evaluated by various tech- West Palm Beach Fla) and R Murphy Jr In AGARD High niques Author Temp Probl in Gas Turbine Eng Feb 1978 19 p ref N78-21143# Pratt and Whitney Aircraft Group West Palm Avail NTIS HC A25/MF A01 Beach, Fla Government Products Div An analytical model was developed to aid in designing TRENDS OF FUTURE TURBINE LIFE PREDICTION TIME afterburners that are free from low frequency instability Rumble PHASE AUTOMATED ANALYSIS AND TEST VERIFICA- mechanisms investigated include the system airflow dynamics, TION combustion efficiency oscillations fuel vaporization recirculation J L Price and I J Gershon (AFAPL) In AGARD High Temp wake energy, and turbulence upstream of the flameholders Probl in Gas Turbine Eng Feb 1978 11 p refs Comparisons of the model predictions with experimental data are good Author Avail NTIS HC A02/MF A01

321 N78-21145

A review of the most significant design parameters affecting In a case of a stator cascade the influence or jets of coolant turbine durability and the structural analysis and verification air on the aerodynamic behavior was tested The jets exhaust techniques which are being developed for identification of from the trailing edges of four blades By the evaluation of structural inadequacies early in th propulsion system development wake flow measurements over two pitches the losses and the cycle are reviewed Author downstream flow angle were determined In addition schlieren pictures were taken The downstream velocity was varied from a subsonic over a transonic up to a supersonic flow The rate N78-21146# Lucas Aerospace Ltd Burnley (England) Fabrica- of the coolant air with respect to the primary air running through tions Div two adjacent blades was changed from zero to four percent EVALUATION OF A CERAMIC COMBUSTION CHAMBER The measurements were carried out in the wind tunnel for two FOR A SMALL GAS TURBINE ENGINE dimensional cascades Author G Sedgwick In AGARD High Temp Probl in Gas Turbine Eng Feb 1978 10 p refs N78-21151# Office National d Etudes et de Recherches Aerospatiales Paris (France) Avail NTIS HC A25/MF A01 MEASURING TECHNIQUES IN HIGH TEMPERATURE A description is presented of the design component evaluation TURBINES and combustion testing of a reverse flow annular combustion Yves LeBot Marc Charpenel, and Pierre-Jacques Michard In chamber in silicon nitride Heat transfer assessments were made AGARD High Temp Probl in Gas Turbine Eng Feb 1978 of the temperature levels which components would reach during 12 p refs In FRENCH ENGLISH summary combustion testing A thermal test program was formulated which enables thermal loadings well in excess of those estimated Avail NTIS HC A25/MF A01 for the actual flame tube environment to be imposed upon An instrument for performing on industrial machines specimen components Thermal stress and probability of survival measurements usually limited to laboratory studies was developed values were obtained using the method based on a Weibull Qualifications of the flow turbulence is described and an analysis statistical analysis using the weakest link volume critical flaw of moble blade wakes by short response time pressure probes assumption Finite element and brittle failure analyses were carried was included Flow temperature fluctuations by thermocouple or out on both thermal stress test specimens and the components resistor probes associated to signal processing electronics and making up the flame tube Author by optical pyrometry were studied Mobile blade surface temperatures were read by short response time optical pyrometry N78-21146jjf Massachusetts Inst of Tech Cambridge The local thermal transfer coefficient on stator blades was SYSTEMATIC STUDIES OF HEAT TRANSFER AND FILM measured by an analysis of evolution in time of the wall COOLING EFFECTIVENESS temperature after sudden cutting off of cooling air The J F Louis In AGARD High Temp Probl in Gas Turbine Eng effectiveness of the wall thermal protection from results of a Feb 1978 36 p refs chromatographic analysis of gaseous samples was also calcu- (Contracts F33625-76-C-2018 N00014-76-C-0253) lated The main characteristics of the instrumentation are presented Avail NTIS HC A25/MF A01 and illustrated by examples of application on various test A review of studies in heat transfer and film cooling facilities Author effectiveness was given to develop an in depth understanding of heat transfer and film cooling in gas turbines A common N78-21162# Von Karman Inst for Fluid Dynamics Rhode-Samt- experimental procedure is described for heat transfer measure- Genese (Belgium) ments under isothermal wall conditions using fast response heat THE MEASUREMENT OF FILM COOLING EFFECTIVENESS transfer gauges in tests conducted in a shock tunnel and a ON TURBINE COMPONENTS IN SHORT DURATION WIND blowdown facility The tests were conducted at flow and thermodynamic conditions modeling the operating conditions of TUNNELS J P Ville and B E Richards In AGARD High Temp Probl in advanced gas turbines The configurations under study were single Gas Turbine Eng Feb 1978 13 p refs In ENGLISH FRENCH slot single line of holes, double line of holes on a flat plate, summary and double line of holes on an airfoil Author (Grant DA-ERO-75-G-074) Avail NTIS HC A25/MF A01 N78-21147*# General Electric Co Evendale Ohio Aircraft A method to measure an adiabatic wall effectiveness, n Engine Group and its associated heat transfer coefficient h, of a film cooling EFFECTS OF FILM INJECTION ON PERFORMANCE OF A system for turbine components in a short duration facility is COOLED TURBINE described Such a facility was used to provide flow conditions James D McDonel and James E Eiswerth In AGARD High selected to simulate those of advanced aircraft turbines The Temp Probl in Gas Turbine Eng Feb 1978 11 p refs measurement of heat transfer rates under different coolant temperature conditions and the definition of a linear relationship (Contract NAS3-16732) between a heat transfer coefficient h, based on mainstream Avail NTIS HC A25/MF A01 recovery temperature and a nondimensional coolant tempera- Tests were conducted in a 20 inch diameter single stage ture, leads to the evaluation of n. and h sub f The measurements air cooled turbine designed to evaluate the effects of film cooling on a flat plate, cooled by air ejected through inclined holes at a air on turbine aerodynamic performance A comparison was made Mach number of 0 6 unit Reynolds number of 2 4 x 10 to the of the experimental results and an analytical method of evaluating 7th power per meter wall to mainstream temperature ratio of film injection effects on turbine performance The results are 0 76 coolant to mainstream temperature of 0 70 to 0 95 and used to determine the effects of film cooling on overall engine mass velocity ratio from 0 5 to 15 confirm the linearity of the performance for selected cycle conditions The engine performance h theta relation and prove the ability of a short duration facility studies are used to show the cycle benefits of increased gas to provide useful film cooling data for blade cooling system temperature at various coolant flow rates Author development Author

N78-21148# Deutsche Forschungs- und Versuchsanstalt fuer N78-21154# Office National d Etudes et de Recherches Luft- und Raumfahrt. Goettmgen (West Germany) Aerospatiales, Paris (France) THE INFLUENCE OF JETS OF COOLING AIR EXHAUSTED NEW COMPUTATION METHOD OF TURBINE BLADES FILM FROM THE TRAILING EDGES OF A SUPERCRITICAL COOLING EFFICIENCY TURBINE CASCADE ON THE AERODYNAMIC DATA Emile LeGrives and Jacques Jules Nicolas In AGARD High Ortwm Lawnczeck In AGARD High Temp Probl in Gas Turbine Temp Probl in Gas Turbine Eng Feb 1978 12 p refs In Eng Feb 1978 13 p refs FRENCH ENGLISH summary

Avail NTIS HC A25/MF A01 Avail NTIS HC A25/MF A01

322 N78-21163

An analytical technique is presented for the computation of to compensate for angle of attack sensitivity and the altitude film cooling effectiveness of gas turbine blades It is based on a error and integral altitude gams were reduced Good Mach hold mathematical description of the counter rotating vortex structure performance was obtained when the angle of attack sensitivity associated with the injection of coolant through discrete holes was removed, however the ride qualities remained poor Author The transport of mass induced by these vortices plays the major part in the mixing process of hot gas with the individual jets which defines the adiabattc effectiveness of the resulting N78-21161*# Princeton Univ N J Instrumentation and film When merging of the jets and entramment by turbulent Control Lab diffusion effects were also taken into account data from various OPTIMAL CONTROL THEORY (OWEM) APPLIED TO A experiments performed on flat plate were found to be in good HELICOPTER IN THE HOVER AND APPROACH PHASE agreement with predictions following this approach Simple rules Gerard J Born and Tadao Kai Jan 1975 289 p refs for computing film effectiveness with injection through several (Contract NAS2-7187) rows of holes allow an extension of the analysis to a large (NASA-CR-152135 Rept-1205) Avail NTIS variety Of injection patterns Author HC A13/MF A01 CSCL 01C A major difficulty in the practical application of linear- N78-21155# Sussex Univ Brighton (England) Dept of quadratic regulator theory is how to choose the weighting matrices Mechanical Engineering in quadratic cost functions The control system design with optimal THE EFFECT Of FREE-STREAM TURBULENCE UPON HEAT weighting matrices was applied to a helicopter in the hover and TRANSFER TO TURBINE BLADING approach phase The weighting matrices were calculated to F J Bayley and R W Milligan In AGARD High Temp Probl extremize the closed loop total system damping subject to in Gas Turbine Eng Feb 1978 13 p ref constraints on the determinants The extremization is really a minimization of the effects of disturbances and interpreted as a Avail NTIS HC A25/MF A01 compromise between the generalized system accuracy and the An initial investigation of the separate effects of free stream generalized system response speed The trade-off between the turbulence intensity and frequency upon the local heat transfer accuracy and the response speed is adjusted by a single parameter to a heavily loaded gas turbine blade section is described It the ratio of determinants By this approach an objective measure was shown that over the whole blade the rate of heat transfer can be obtained for the design of a control system The measure is significantly increased by both those parameters with the is to be determined by the system requirements Author pressure surface showing the greatest response and the downstream half of the suction surface the least Author

N78-21162# Michigan Univ Ann Arbor Dept of Aerospace N78-21157| Pisa Univ (Italy) Dept of Engineering Engineering CALCULATION OF TEMPERATURE DISTRIBUTION IN SYSTEM OPTIMIZATION BY PERIODIC CONTROL Interim DISKS AND COOLING FLOW IN A TRANSIENT STATE M Caprili and R Lazzeretti In AGARD High Temp Probl m Scientific Report. 1 Oct 1976 - 1 Oct 1977 Elmer G Gilbert 1977 6 p refs Gas Turbine Eng Feb 1978 23 p refs (Gram AF-AFOSR-3158-77) (AD-A049522 AFOSR-78-0012TR) Avail NTIS Avail NTIS HC A25/MF A01 HC A02/MF A01 CSCL 01/3 The temperature distribution in irregularly shaped disks and Research was conducted in two areas the theory and that of the cooling fluid was determined for a transient stator computation of periodic controls, and the input-output charac- The method of calculation used is described, and the stability of terization of nonlinear systems The effort on periodic control the numerical solution is discussed The calculation program makes was devoted almost entirely to sufficient conditions for optimality it possible to evaluate the influence of the functional parame- a computational study of periodic aircraft cruise the use of ters on temperature distribution Author vanational models for analyzing the effect of system nonlmeanties in the presence of periodic forcing The investigation of input- output characterizations for nonlinear systems was extended to N78-21159*# National Aeronautics and Space Administration the realization problem for nonlinear systems Author (GRA) Ames Research Center Moffett Field Calif A NOTE ON MULTICYCLIC CONTROL BY SWASHPLATE OSCILLATION James C Biggers and John L McCloud III Apr 1978 11 p refs N78-21163# Boeing Vertol Co. Philadelphia. Pa (NASA-TM-78475 A-7367) Avail NTIS HC A02/MF A01 HEAVY LIFT HELICOPTER FLIGHT CONTROL SYSTEM CSCL 01C VOLUME 2 PRIMARY FLIGHT CONTROL SYSTEM It was shown that for two three, or four bladed rotors DEVELOPMENT AND FEASIBILITY DEMONSTRATION simple oscillation of the nonrotating swashplate controls can Final Report. Jul 1971 - Jul 1975 produce prescribed blade pitch schedules of the sort which were T H Sanders and B L McManus Sep 1977 122 p refs suggested for vibration alleviation Equations were given which (Contract DAAJ01-71-C-0840) relate the swashplate motions to the resulting blade pitch (AD-A049580 USAAMRDL-TR-77-40B-Vol-2) Avail NTIS schedules Author HC A06/MF A01 CSCL 01/3 The U S Army s Heavy Lift Helicopter Advanced Technology N78-2116O*# National Aeronautics and Space Administration Component Program required the design, development and inflight Hugh L Dryden Flight Research Center. Edwards Calif feasibility demonstration of an electrohydraulic flight control RESULTS FROM FLIGHT AND SIMULATOR STUDIES OF system referred to as fly-by-wire Total flight testing encom- A MACH 3 CRUISE LONGITUDINAL AUTOPILOT passed evaluation and demonstration in two parts First, a direct Glenn 8 Gilyard and John W Smith Apr 1978 85 p refs electrical linkage was successfully demonstrated in September (NASA-TP-1180 H-940) Avail NTIS HC A05/MF A01 CSCL 1973 Subsequently an automatic flight control system was 01D installed and evaluated with the direct electrical linkage This At Mach numbers of approximately 3 0 and altitudes greater volume describes the primary flight control system its design than 21 300 meters the original altitude and Mach hold modes features installation test Included also is a report of a related of the YF-12 autopilot produced aircraft excursions that were activity to design and evaluate in laboratory tests a compatible erratic or divergent or both Flight data analysis and simulator cockpit controller subsystem in which pilot commands are studies showed that the sensitivity of the static pressure port to converted to electrical signals Standard pilot interface features, angle of attack had a detrimental effect on the performance of such as magnetic brakes stick position trim and force trim are the altitude and Mach hold modes Good altitude hold performance included To interface with the automatic flight control system, was obtained when a high passed pitch rate feedback was added controller driver actuators are included GRA

323 N78-21164

N78-21164# Boeing Vertol Co. Philadelphia Pa under the major categories of asphalt- or tar-surfaced pavements HEAVY LIFT HELICOPTER FLIGHT CONTROL SYSTEM and jointed concrete pavements Names descriptions, seventy VOLUME 3 AUTOMATIC FLIGHT CONTROL SYSTEM levels photographs, and measurement or count criteria are DEVELOPMENT AND FEASIBILITY DEMONSTRATION presented for each distress type Author (GRA) Final Report. Jul 1971 - Jul 1975 J Davis T Barnett and J Gaul Sep 1977 705 p refs N78-21214*# National Aeronautics and Space Administration (Contract DAAJ01-71-C-0840) Ames Research Center, Moffett Field Calif (AD-A050059 USAAMRDL-TR-77-40C-Vol-3) Avail NTIS FIRE RESISTIVITY AND TOXICITY STUDIES OF CANDI- HC A99/MF A01 CSCL 01/3 DATE AIRCRAFT PASSENGER SEAT MATERIALS The U S Army Heavy Lift Helicopter Advanced Technology L L Fewell Ed Trabold (McDonnell Douglas Corp Long Beach Component program required the design development and Calif), and H Spieth (McDonnell Douglas Corp Long Beach feasibility demonstration of an electrohydraulic flight control Calif) Mar 1978 44 p refs system This volume details the evolution of an automatic flight (NASA-TM-78468 A-7334) Avail NTIS HC A03/MF A01 control system (AFCS) operating by means of a direct electrical CSCL 218 linkage AFCS software and hardware development and testing Fire resistivity studies were conducted on a wide range of are discussed The results of flight clearance testing and in-flight candidate nonmetallic materials being considered for the evaluations of AFCS control laws are examined GRA construction of improved fire resistant aircraft passenger seats N78-2116S# Air Force Civil Engineering Center Tyndall AFB These materials were evaluated on the basis of FAA airworthiness Fla burn and smoke generation tests colorfastness, limiting oxygen RUNWAY ROUGHNESS EVALUATION LASER PROFI- index and animal toxicity tests Physical mechanical, and aesthetic LOMETER IMPLEMENTATION STUDY Final Report. Nov properties were also assessed Candidate seat materials that have 1976 - Sep 1977 significantly improved thermal response to various thermal loads Dannie O Burk and James I Clark Oct 1977 66 p refs corresponding to reasonable fire threats as they relate to (AD-A049440. AFCEC-TR-78-1) Avail NTIS in-flight fire situations are identified Author HC A04/MF A01 CSCL 20/5 Runway profiles and aircraft vertical acceleration responses N78-21223*# Douglas Aircraft Co Inc Long Beach Calif were analyzed to develop an evaluation methodology *or runway AIRCRAFT CARGO COMPARTMENT FIRE TEST SIMULA- roughness and to develop roughness standards against which TION PROGRAM Final Report. Oct 1974 - Jan 1977 runways can be evaluated Root mean square values of filtered R E Blumke Jan 1977 84 p refs profile data and vertical aircraft accelerations were statistically (Contract NAS2-8699) developed on a segmental basis into runway roughness standards (NASA-CR-151951 MDC-J7471) Avail NTIS A methodology was developed to evaluate runway profiles against HC A05/MF A01 CSCL 11D these standards, and to recommend corrective construction of The objective of the test was to assess fire containment the profile to reduce aircraft response Profile roughness has and fire extinguishment in the cargo by reducing the ventilation therefore been based on a numerically relative basis The through the cargo compartment Parameters which were measured establishment of runway roughness standards and evaluation included ignition time burnthrough time, and physical damage methodology is considered incomplete, and additional work is to the cargo liner composition of selected combustible gases, recommended in this report Author (GRA) temperature-time histories heat flux, and detector response The ignitor load was made of a typical cargo consisting of filled N78-21166# Naval Postgraduate School. Monterey Calif cardboard cartons occupying 50% of the compartment volume A SUB-SCALE TURBOJET TEST CELL FOR DESIGN Author EVALUATIONS AND ANALYTICAL MODEL VALIDATION Interim Report N78-21234| National Bureau of Standards. Washington D C Holden W Hewlett P J Hickey and David W Netzer Sep Center for Fire Research 1977 48 p refs TIME-DEPENDENT FIRE BEHAVIOR OF AIRCRAFT CABIN (AD-A049862 NPS-67NT77091) Avail NTIS MATERIALS Final Report. Mar 1976 - Jun 1977 HC A03/MF A01 CSCL 14/2 Clayton Huggett Dec 1977 42 p refs A one-eighth scale (1/64 scale on mass flow) NARF Alameda (Contract DOT-FA76WAI-610) turbojet test cell was designed and constructed The test cell is (AD-A050923 FAA-RD-77-99) Avail NTIS to be employed for evaluation of optimum augmentor design HC A03/MF A01 CSCL 01/3 and pollution abatement methods and for validation of analyti- In an aircraft cabin or other inhabited compartment the cal models Initial evaluation of the test cell demonstrated its early stages of fire growth are critical to life safety During this versatility and ease of operation as well as some deficiencies period the rate of fire growth as measured by the mass fuel Model operating characteristics and planned investigations are consumption rate can be represented approximately as a simple discussed GRA exponential function of time The rates of development of hazard from temperature rise and smoke and gas accumulation can be related to the mass fuel consumption rate The growth constant N78-21170f Army Construction Engineering Research Lab. k can be related to a small number of system parameters and Champaign, III fuel combustion properties These properties were identified and DEVELOPMENT OF A PAVEMENT MAINTENANCE MAN- laboratory methods for their measurement are suggested In a AGEMENT SYSTEM VOLUME 2 AIRFIELD PAVEMENT fire situation the critical hazard (temperature smoke or gas) DISTRESS IDENTIFICATION MANUAL Final Report. Jul can be considered to be the one which first reaches a limiting 1974 - Jul 1976 human tolerance level This mode can be identified and the Mohamed Y Shahm Michael I Darter, and Starr D Kohn Tyndall effects of changes in design and materials on the rate of critical AFB. Fla Civil and Environ Eng Develop Office Dec 1977 hazard development can be estimated The simple exponential 115 p Supersedes AFCEC-TR-76-27-Vol-2 growth model may provide a means of predicting relative hazard (AF MIPR-FQ8952-76-66005) with reasonable accuracy Author (AD-A049029. CERL-TR-C-76-Vol-2 CEEDO-TR-77-44-Vol-2. AFCEC-TR-76-27-Vol-2) Avail NTIS HC A06/MF A01 CSCL N78-21326*# Michigan Umv . Ann Arbor Dept of Applied 01/5 Mechanics and Engineering Science This manual is designed to provide airfield pavement DEFINITION OF TIRE PROPERTIES REQUIRED FOR inspectors with a comprehensive reference for pavement distress LANDING SYSTEM ANALYSIS Final Report identification The information is to be used in conjunction with S K dark. R N Dodge, and J R Luchmi Mar 1978 26 p procedures presented in Volume I of this report to determine (Grant NsG-1080) pavement condition and maintenance and repair requirements (NASA-CR-156171 UMICH-012881) Avail NTIS The types of airfield pavement distress are listed alphabetically HC A03/MF A01 CSCL 14D

324 N78-21473

The data bank constructed provided two basic advantages preventing the severe airflow included (Da two foot extension for the user of aircraft tire information First computerization of of the radiometer housing (2) a one foot extension of the the data bank allowed mechanical property data to be stored, radiometer with either an asymmetric set of deflectors on the corrected updated, and revised quickly and easily as more reliable present nose or (3) a larger scooped shaped nose JMS tests and measurements were carried out Secondly, the format of tne book which can be printed from the computerized data N78-21410*# National Aeronautics and Space Administration bank can be easily adjusted to suit the needs of the users Langley Research Center Langley Station. Va without the great expense normally associated with reprinting CORRELATION OF LASER VELOCIMETER MEASURE- and editing books set by ordinary typography Author MENTS OVER A WING WITH RESULTS OF TWO PREDIC- TION TECHNIQUES N78-21368| McDonnell-Douglas Corp St Louis. Mo Danny R Hoad. James F Meyers. Warren H Young, Jr. and HF RADIATION CHARACTERISTICS OF THE RH-63D Timothy P Hepner Apr 1978 66 p refs HELICOPTER AND THE MARK 106 AMCM SYSTEM (DA Proj 1L1-61102-AH-45) Final Report. 1 Nov. 1976 - 1 Feb 1977 (NASA-TP-1168 L-11980) Avail NTIS HC A04/MF A01 L N Medgyesi-Mitschang Feb 1977 44 p refs CSCL 20D (Contract N61331-76-M4839) The flow field at the center line of an unswept wing with (AD-A049795 MDC-Q0616) Avail NTIS HC A03/MF A01 an aspect ratio of eight was determined using a two dimensional CSCL 09/5 viscous flow prediction technique for the flow field,calculation, A computer algorithm is used to predict the power gain and a three dimensional potential flow panel method to evaluate and phase characteristics of the Raydist receiving antenna the degree of two dimensionality achieved at the wing center (modified retractable hf type) used aboard the RH-53D helicopter line The analysis was made to provide an acceptable reference The calculations were performed at 1 6 and 3 3 MHz for the for comparison with velocity measurements obtained from a fringe horizontal plane Both vertical and horizontal polarizations were type laser velocimeter optics systems operating in the backscatter considered Four different tow cable configurations were mode in the Langley V/STOL tunnel Good agreement between investigated and their effect on the receiving antenna system laser velocimeter measurements and theoretical results indicate were determined Author (GRA) that both methods provide a true representation of the velocity field about the wing at angles of attack of 0 6 and 4 75 deg Author N78 21363# McDonnell Aircraft Co St Louis Mo MULTIBANO ANTENNA SYSTEM FOR TACTICAL AIR- CRAFT Final Report. 30 Dec 1976 - IS Aug 1977 N78-21464 Washington Univ Seattle F W Vortmeier Sep 1977 527 p A PERTURBATION METHOD FOR PREDICTING AMPLI- (Contract N62269-77-C-0138) TUDES OF NONLINEAR WHEEL SHIMMY PhD Thesis (AD-A049699 NADC-76240-20) Avail NTIS James Thomas Gordon, Jr 1977 226 p HC A23/MF A01 CSCL 17/2 Avail Univ Microfilms Order No 7800928 The ability to extend the frequency range of a 100 MHz to A perturbation method is presented for the stability analysis 40 MHz antenna to include the 30 MHz to 100 MHz range of nonlinear shimmy models Analytical expressions for the limit was examined through analysis and testing Antenna impedance cycle amplitude and frequency were obtained as functions of patterns, power handling and gain comparison measurements the taxi velocity V and stability was examined The solution were made over the extended frequency range The measurements method was applied to aircraft landing gear shimmy models were made on full scale as well as fifth and quarter scale which include a nonlinear (velocity squared) damper The models Results show that it is possible to construct an antenna perturbation solution results are shown to agree well with those that will radiate from 30 MHz to 400 MHz effectively without obtained by direct numerical integration of the nonlinear shimmy the need for active tuning A single input connector to the antenna equations Dissert Abstr is used A mechanical design study was performed to demonstrate the feasibility of locating this antenna in the vertical stabilizer of the F-4 and F-18 aircraft In the case of the F-4 retrofit possibilities were investigated and a flyable fmcap antenna was N78-21471*# Michigan Univ Ann Arbor Dept of Aerospace fabricated The results of the mechanical study showed that it Engineering is feasible to use the antenna in the F-4 and F-18 as well as LIGHTWEIGHT. LOW COMPRESSION AIRCRAFT DIESEL other Navy aircraft including the AV-8 Author (GRA) ENGINE T L Gaynor. M S Bottrell C D Eagle and C F Bachle Jul N78-214O2# Michigan Univ Ann Arbor Dept of Aerospace 1977 103 p refs Engineering (Contract NAS3-20051) APL RADIOMETER WIND TUNNEL TEST PROGRAM WITH (NASA-CR-135300) Avail NTIS HC A06/MF A01 CSCL SIMULATED AIRCRAFT RADOME Final Report 21G William W Willmarth J Maszatics (Bendix Aerospace Systems The feasibility of converting a spark ignition aircraft engine Div ) and E Granholm (Bendix Aerospace Systems Div ) 26 Sep to the diesel cycle was investigated Procedures necessary for 1977 38 p ref Backup document for AIAA Synoptic converting a single cylinder GTS 10-520 are described as well "Management of Turbulent Shear Layers in Separated Flow as a single cylinder diesel engine test program The modification scheduled for publication in Journal of Aircraft in Aug 1978 of the engine for the hot port cooling concept is discussed A (Contract APL/JHU-600276) digital computer graphics simulation of a twin engine aircraft (BSR-4230. POR-3702) Avail NTIS HC A03/MF A01 incorporating the diesel engine and Hot Fort concept is presented Severe airflows encountered within the radiometer cavity showing some potential gains in aircraft performance Sample during flight tests were examined The close proximity of the results of the computer program used in the simulation are aircraft fairing seal to the radiometer windows, the effect of the included Author radome blockage and the effects of radiometer extension, angle of attack, seal location, fences, deflectors, baffles, and a scooping nose are among the factors studied The airborne radiometer housing with a full scale model of the upper half of the radome, N78-21473*# National Aeronautics and Space Administration pod fairing, and aerodynamic seal was evaluated in terms of Lewis Research Center Cleveland Ohio alleviating the severe cavity airflows Results indicate that the ROLLING-ELEMENT FATIGUE LIFE OF AISI M-50 AND low mean and fluctuating flow conditions were obtained in the 18-4-1 BALLS simulator radiometer model when exposed to a uniform flow Richard J Parker and Erwfn V Zaretsky Apr 1978 19 p with pitch angles between + or - 10 deg and the severe high refs speed upflow was caused by the blockage effect of the radome (NASA-TP-1202, E-9350) Avail NTIS HCA02/MFA01 CSCL Radiometer housing configurations found to be successful in 131

325 N78-21891

Rolling element fatigue studies were conducted with AISI M-50. EFR 18-4-1. and VAR 18-4-1 Groups of 12 7 mm (1/2-m) diameter balls of each material were tested in the five ball fatigue tester Test conditions included a load of 1540 N (347 Ibf) giving a maximum Hertz stress of 5520 MPa (800 000 psi) a shaft speed of 10,700 rpm, and a contact angle of 30 deg Tests were run at a race temperature of 339 K (150 F) with a type 2 ester lubricant The rolling element fatigue life of AISI M-50 was not significantly different from that of EFR 18-4-1 or VAR 18-4-1 based on a statistical comparison of the test results Author

N78-21891# Committee on Public Works and Transportation (U S House) AIRPORT AND AIRCRAFT NOISE REDUCTION Washington GPO 1977 590 p refs Hearings on H R 4539 and related bills before Subcomm on Aviation of the Comm on Public Works and Transportation. 95th Congr 1st Sess 30-31 Mar, 5-6. 19-21. 27 Apr. 5 May 1977 (GPO-91-591) Avail Subcomm on Aviation The establishment of a comprehensive program for the systematic reduction of noncompatible land uses in areas surrounding certain airports in the United States and the level of noise created by aircraft operating at such airports was discussed in testimony delivered and statements submitted for the record during House hearings on the resolution The text of the bill is included A R H

326 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl 98) JULY 1978 Typical Subject Index Listing

TIPOBIZBBS- ~Liqaid hydrogen flash vaporizer - lEHODTBAHIC BA1ASCE fuel systems Few rotation-balance apparatus for measuring [BASA-CASE-L4B-12159-1 1 airplane spin aerodynamics in the wind tunnel [AliA 78-835] A78-32386 iEBODHAHIC CH1B1CTEBISTICS The aerodynamic behaviour of fully inflated REPORT TITLE parachutes NUMBER A78-29215 Helicopters: Calculation of integral aerodynamic performance and air-technical data Bussian book The title is used to provide a description of the subject matter When the title is A78-30124 insufficiently descriptive of the document content a title extension is added Dynamic response of lift fans subject to varying separated from the title by three hyphens The NASA or AIAA accession number backpressure for Surface Effect Ships [AIAA PAPEB 78-756] A78-32176 is included in each entry to assist the user in locating the abstract in the abstract P computer-controlled video instrumentation section of this supplement If applicable a report number is also included as an technique for wind tunnel testing of full-scale aid m identifying the document lifting parachutes [AIAA 78-785] A78-323U3 Aerodynamic fluid-fiber interactions [1T-77-CN-1] N78-20060 Effect of winglets on a first-generation jet transport wing. 1: Longitudinal aerodynamic characteristics of a semispan model at subsonic ACCELEBATIOH (PBYSICS) speeds in the Langley 8 ft transonic tunnel A lifting surface theory based on an unsteady [NASA-TN-D-8173] R78-2006U linearized transonic flow model Subsonic longitudinal and lateral-directional [AIAA 78-5011 A78-29820 static aerodynamic characteristics for a model ACCIDBHT PBEVESTIOH with swept back and swept forward wings How to make an airport unattractive to birds [NASA-TH-7U093] N78-20073 A78-29209 Theoretical analysis of aerodynamic Some lessons learned from aircraft accidents - The characteristics of two helicopter rotor airfoils engineering aspects [NASA-TH-78680] N78-20075 A78-29936 Effect of cooling-hole geometry on aerodynamic ICOtJSTIC ERISSIOH performance of a film-cooled turbine vane tested Acoustic emission detection of fatigue crack with cold air in a two-dimensional cascade growth in a production-size aircraft wing test [NASA-TP-1136] H78-20080 article under simulated flight loads Effect of winglets on a first-generation jet A78-31733 transport wing. 5: Stability characteristics ACOUSTIC P&TIGUE of a full-span wing with a generalized fuselage Methods and eguipment for testing for acoustic at high subsonic speeds fatigue of aircraft structural components [BASA-TP-1163] S78-20081 A78-3035M Analysis and comparison of several methods for »COOSTIC PBOBEBTIES computing aerodynamic compressibility and The problem of the acoustic properties of the interference effects up to critical Hach numbers propeller and Q-fan type blower with regard to [AD-A050267] N78-20083 exterior and interior noise in transport aircraft Engineering calculation methods for turbulent A78-30358 flow, volume 1 ACTUiTOBS [IC-AEBO-77-102-VOL-1] H78-20091 A study of low-cost reliable actuators for light Engineering calculation methods for turbulent aircraft. Part A: Chapters 1-8 flow, volume 2 [NASA-CB-1561U2] N78-20110 [IC-AEBO-77-102-VOL-2] N78-20092 A study of low-cost reliable actuators for light Engineering calculation methods for turbulent aircraft. Part E: Appendices flow, volume 3 fNASA-CB-1561U3] N78-20111 [IC-AEBO-77-102-VOL-3] N78-20093 ADIABJTIC COHDITIOHS Modern wing technology for general aviation aircraft The measurement of film cooling effectiveness on [BHFT-FB-W-77-1U] H78-20127 turbine components in short duration wind tunnels Two-dimensional cold-air cascade study of a H78-21152 film-cooled turbine stator blade. 1: AEBOACOOSTICS Comparison of experimental and analytical Aircraft noise and its sources aerodynamic results for blade with 12 rows of A78-30351 0.076-centimeter-(0.030-inch-) diameter holes Effect of noise on life of aircraft structure and having streamwise ejection angles design of parts resistant to acoustic loads [NASA-TP-1151] N78-20130 A78-30352 Subsonic longitudinal and lateral-directional Measuring noise in aircraft cabins static aerodynamic characteristics for a A78-30353 close-coupled wing-canard model in both swept Methods and equipment for testing for acoustic back and swept forward configurations fatigue of aircraft structural components [NASA-TH-7H092] H78-21019 178-30351 Comparison of aerodynamic data measured in air and Methods of reducing aircraft noise Freon-12 wind-tunnel test mediums A78-30355 [NASA-TB-78671] B78-21052

A-1 ABBODYNABIC COEFFICIENTS SUBJECT INDEX

Lou-speed aerodynamic characteristics from Unsteady two dimensional airloads acting on wind-tunnel tests of a large-scale advanced oscillating thin airfoils in subsonic ventilated arrow-wing supersonic-cruise transport concept vind tunnels rNASA-CB-1U5280] N78-21053 [NASA-CB-2967] H78-21059 Fffect of high lift flap systems on the conceptual AEBODTIARIC BOISE design of a 1985 short-haol commercial STOL tilt A new technique for reducing test section noise in rotor transport supersonic wind tunnels [NASA-T1-7817it] N78-21091 [AIAA 78-817] A78-32371 Effects of film injection on performance of a Simulated flight effects on noise characteristics cooled turbine of a fan inlet with high throat Hach nunber H78-21117 [HASA-TP-1199] N78-20132 The influence of jets of cooling air exhausted A method for calculating externally blown flap noise from the trailing edges of a supercritical [NASA-CB-29511] N78-20920 turbine cascade on the aerodynamic data AEBODYHiHIC STABILITY H78-211U8 Theory of dolphin-style sailplane flight and the System optimization by periodic control principles of dynamic flight. II [AD-A019522] N78-21162 A78-29672 AEBODYHAHIC COBFFIC1EHTS A theoretical technique for analyzing aeroelastic A constant aerodynamic parameter testing technique stability of bearingless rotors with automatic wind tunnel control [AIAA 78-503] A78-29805 [AIAA 78-78U] A78-32312 Optimization of linear stabilization systems of Analysis of empirically determined aerodynamic and flight vehicles on the basis of orthogonal filters ram coefficients for a power-augaented-ram A78-32270 wing-in-ground effect Effect of winglets on a first-generation jet [AD-AOU9636] N78-20087 transport wing. 5: Stability characteristics AEBODYBABIC COHFIGU8ATIOHS of a full-span wing with a generalized fuselage Some specific hydrodynamic and aerodynamic at high subsonic speeds problems of surface-effect ships with sidewalls [NASA-TP-1163] R78-20081 A78-31126 Flight evaluation of the transonic stability and Unsteady loads due to propulsive lift control characteristics of an airplane configurations. Part A: Investigation of incorporating a supercritical wing scaling laws [NASA-TP-1167] B78-201tO [NASA-CB-156120] H78-20067 Effect of leading-edge contour and vertical-tail Unsteady loads due to propulsive lift configuration on the low-speed stability configurations. Part C: Development of characteristics of a supersonic transport model experimental techniques for investigation of having a highly-swept arrow wing unsteady pressures behind a cold model jet [NASA-TH-78683] N78-21051 [UASA-CB-156122] N78-20069 AEEODYBAHICS Simplified sonic-boom prediction using A lifting surface theory based on an unsteady aerodynamic configuration charts and calculators linearized transonic flow model or slide rules [AIAA 78-501] A78-29820 [SASA-TP-1122] N78-20078 An empirical correction for wind tunnel wall AEBODYHAHIC DBAG blockage in two-dimensional transonic flow Drag formula for elongated aircraft noses [AIAA 78-806] A78-32360 A78-29718 Study of advanced composite structural design Supersonic transports drag minimization concepts for an arrow wing supersonic cruise techniques configuration, task 3 A78-31152 [NASA-CB-145192] F78-20112 The effect of a parachute on the motion of an Numerical study of transonic flow over oscillating axisymmetric object dropped from an aircraft airfoils using the full potential equation A78-31811 [HASA-TP-1120] N78-21055 Model support system interference on zero-lift AEBOEliSTICITY drag at transonic speeds A theoretical technique for analyzing aeroelastic [AIAA 78-809] A78-32363 stability of bearingless rotors AEBODYNABIC FORCES [AIAA 78-503] A78-29805 Computation of the pressure on the surface of a AEBON10TICAL EHGIHBEBIHG fuselage with a wing in an ideal fluid Applications of wind tunnels to investigations of A78-29712 wind-engineering problems Kormal force of a flat triangular wing in a [AIAA 78-812] A78-32366 supersonic flov Eotorcraft linear simulation model. Volume 1: A78-29720 Engineering documentation Influence of spin rate on side force of an [NASA-CB-152079-VOL-1] N78-20136 axisyumetric body AEBOTBEBHODYHAHICS A78-30690 A critical examination of expansion tunnel Problems concerning high temperatures in small performance turbomachines [AIAA 78-768] A78-32329 H78-21121 Supersonic aerothermal testing - A new requirement AEBODTHAHIC INTBBPEftEHCE [AIAA 78-773] A78-32333 Tunnel interference assessment by boundary AFTEBBOBNIHG measurements Catalytic flame stabilization for aircraft A78-30689 afterburners A parametric experimental study of the A78-31955 interference effects and the boundary-condition Low frequency combustion instability in angmentors coefficient of slotted wind-tunnel walls 878-21138 [AIAA 78-805] A78-32359 AIB CABGO AEBODYSAHIC 1OADS Technical and economic evaluation of advanced air Prediction of the unsteady airloads on cargo systems harmonically oscillating spheroids based on an [HASA-TB-78672] N78-20108 analytical solution of the governing wave equation Gondola system for helicopter transport of A78-29338 external cargo Unsteady loads due to propulsive lift [AD-A017560] H78-20120 configurations. Part B: Pressure and velocity AIB COOLIIG measurements in a three dimensional wall jet Hot cascade test results of cooled turbine blades fNASA-CB-156121] H78-20068 and their application to actual engine conditions Unsteady loads due to propulsive lift H78-21125 configurations. Part C: Development of Effects of film injection on performance of a experimental techniques for investigation of cooled turbine unsteady pressures behind a cold model jet N78-211U7 fNASA-CF-156122] B78-20069

A-2 SUBJECT IHDEI AIBCBAFT COHTBOL

The influence of jets of cooling air exhausted AIBBOBBE EQDIPHBHT from the trailing edges of a supercritical The next generation Ei system - ASPJ Airborne turbine cascade on the aerodynanic data Self Protection Janoer 178-21108 A78-31700 AIB DEPEBSE The BPB 320 airborne simulator of DPVLB as test Simulation tests of anti-flak profiles instrument for determining flight characteristics aircraft flight optimization for ground attack [DGLR PAPEB 77-082] A78-3191I11 mission A test using simulated mission profile environments A78-31951 Airborne Instrumentation Subsystem pod AIB FLOB reliability Investigation of the flow in a plane diffuser by A78-32126 aeans of a laser Doppler anemoueter A spectroradioneter for airborne remote sensing A78-28969 for geological, vegetation and hydrological AIB NAVIGATIOH mapping Choice of optimal ellipsoid-surface projection A78-32396 onto a sphere in solving problems of air AIBBOBBE SOBVEILLAHCE BADAB navigation Fire power fighter aircraft target acquisition A78-28523 and tracking radar Observability criteria for nonlinear dynamic A78-31125 systems subjected to Doltiparameter measurements AIBBOBHE/SPACEBOBBB COHPOTEBS noting air navigation applicability Optimal control of the longitudinal motion of a A78-29089 helicopter on the basis of an operational Benefits cf strapdown over gimbal INS systens for algorithm aircraft application A78-32272 A78-30253 Stand-alone development system using a Kin-1 Applications of Advances in Navigation to Guidance microcomputer nodule and Control [NASA-CB-156067] S78-20100 [AGARD-CP-220] N78-21071 AIBCBAFT JCCIDEBT IBVESTIGATIOS AIB POLLUTION Some lessons learned from aircraft accidents - The Air quality impact of aircraft at ten O.S. Air engineering aspects Force bases A78-29936 A78-32222 Aircraft accident report: Southern Airways Inc., AIB QUALITY DC-9-31, N13350, New Hope, Georgia, April H, 1977 Air quality mpact of aircraft at ten O.S. Air [NTSB-AAB-78-3] N78-2106U Force bases AIBCBAFT ACCIDEBTS A78-32222 Clear air turbulence accidents AIB TBAFFIC J78-28833 Air traffic safety in the airport near range How to make an airport unattractive to birds [TOBS/SFB58/n«] N78-20103 A78-29209 AIB TBiPFIC COHTBOL AIBCBAFT ANTEHHJS Automatic airspace automatic flight control of Special problems in the determination of the terminal configored vehicle for ATS radiation characteristics of antennas on A78-28831 aircraft and satellites with the aid of A method of calculating ILS approach surfaces geometric diffraction theory A78-29207 A78-31582 Air traffic control and energy conservation in air HP radiation characteristics of the RH-53D operations helicopter and the Hark 105 AHCH system A78-3131U [AD-AOU9795] B78-21358 Ground radar - Vital tool or luxury for nultiband antenna system for tactical aircraft aircraft surface movements [AD-AOU9699] H78-21363 A78-31869 AIBCBAFT APPBOACH SPACING Terminal-area flight experience with the NASA A method of calculating ILS approach surfaces Terminal Configured Vehicle A78-29207 A78-31972 Doppler MLS - The OK solution The impact of a proposed active BCAS on ATCRBS A78-2993D performance in the Washington, D. C., 1981 AIBCBAFT COHBOHICATION environment Flight tests of digital data transmission MSK rAD-AO»8589/6] N78-20099 - a quadrature PSK system Cockpit displayed traffic information study, part 2 A78-31050 [NASA-CR-156115] H78-20102 AIBCBAFT COBPABTHEKTS Air traffic safety in the airport near range Aircraft and helicopter cockpit noise [TOBS/SFB58/H1] N78-20103 A78-29673 Simulation and development possibilities of the Measuring noise in aircraft cabins manual control concept in the near range and A78-30353 control zone Time-dependent fire behavior of aircraft cabin N78-20101 materials Program for simulation of air traffic and air [AD-A050923] N78-21230 space structure of the Frankfurt near range, a AIBCBAFT CONSTBDCTION HATEBIALS planning control and a collision avoidance Microfractographic fracture analysis of some system with situation dependent avoidance aircraft parts maneuvers A78-28789 N78-20105 Future trends in aircraft structural design and Improved aircraft tracking using maneuver materials statistics enroate and in the terminal area [AIAA 78-165] A78-29822 178-21087 Alloy needs and design - The airframe AIB TBAHSPOBTATIOH A78-30856 Factors influencing schedule reliability in Basic problem of control of the motion of a international operations non-Newtonian fluid in a gap roll forcing of A78-29213 aircraft plastics Critical considerations on the legal development A78-32257 of personal liability with attention to air Estimating times to early failures using finite transportation data to estimate the Heibnll scale parameter A78-299QO [AD-A050263] B78-2052» Flying over the exclusive economic zone Evaluation of windshield materials subjected to aircraft overflight regulations simulated supersonic flight A78-2")9it5 IAD-A019981] N78-21101 STOL system fuel savings - Ground and air AIBCBAFT COHTBOL A78-31312 Fly-by-wire flight control A78-29935

S-3 AIBCBiFT DESIGN SUBJECT HDEX

New trends and problem areas in automatic flight The problem of choosing design parameters for control unpiloted flight-vehicles control configured A78-30252 optimization Sensitivity reduction in aircraft control systems A78-32258 A78-3103H Optimization of the structure of a multibulkhead Analytical design of an automaton for the large-aspect-ratio wing longitudinal control of an aircraft A78-32275 A78-32262 Technical and economic evaluation of advanced air New rotation-balance apparatus for measuring cargo systems airplane spin aerodynamics in the wind tunnel [NASJ-TM-78672] N78-20108 [AIAA 78-835] A78-32386 Multi-variate optimization problems of flight Simulator evaluation of a flight-path-angle vehicle synthesis control system for a transport airplane with [PB-276123/7] 1178-21103 direct lift control AIECBAPT ES6IHES [NASA-TP-1116] N78-20139 'Chain pooling1 model selection as developed for Flight evaluation of the transonic stability and the statistical analysis of a rotor burst control characteristics of an airplane protection experiment incorporating a supercritical wing A78-29327 [NASi-TP-1167] N78-20110 General aviation energy-conservation research Pilot-model analysis and simulation study of programs at NASA-Lewis Research Center for effect of control task desired control response non-turbine general aviation engines [NASA-TP-1UO] N78-20113 A78-29330 Applications of Advances in Navigation to Guidance Control of aircraft turbine engine acceleration and Control A78-29583 [AGARD-CP-220J N78-21071 Using simulation to determine the transfer DBF DF triangulation system for control and function of the electronic part of a control loop guidance of military aircraft for gas turbine aircraft engines N78-21077 A78-2958I1 AIBCBiFT DESIGN Determining the reliability requirements of OS Navy examining a wide range of V/STOL concepts aircraft engine control systems during design A78-29175 stage Optimum tail plane design for artificially A78-29590 stabilized aircraft Evolution of the aircraft gas turbine engine S78-29331 A78-30257 Determining the reliability requirements of Choice of engine design for small transport aircraft aircraft engine control systems during design A78-30357 stage Some aspects of powerplant airframe integration A78-29590 affecting fuel conservation Computation of the pressure on the surface of a A78-3130I4 fuselage with a wing in an ideal fluid Aircraft fuel economy - The propulsion system A78-29712 contribution Future trends in aircraft structural design and A78-31309 materials Energy conserving aircraft from the engine viewpoint [AIAA 78-fl65] A78-29822 A78-31310 Weight design and the efficiency of passenger Thrust computing system applications to increase aircraft. Volume 2 - Calculation of the center engine life and provide fuel conservation of gravity and moments of inertia of aircraft. A78-31311 Weight analysis Russian book Hirage 2000 French flighter aircraft design A78-30175 characteristics, SNECHA M53 engine and avionics The An-26 aircraft: Construction and use A78-31755 Russian book Catalytic flame stabilization for aircraft A78-30273 afterburners Effect of noise on life of aircraft structure and A78-3195S design of parts resistant to acoustic loads Ejector-powered engine simulators for small-scale A78-30352 wind tunnel models of high performance aircraft Remotely piloted aircraft in the civil environment [AIAA 78-826] A78-32388 A78-30506 Effectiveness of the real time ferrograph and supersonic transports drag minimization other oil monitors as related to oil filtration techniques [AD-AOU933Q] N78-20131I A78-31152 Fuel conservation merits of advanced turboprop The NASA Aircraft Energy Efficiency Program transport aircraft A78-31302 [NASA-CB-152096] N78-21095 Prospects for energy conserving STOL transports A review of techniques for the thermal protection using prop-fans of the walls of the combustion chamber and A78-31303 reheating ducts of turboreactors Some aspects of powerplant airframe integration N78-211311 affecting fuel conservation Lightweight, low compression aircraft diesel engine A78-31301 converting a spark ignition engine to the Improved energy efficiency for small CT01 diesel cycle transport aircraft [NASA-CB-135300] N78-21171 A78-31305 AIBCBAFT BQOIPBEHT Fuel saving potential of Hach 0-8 twin engine Product support for French equipment used by civil prop-fan transports aviation companies A78-31306 A78-29657 Fuel efficiency - where we are heading in the Unique test capabilities of the Eglin AF3 HcKinley lesign of future jet transports Climatic laboratory A78-31307 A78-32127 Mirage 2000 French flighter aircraft design Investigation of a high speed data handling ^system characteristics, SNECHA B53 engine and avionics for use with mnltispectral aircraft scanners A78-31755 [NASA-TM-78689] N78-201181 Ose of and experience with simulation in the Nickel/cadmium aircraft batteries: Battery alarm development of the VPB 6m and the VAK 191 unit [DOLE PAPEP 77-083] A78-319U2 [AD-A039521] N78-20631 The error function of analytical structural design SicXel/cadmina aircraft batteries: Rapid in aircraft component failure in static tests electrolyte exchange technique A78-32123 [AD-A039335] N78-20632 Nickel/cadmium aircraft batteries: Single sensor temperature monitoring [AD-A037722] N78-20635

A-0 SUBJECT IHDEX AIBCBAFT PBODOCTIOH

Hickel/cadmium aircraft batteries: Multichannel Subsonic longitudinal and lateral-directional gassing-rate meter static aerodynamic characteristics for a model [AD-A039735} H78-20636 with swept back and swept forward wings Design, fabrication, and testing of a fall-scale [HASA-TH-711093] 878-20073 breadboard in nitrogen generator for fuel tank Botorcraft linear simulation model. Volume 1: inerting application Engineering documentation [AD-A019«59] H78-21097 [HASA-CB-152079-VOL-1] 878-20136 AIBCBAFT FUELS Botorcraft linear simulation model. Volume 2: Properties of fuels used in the Czechoslovak Computer implementation aircraft industry [HASA-CB-152079-VOL-2] 878-20137 A78-29588 Botorcraft linear simulation model. Volume 3: Aviation fuels - A supplier's perspective User's manual A78-31308 [BASA-CB-152079-VOL-3] B78-20138 Fuel conservation merits of advanced turboprop AIBCBAFT BOISE transport aircraft Investigation of interior noise in a twin-engine [BASA-CB-152096] S78-21095 light aircraft AIBCBAFT GOIDABCE A78-296H1 Navigation, guidance and control for high Aircraft and helicopter cockpit noise performance nilitary aircraft A78-29673 H78-21090 Aircraft noise and its sources AIBCBAFT HAZABDS A78-30351 An evaluation of the bird/aircraft strike hazard, Effect of noise on life of aircraft structure and Ralnstrom AFE, Montana design of parts resistant to acoustic loads [AD-A019637] S78-20095 A78-30352 Fire resistivity and toxicity studies of candidate Measuring noise in aircraft cabins aircraft passenger seat naterials A78-30353 [8ASA-TM-78U68] B78-2121H Methods of reducing aircraft noise AIBCBAFT INSTBOHEHTS A78-30355 Automatic airspace automatic flight control of The problem of the acoustic properties of the terminal configured vehicle fcr ATS propeller and Q-fan type blower with regard to A78-2883U exterior and interior noise in transport aircraft Advanced flight decks for the 80s cockpit A78-30358 design for transport aircraft On sound transmission into a heavily-damped cylinder 578-28835 aircraft noise in fuselage Systematic analysis of safety in aviation. II A78-31019 A78-29671 The aircraft ducted fan Further experimental evaluation of the A78-31153 electrostatic roll sensor at Mach 2.3 and 3.5 Psychological Assessment of Aircraft 8oise Index [AIAA 78-802] A78-32357 A78-32058 Development of a binary frequency synthesis as Study of the use of a nonlinear, rate-limited control element for freguency correction in filter on pilot control signals time-synchronous collision systems without [BASA-TP-1147] B78-201U2 onboard atomic frequency standard avoidance Comparison of measured and calculated helicopter N78-20106 rotor impulsive noise wind tunnel test data APL radiometer wind tunnel test program with and prediction analysis techniques simulated aircraft radome [8f SA-TH-78I173] B78-20917 CBSB-11230] 878-211402 Airport and aircraft noise reduction AIBCBAFT 1AHDIBG [GPO-91-591] 878-21891 Optimal control of the longitudinal motion of a AIBCBAFT FABTS helicopter on the basis of an operational Microfractographic fracture analysis of some algorithm aircraft parts A78-32272 A78-28789 fn evaluation of the bird/aircraft strike hazard, Acoustic emission detection of fatigue crack Malmstrcm AFB, Montana growth in a production-size aircraft wing test [AD-AOI49637] 878-20095 article under simulated flight loads Development of systems and techniques for landing A78-31733 an aircraft using onboard television Quality assurance in the fabrication of products [BASA-TP-1171] H78-20VII in aviation technology Ground distance covered during airborne horizontal A78-32267 deceleration of an airplane AIBCBAFT FEBFOBHAUCE CNASA-TP-1157] N78-20115 Handling"gualities of aircraft in the presence of AIBCBJFT HAIHTBH&BCE simulated turbulence Product support for French equipment used by civil A78-296U3 aviation companies Performance of the ABAVA aircraft with wing-tip A78-29657 winglets Life-cycle analysis of aircraft turbine engines A78-30256 [AD-A0503«9] H78-20135 Some aspects of powerplant airframe integration A life cycle cost study of contractor versus affecting fuel conservation organic support of aircraft programs A78-3130i» [AD-A019U38] N78-210M5 The Dual-Plight-Simulator on the evaluation of air AIBCBAFT MAHBOVEBS combat effectiveness Going for a spin - Fighter style [DGLB PAPEB 77-080] A78-319U8 A78-317U5 Aircraft takeoff from dirt airstrips Digital computer program maneuver pilot A78-32273 A78-319U6 Analysis of empirically determined aerodynamic and Program for simulation of air traffic and air ram coefficients for a power-augmented-ram space structure of the Frankfurt near range, a wing-in-ground effect planning control and a collision avoidance [AD-SOU9636] N78-20087 system with situation dependent avoidance Study of the use of a nonlinear, rate-limited maneuvers filter on pilot control signals 1)78-20105 [SASA-TP-11lf7] 878-20112 AIBCBAFT MODELS AIBCBAFT PBODOCIIOB Ejector-powered engine simulators for small-scale Laser and optical methods of monitoring in vind tunnel models of high performance aircraft aircraft construction Russian book [AIA4 78-826] A78-32388 A78-30123 Subsonic roll damping of a model with swept-back and swept-forward wings [NASA-TH-78677] 878-20061

A-5 AIBCBAFT RELIABILITY SUBJECT IHDEX

AIBCBAFT BE1IABIIITI AIBFOILS Determining the reliability requirements of Some measurenents in two-dimensional turbulent wakes aircraft engine control systems daring design A78-31836 stage The shock tube as a device for testing transonic A78-29590 airfoils at high Reynolds numbers A fail-safe analysis of a spanwise Ming-panel splice [AIAA 78-769] A78-32330 [AIA? 78-187] A78-29791 An experimental investigation of oscillating flows Joint ASD/AFSAL Combined Environment Beliability over an airfoil rotary wings Test /CERT/ Evaluation Program N78-20058 A78-32118 Onset of condensation effects with a BACA 0012-61 Research requirements to improve reliability of airfoil tested in the Langley 0.3-meter civil helicopters cryogenic tunnel [NASA-CR-1115335] B78-21093 [NASA-TH-78666] N78-20071 AIBCBAFT SAFETt A critical evaluation of the predictions of the Fatigue life analysis of the L 13 /Blanik/ glider HASA-Iockheed multielement airfoil computer A78-30360 program Investigation to support phase 1 of the DSAF [HASA-CB-115322] B78-20076 midair prevention systems program (MAPS) An improved version of the SfSA-Lockheed [AD-A019713] N78-21066 multielement airfoil analysis computer program Bearing study program hearing measurement [NASA-CB-115323] N78-20077 subsystem for SECANT Collision Avoidance System Numerical study of transonic flow over oscillating [AD-A019767] N78-21068 airfoils using the full potential equation AIHCBAFT STABILITY [HASA-TP-1120] S78-21055 Optimum tail plane design for artificially Unsteady two dimensional airloads acting on stabilized aircraft oscillating thin airfoils in subsonic ventilated A78-29334 wind tunnels The wind and turbulence measuring system of the [SASA-CB-2967] K78-21059 HAE Airborne V/STOI Simulator Unsteady, surface pressure and near-wave hotwire A78-30850 measurements of a circulation control airfoil Theory of bending-torsional self-oscillations of [AD-A050025] S78-21061 an aircraft ving system Transonic wind tunnel tests on two-dimensional A78-32261 aerofoil sections. Determination of pressure AIBCB4FT STBOCTOBES distribution and drag for an aerofoil with a Investigation of interior noise in a twin-engine modified NACA 65 sub2-215 section in FFA wind light aircraft tunnel S5, part 2 A78-296«1 [FFA-TB-AD-725] N78-21062 Stress analysis of typical flaws in aerospace AIBFBAHE BATERIALS structural components using 3-D hybrid Alloy needs and design - The airframe displacement finite element method A78-30856 fAIAA 78-513] A78-29812 AIRFBABES Future trends in aircraft structural design and Some aspects of powerplant airframe integration materials affecting fuel conservation [AIAA 78-165] A78-29822 A78-31301 The An-26 aircraft- Construction and use Estimating times to early failures using finite Russian book data to estimate the Seibull scale parameter A78-30273 [AD-A050263] N78-20521 Effect of noise on life of aircraft structure and A-1F Blue Angel flight usage data, 1976 design of parts resistant to acoustic loads [AD-A050161] H78-21100 A78-30352 Airflow and thrust calibration of an F100 engine, Methods and equipment for testing for acoustic S/N P680059, at selected flight conditions fatigue of aircraft structural components [NASA-TP-1069] S78-21112 A78-30351 AIBLIHE OPERATIONS Basic fatigue curves of aircraft structures Factors influencing schedule reliability IE A78-30356 international operations Analysis and synthesis of operational loads A78-29213 aircraft structures Critical considerations on the legal development [ISD-193] H78-20551 of personal liability with attention to air Report on aircraft fatigue studies in-flight transportation monitoring and stress measurements A78-29911 [AD-A019876] N78-21102 Flying over the exclusive economic zone »IBCBAFT SOBVIVABI1ITY aircraft overflight regulations Crashworthiness of aircraft fuselage structures A78-29915 [AIAA 78-177] A78-29785 The division of air transport markets between A review of methodologies and concepts to measure carriers - local service operations and evaluate aircraft survivability/vulnerability A78-30697 [AD-A050152] N78-21099 Aviation fuel usage - Economy and conservation AIHCB1FT TIBES A78-30698 Definition of tire properties required for landing A new method for estimating current and future system analysis transport aircraft operating economics [HASA-CB-156171] N78-21326 [NASA-CR-115190] B78-20091 AISDROPS Airport and aircraft noise reduction The effect of a parachute on the motion of an [GPO-91-591] S78-21891 axisymmetnc object dropped from an aircraft AIBPOBT FLASHING A78-31811 More public consultation on airport plans ilBFIFID SURFACE HOVEHEHTS A78-29208 Ground radar - Vital tool or luxury for Profile of the airport-development crisis aircraft surface movements A78-30211 A78-31869 Looking offshore at the airport future 1ISFOIL PBOFILES A78-30215 Transonic flows past a lift profile Tandem-queue algorithm for airport user flows A78-28961 A78-30677 Variational principles for the transonic airfoil Airport/community environmental planning problem A78-30678 A78-30891 Sweden's latest- and last airport Bixed ventilated foils design for immersed A78-31868 hydrofoils AIBPOBI SECOBIT7 A78-31127 How to make an airport unattractive to birds Airfoil profile in a nonuniform flow A78-29209 [BASA-TH-75272] N78-21018

A-6 SUBJECT IBDBI AXISTBBETBIC BODIES

AIBPOBTS ATHOSPHEBIC TORBOLBHCE Factors influencing schedule reliability in The wind and turbulence measuring system of the international operations HAE Airborne V/STOL Smulator A78-29213 A78-30850 Simulation and development possibilities of the ATTACK AIBCBAFT Dannal control concept in the near range and Emulation tests of anti-flak profiles control zone aircraft flight optimization for ground attack N78-20101 mission Program for simulation of air traffic and air A78-31951 space structure of the Frankfort near range, a A-HF Blue Angel flight usage data, 1976 planning control and a collision avoidance [AD-A0501611] H78-21100 system with situation dependent avoidance AOTOCOBBELATION maneuvers Improved aircraft tracking using maneuver 178-20105 statistics enroute and in the terminal area Airport and aircraft noise reduction B78-21087 [GPO-91-591] 178-21891 A0TOBATA TBEOBI ALGOBWBBS Analytical design of an automaton for the Tandem-queue algorithm for airport user flovis longitudinal control of an aircraft A78-30677 A78-32262 Optimal control of the longitudinal notion of a AOTOBATIC COSTBOL helicopter on the basis of an operational Use of a stepping motor for measuring fuel algorithm quantity in a digital system for control of A78-32272 rotational speed 41PB4 JET AIBCBAFT A78-29586 Simulation in the development of the training and A reliable modular automatic system adapted to ground-attack aircraft Alpha Jet avionics controls: Design through successive A78-319U3 refinements - Production French book ALTIBETEBS A78-3002<4 Use of NS LX1600A as a short-range altimeter Optimal control of the longitudinal motion of a >78-28830 helicopter on the basis of an operational Differential altimetry for satellite orbit algorithm determination A78-32272 A78-31915 AD10HATIC FLIGBT CORTBOL ALTITUDE COBTBOl Automatic airspace automatic flight control of Pilot-model analysis and simulation study of terminal configured vehicle for ATS effect of control task desired control response A78-2883U [NASA-TP-11140] H78-201«3 Observability criteria for nonlinear dynamic ALOBIROB ALLOTS systems subjected to multiparameter measurements Alloy needs and design - The airframe noting air navigation applicability 178-30856 A78-29089 ANGLE OF ATTACK Fly-by-wire flight control Determination of high attitude vail corrections in A78-29935 a low speed wind tunnel Hew trends and problem areas in automatic flight [AIAA 78-810] A78-3236H control ANTEHHA DESIGH A78-30252 Hultiband antenna system for tactical aircraft Analytical design of an automaton for the [AD-AO«9699] H78-21363 longitudinal control of an aircraft AHTEHRA BADIATIOR P1TTEBBS A78-32262 Special problems in the determination of the Heavy lift helicopter flight control system. radiation characteristics of antennas on Volume 3: Automatic flight control system aircraft and satellites with the aid of development and feasibility demonstration geometric diffraction theory [AD-A050059] S78-2116U A78-31582 ADTOBATIC TEST EQUIPBEHT Hultiband antenna system for tactical aircraft Automatic sustainment of resonance conditions in [AD-A049699] N78-21363 the multipoint excitation of flight-vehicle ARTOHOV AIBCBAFT vibrations The An-26 aircraft: Construction and use A78-32268 Russian book A constant aerodynamic parameter testing technique A78-30273 with automatic wind tnnnel control APPLICATION OF BATBEBATICS [AIAA 78-784] A78-323H2 New computation method of turbine blades film AOTOBOTATIOR cooling efficiency A simple method for estimating minimum N78-21151 autorotative descent rate of single rotor Calculation of temperature distribution in disks helicopters and cooling flow in a transient state [NASA-TH-78U52] B78-20113 178-21157 AVIORICS AFFBOACB COHTBOl A reliable modular automatic system adapted to A UD approach control using VOB/DHE/ILS guidance avionics controls: Design through successive N78-21083 refinements - Production French book Optimal control theory (OHEH) applied to a A78-30020 helicopter in the hover and approach phase Hiraqe 2000 French flighter aircraft design [NASA-CB-152135] N78-21161 characteristics, SNECHA H53 engine and avionics ABROS SIHGS A78-31755 Study of advanced composite structural design Joint ASD/AFWAL Combined Environment Reliability concepts for an arrow wing supersonic cruise Test /CEBT/ Evaluation Program configuration A78-32118 rNASA-CB-2825] 1178-20116 Practical experience in vibration testing external Effect of leading-edge contour and vertical-tail avionics systems configuration on the low-speed stability A78-3213H characteristics of a supersonic transport model Bulti-variate optimization problems of flight having a highly-swept arrow wing vehicle synthesis [NASA-TH-78683] S78-21051 [PB-276123/7] B78-21103 ATBOSPBEBIC BODSDABI LATEB AZISYBBBTBIC BODIES Applications of wind tunnels to investigations of Influence of spin rate on side force of an wind-engineering problems axisymraetric body [AIAA 78-812] A78-32366 A78-30690 Research on various aspects of atmospheric flight The effect of a parachute on the motion of an [AD-A033681] F78-20088 axisymmetric object dropped from an aircraft A78-31811

A-7 B-1 AIRCRAFT SOBJECT INDEX

BRAKES (FOR ABBESTING BOTIOS) Summary of NASA landing gear research B [NASA-TH-78679] N78-20050 B-1 AIBCHAFT BREADBOARD BODELS An engine nozzle vibration phenomenon encountered Design, fabrication, and testing of a full-scale in B-1 flight tests breadboard in nitrogen generator for fuel tank A78-32129 inerting application Fiber Optics Cost Analysis Program (POC1P) [AD-A049459] N78-21097 [AD-A049859] 1178-21105 BUCKLING BALLISTIC BAIGES Preliminary design of composite wings for The AEDC Bange K facility for erosion testing buckling, strength and displacement constraints [AIAA 78-7751 178-32331 [AIAA 78-466] A78-29777 BALLISTICS Experimental and finite element investigation of Hypersonic heat transfer test program in the VKI the buckling characteristics of a beaded skin longshot facility ogive body configuration panel for a hypersonic aircraft [AD-A050295] N78-20086 [HASA-CH-1411863] N78-20534 BALLS BULKHEADS Rolling-element fatigue life of AISI 1-50 and Optimization of the structure of a multibulkhead 18-11-1 balls large-aspect-ratio wing [NASA-TP-1202] N78-21473 A78-32275 BASE PRESSURE BYPASSES Sting effects as determined by the measurement of Influence of structural components of a by-pass pitch-damping derivatives and base pressnres at engine on its flight characteristics STOL Mach number 3 aircraft CAIAA 78-830] A78-32381 A78-29582 BEACONS Some test results concerning visibility of obstacle and hazard beacons A78-29907 CALCULATORS BEABING1BSS BOTOBS Simplified sonic-boom prediction using Bearingless tail rotor loads and stability aerodynamic configuration charts and calculators [AD-A049579] 1178-21098 or slide rules BIBD-AIRCRAFT COLLISIONS [NASA-TP-1122] 1178-20078 How to make an airport unattractive to birds CALIBRATING A78-29209 Airflow and thrust calibration of an F100 engine, ?n evaluation of the bird/aircraft strike hazard, S/N P680059, at selected flight conditions lalmstrom AF"3, Montana [NASA-TP-1069] 1178-21112 [AD-A049637] 178-20095 CANARD CONFIGURATIONS BLADE TIPS Hind-tunnel investigation at flach numbers from Acoustical effects of blade tip shape changes on a 1.90 to 2.86 of a canard-controlled missile with full scale helicopter rotor in a wind tunnel ram-air-jet spoiler roll control in the [NASA-CB-152082] N78-20918 Langley Unitary Plan Wind Tunnel BLOCKING [NASA-TP-1124] S78-20079 An empirical correction for wind tunnel wall Subsonic longitudinal and lateral-directional blockage in two-dimensional transonic flow static aerodynamic characteristics for a CAIAA 78-806] A78-32360 close-coupled wing-canard model in both swept BLORING back and swept forward configurations Moving ground simulation by tangential blowing [NASA-TH-74092] N78-21049 [AIAA 78-811] A78-32368 CARGO AIRCRAFT BODIES OF BEVOLOTION An economic analysis of a government sponsored, Influence of spin rate on side force of an commercial convertible aircraft axisynmetric body [AD-A047633] 1178-20096 A78-30690 Technical and economic evaluation of advanced air BODY-WING AND TAIL CONFIGOHATIONS cargo systems Aeroelastic analysis and ground vibration survey [NASA-TH-78672] N78-20108 of the NASA, Grumman American Yankee modified Aircraft cargo compartment fire test simulation for spin testing program [NASA-CB-156119] N78-20109 [NASA-CB-151951] N78-21223 BODY-SING CONFIGURATIONS CASCADE FLOR Computation of the pressure on the surface of a Two-dimensional cold-air cascade study of a fuselage with a wing in an ideal fluid film-cooled turbine stator blade. 4: A78-29712 Comparison of experimental and analytical BOEING 717 AIBCBAFT aerodynamic results for blade with 12 rows of An economic analysis of a government sponsored, 0.076-centimeter-(0.030-inch-) diameter holes commercial convertible aircraft having streamwise ejection angles TAD-AOU7633] N78-20096 [NASA-TP-1151 ] 1178-20130 BOUNDARY LAYEB CONTROL Two-dimensional cold-air cascade study of a Effect of boundary layer suction through slits on film-cooled turbine stator blade. 5: the efficiency of tnrbomachine outlet diffusors Comparison of experimental and analytical A78-30572 aerodynamic results for blade with 12 rows of Experiments on supercritical flows in a 0.038-centimeter-(0.015 inch) diameter coolant self-correcting wind tunnel holes having streamwise ejection angles A78-32345 [NASA-TP-1200] N78-20133 Unsteady, surface pressure and near-wave hotwire Hot cascade test results of cooled turbine blades measurements of a circulation control airfoil and their application to actual engine conditions [AD-A050025] N78-21061 1178-21125 BOONDABY LAYEB FLOR CASCADE BIND TDNHELS An analytic study of free molecule flow fields at Effect of cooling-hole geometry on aerodynamic the front and back edges of a plate performance of a film-cooled turbine vane tested A78-28972 with cold air in a two-dimensional cascade BOUNDARY LAYERS [NASA-TP-1136] N78-20080 A brief examination of the flow external to an CASE HISTORIES F-111 intake at Mach 1.6 Effect of reliability programs on life cycle cost fABL/HE-NOTE-3571 N78-21054 - A case history of TACAN test set BOUNDARY VALUE PROBLBBS A78-29178 Tunnel interference assessment by boundary CATALYTIC ACTIVITY measurements Catalytic flame stabilization for aircraft A78-30689 afterburners A78-31955

A-8 SDEJECT IHDBX COBPUTATIOH

CEBABIC COilIHGS Investigation to support phase 1 of the DSAF Evaluation of a ceramic combustion chaaber for a midair prevention systems program (HAPS) snail gas turbine engine [AD-A049703] H78-21066 H78-211«5 Bearing study program bearing measurement CHABTS subsystem for SECANT Collision Avoidance System Simplified sonic-boon prediction osing [AD-AOU9767] N78-21068 aerodynamic configuration charts and calculators COllOCiTIOH or slide roles Unsteady two dimensional airloads acting on [NASA-TP-11221 H78-20078 oscillating thin airfoils in subsonic ventilated CIVIL AVIATIOS wind tunnels Product support for French equipnent used by civil [NASA-CB-2967] N78-21059 aviation companies COBBAT 478-29657 The Dual-Flight-simulator on the evaluation of air Hhither HLS Microwave landing Systen civil and combat effectiveness military applications [DGLR PAPEB 77-080] A78-319<48 A78-30096 COBBDSTIOH CBABBEBS Profile of the airport-development crisis A review of techniques for the thermal protection A78-302

A-9 COSPOTER DESIGN SUBJECT IHDEX

Engineering calculation methods for turbulent COHCOBDE AIRCRAFT flow, volume 2 Concorde noise-induced building vibrations, John [IC-AERO-77-102-VOL-2] S78-20092 F. Kennedy International Airport Engineering calculation methods for turbulent [NASA-TB-78676] N78-20919 flow, volume 3 COBDEBSATIOB CIC-ABRO-77-102-VOL-3J F78-20093 Onset of condensation effects with a SACS 0012-61 COBPUTER DESIGN airfoil tested in the Langley 0.3-meter lain characteristics of the ADT UOOO-U1QO digital cryogenic tannel computer for a hybrid computing system for [NBSA-TB-78666] N78-20071) jet engine simulation COHDBBSIHG A78-29589 Condensation and its growth down the test-section * reliable modular automatic system adapted to of the Langley 0.3-m transonic cryogenic tunnel avionics controls: Design through successive [AIAA 78-811] A78-32365 refinements - Production French book COSDITIOHS A78-3002U Expansion of flight simulator capability for study COBPDTEE GBAPBICS and solution of aircraft directional control Proposal and construction of a hybrid flight-sight problems on runways simulator with large picture projection [NASA-CB-2970] N78-20118 [DGLH PAPER 77-087] A78-31915 COHFEBEHCBS The Boeing Aerodynamic Labs data system High temperature problems in gas turbine engines [AIAH 78-789] A78-32316 [AGABD-CP-229] H78-21118 CO9POTEB PBOGBABS COHGBBSSIOSAI FEPOETS P critical evaluation of the predictions of the Airport and aircraft noise reduction NASA-Lockheed multielement airfoil computer [GPO-91-591] N78-21891 program COHICAL FLOH f!!!tSa.-CR-1U5322] N78-20076 Investigation of the flow in a plane diffuser by An improved version of the NASA-Lockheed means of a laser Doppler anemometer multielement airfoil analysis computer program A78-28969 fBASA-CR-1i)5323] B78-20077 COHTilBEBS Rotorcraft linear simulation model, volume 2: Gondola system for helicopter transport of Computer uplementation external cargo [SASA-CR-152079-VOL-2] N78-20137 [AD-AOU7560] B78-20120 A three-dimensional potential-flow program with a CONTROL geometry package for input data generation System optimization by periodic control rNASA-CR-115311] B78-210U7 [AD-A019522] N78-21162 A vectonzation of the Jameson-Caughey BTO COHTBOL COHFIGOBBD VEHICLES transonic swept-wing computer program FLO-22-V1 The problem of choosing design parameters for for the STAS-100 computer unpiloted flight-vehicles control configured [NASA-TB-78665] B78-21050 optimization COBPDTEB SYSTEBS PBOSBiHS A78-32258 Fault tolerant flight controls Optimization of the design parameters of finned A78-28900 pilotless flight vehicles Trends of fatare turbine life prediction: Time A78-32269 phase automated analysis and test verification CONTBOL BQOIPBENT N78-21113 Fly-by-wire flight control COHPOTEHTZED DESIGH A78-29935 Preliminary design of composite wings for COHTBOL SIBOLATIOB buckling, strength and displacement constraints Dsing simulation to determine the transfer [AIAA 78-1166] A78-29777 function of the electronic part of a control loop The problem of choosing design parameters for for gas turbine aircraft engines unpiloted flight-vehicles control configured A78-29S8H optimization Rotorcraft linear simulation model. Volume 1: A78-32258 Engineering documentation Semispan wind tunnel test of a computer-controlled [NASA-CB-152079-VOL-1 ] N78-20136 self-optimizing flexible technology wing Rotorcraft linear simulation model. Volume 2: [AIAA 78-786] A78-3234U Computer implementation COBPDTEBIZED SIBDLATIOH [NASA-CB-152079-VOL-2] B78-20137 'Chain pooling' model selection as developed for Rotorcraft linear simulation model. Volume 3: the statistical analysis of a rotor burst User's manual protection experiment [NASA-CB-152079-70L-3] B78-20138 A78-29327 Besults from flight and simulator studies of a Use of and experience with simulation in the Bach 3 cruise longitudinal autopilot development of the VFH 61« and the VAK 191 [NASA-TP-1180] B78-21160 [DGLB PAPEB 77-083] A78-319112 COHTBOL SDBFACES The HFB 320 airborne simulator of OF7LR as test Tunnel interference assessment by boundary instrument for determining flight characteristics measurements fDGLR PAPER 77-082] A78-319H1 A78-30689 Proposal and construction of a hybrid flight-sight A study of low-cost reliable actuators for light simulator with large picture projection aircraft. Part A: Chapters 1-8 fDGLR PAPEE 77-087] A78-31945 [NASA-CB-156142] S78-20110 The Dual-Flight-Simulator on the evaluation of air A study of low-cost reliable actuators for light combat effectiveness aircraft. Part B: Appendices [DGLR PAPEB 77-080] A78-31918 [NASA-CB-1561Q3] B78-20111 Hew aspects in the movement simulation of the COHTBOL TBBOBY research flight simulator of DFVLB Observability criteria for nonlinear dynamic [DGLR PAPEB 77-086] A78-31950 systems subjected to mnltiparameter measurements The impact of a proposed active BC?S on ATCBBS noting air navigation applicability performance in the Washington, D. C., 1981 A78-29089 environment The helicopter as a control object Russian book rAD-AO«8589/6] N78-20099 A78-29101 Program for simulation of air traffic and air Optimal control theory (OSBB) applied to a space structure of the Frankfurt near range, a helicopter in the hover and approach phase planning control and a collision avoidance [NASA-CB-152135] B78-21161 system with situation dependent avoidance COHTBOL VALVES maneuvers Properties of hydraulic servomotor controlled by K78-20105 flapper valve or by edge valve turbojet engine system A78-29587

A-10 SUBJECT IHDBI DECAY BATES

COHTBOLLEBS CB4CRS A study of Ion-cost reliable actuators for light Stress analysis of typical flaws in aerospace aircraft. Part A: Chapters 1-8 structural components using 3-D hybrid [BASA-CB-156142] H78-20110 displacement finite element method f study of Ion-cost reliable actuators for light [AIAA 78-513] A78-29812 aircraft. Part B: Appendices CB4SB LABDIBG fNASA-CE-156143] H78-20111 Aircraft accident report: Southern Airways Inc., COBVECTIOS DC-9-31, H13350, Hew Hope, Georgia, April H, 1977 Investigations of the local heat transfer [HTSB-AAB-78-3] S78-2106U coefficient of a convection cooled rotor blade CBOSS FLOi H78-21126 Experimental investigation of effect of jet decay COBVECTIVB F10I rate on jet-induced pressures on a flat plate Bean velocity, tarbolence intensity and turbulence THASA-CB-2979] B78-21096 convection velocity measurements for a CBODE OIL convergent nozzle in a free jet wind tunnel Aviation fuels - 4 supplier's perspective [RASA-CB-2949] N78-21058 A78-31308 COBVBBGEST BOZZIBS CB10GEHIC «ISD TTISBS1S Hean velocity, turbulence intensity and turbulence An intermittent high Reynolds number wind tunnel convection velocity measurements for a [AIAA 78-766] A78-32327 convergent nozzle in a free jet wind tunnel Condensation and its growth down the test-section [NASA-CB-29U9] N78-21058 of the Langley 0.3-m transonic cryogenic tunnel COHVEBGEBT-DIVEBGEHT BOZZ1ES [AIAA 78-811] 478-32365 Boundary-layer interaction with a noneqnilibrium Onset of condensation effects with a HACA 0012-64 two-phase stream on a surface being burned out airfoil tested in the Langley 0.3-meter in an axisymnetric laval nozzle cryogenic tunnel A78-28610 [NASA-TM-78666] N78-20074 COOLAHTS CV-340 AIBCBAFT The influence of coolant turbulence intensity of Flight test results of the Strapdown hexad film cooling effectiveness Inertial Heference Onit (SIED). Volume 3: N78-21136 Appendices A-G COOLING STSTEHS fHASA-Tll-73224] 1178-20098 Effect of cooling-hole geometry on aerodynamic CTLIUDBICAL SHELLS performance of a film-cooled turbine vane tested Cutout reinforcement of stiffened cylindrical shells with cold air in a two-dimensional cascade [JIAA 78-512] 478-29811 [NASA-TP-1136] N78-20080 On sound transmission into a heavily-damped cylinder High temperature problems in gas turbine engines aircraft noise in fuselage [AGABD-CP-229] N78-21118 478-31019 Heat transfer characteristics of the closed thermosyphon system IO8-21132 Heasnring tecbnigues in high temperature turbines DABAGE N78-21151 Correlation study of the aH-18 helicopter blast COBBELATOES test results from the DICE-THBOB event Design of a collision avoidance system model with [AD-A050U63] N78-20122 statistical interrogation separation and DABPIBG collision avoidance by nonsynchronons technigues Subsonic roll damping of a model with swept-back (SECAHT) and swept-forward wings H78-20107 [NASA-TM-78677] N78-20061 COBKOSIOH BESISTiNCE DAHPIBG TESTS Cobalt-base alloys for hot corrosion protective Steady-state unbalance response of a three-disk coatings flexible rotor on flexible, damped supports N78-21142 A78-29326 COST ANALYSIS DATA ACQOISITIOH A new method for estimating current and future The induction driven tunnel T2 at ONEBA-CEBT - transport aircraft operating economics Flow qualities, testing techniques and examples [NASf-CB-1l(5190] N78-20091I of results S life cycle cost study of contractor versus [AIAA 78-767] A78-32328 organic support of aircraft programs DATA COBBELATIOB [AD-A019U38] H78-210H5 Correlation of laser velocimeter measurements over Fiber optics Cost Analysis Program (FOCAP) a wing with results of two prediction techniques [4D-4019859] N78-21105 in the Langley V/STOL tunnel COST EFFECTITEBESS [SASA-TP-1168] H78-21U10 ''be Dnal-rlight-Sitralator as an aid for a DATA B&BAGEBEBT government mission specialist TESTPLT: Interactive computer procedure for [OGLE PAPEB 77-079] A78-319U9 wind-tunnel-data management, retrieval, Joint ASD/AF^AL Combined Environment Beliability comparison, and plotting Test /CEBT/ Evaluation Program tNASA-TB-78663] H78-201UU 478-32118 DATA SfSTEHS A review of methodologies and concepts tc measure Bunway roughness characterization by DDS approach and evaluate aircraft survivability/vulnerability Dynamic Data System TAD-A050152) N78-21099 478-30679 COST BBDOCTIOH The Boeing Aerodynamic Labs data system The AH/ABC-161 radio - Life-cycle-cost savings [AIAA 78-789] A78-32316 OHF communication eguipment reliability and Investigation of a high speed data handling system maintainability improvement for use with maltispectral aircraft scanners 478-291179 [SAS4-TB-78689] B78-20181 Benefits of strapdown over global INS systems for DATA TBABSBISSIOB aircraft application Flight tests of digital data transmission HSK A78-30253 - a quadrature PSK system Bemotely piloted aircraft in the civil environment A78-31050 478-30506 DC 9 AIBCBAFT CBACK PBOPAGATIOS Mrcraft accident report: Southern Airways Inc., Acoustic emission detection of fatigue crack DC-9-31, H1335D, Hew Hope, Georgia, April 1, 1977 growth in a production-size aircraft wing test [NTSB-AAB-78-3] B78-21061 article under simulated flight loads DECAY BATES 478-31733 Experimental investigation of effect of }et decay rate on jet-induced pressures on a flat plate [HASA-CH-2979] B78-21096

A-11 DECBLEBATIOB SUBJECT INDEX

DECBLEB1TION DOPPLEB EFFECT Ground distance covered daring airborne horizontal Doppler BLS - The OK solution deceleration of an airplane A78-2993U tHASA-TP-1157] N78-20115 DOPPLEB NAVIGATION DELIS RINGS Microwave landing systems time reference Normal force of a flat triangular wing in a scanning beam used to determine aircraft approach supersonic flow A78-29221 A78-29720 Integrated Doppler/TACAN navigation through DESCENT TBAJBCTOBIES conformity with the least squares method - A simple method for estimating minimum Analysis from registered flight data autorotative descent rate of single rotor 478-29906 helicopters DBAS [NASA-TH-781452] 178-20113 Transonic-wind tunnel tests on two-dimensional DESIGN ANALYSIS aerofoil sections. Determination of pressure Determining the reliability requirements of distribution and drag for an aerofoil with a aircraft engine control systems during design modified HACA 65 sub2-215 section in FFA wind stage tunnel S5, part 2 A78-29590 [FFA-TN-4U-725] 1178-21062 DIESEL ENGINES DBAG BEDOCTION Lightweight, low compression aircraft diesel engine Supersonic transports drag minimization converting a spark ignition engine to the techniques diesel cycle 678-31152 CHASA-CB-135300] N78-211471 Hodel support system interference on zero-lift DIFFOSEBS drag at transonic speeds Investigation of the flow in a plane diffuser by [AIAA 78-809] A78-32363 means of a laser Doppler anemometer DBOP TESTS A78-28969 Crashworthiness of aircraft fuselage structures Effect of boundary layer suction through slits on [AIAA 78-U77] A78-29785 the efficiency of turbomachine outlet diffusors DUCTED FAN ENGINES A78-30572 The aircraft ducted fan DIGITAL COBPOTEBS 678-31153 Main characteristics of the ADT 11000-1100 digital DYNiHIC CONTBOL computer for a hybrid computing system for Observability criteria for nonlinear dynamic jet engine simulation systems subjected to multiparameter measurements A78-29589 noting air navigation applicability DIGITAL BADAB SYSTEBS A78-29089 On the possibility of classifying radar targets Basic problem of control of the motion of a with a coherently measured echo signal non-Newtonian fluid in a gap roll forming of German book aircraft plastics 478-32308 A78-32257 DIGITAL SIHOLATION DYNABIC BESPONSE Digital computer program maneuver pilot Crashworthiness of aircraft fuselage structures A78-31916 [AIAA 78-1177] A78-29785 DIGITAL STSTEHS DYNABIC STABILITY Dse of a stepping motor for measuring fuel Influence of spin rate on side force of an quantity in a digital system for control of axisymmetric body rotational speed A78-30690 A78-29586 DYNABIC STHOCTOBAL ANALYSIS New trends and problem areas in automatic flight Crashworthiness of aircraft fuselage structures control [AIAA 78-U77] J78-29785 A78-30252 A fail-safe analysis of a spanwise wing-panel splice Plight tests of digital data transmission MSK [4IAA 78-187] A78-29791 - a guadratnre PSK system Dynamic stability of a two blade rotor A78-31050 A78-32037 A rotor-mounted digital instrumentation system for Analysis and synthesis of operational loads helicopter blade flight research measurements aircraft structures [NASA-TP-1146] 1178-20128 [ISD-193] 1178-20551 DIGITAL TECHNIQUES Evaluation of a ceramic combustion chamber for a New aspects in the movement simulation of the small gas turbine engine research flight simulator of DPV1B N78-21105 [DG1B PAPEB 77-086] A78-31950 DIBECTIONAL CONTBOL Expansion of flight simulator capability for study and solution of aircraft directional control ECONOHIC ANALYSIS problems on runways An economic analysis of a government sponsored, [NASA-CR-2970] H78-20118 commercial convertible aircraft DISCONTIHOITT [4D-A0117633] N78-20096 Calculation of supersonic flows past wings with Technical and economic evaluation of advanced air allowance for trailing tangential cargo systems discontinuities within the framework of a model [NASA-IH-78672] B78-20108 employing a system of Enler equations EJECTOBS A78-28958 Ejector-powered engine simulators for small-scale DISPLAY DEVICES wind tunnel models of high performance aircraft Proposal and construction of a hybrid flight-sight [AIAA 78-826] A78-32388 simulator with large picture projection ELASTIC BODIES TDGLB PAPER 77-087] A78-319U5 Stress analysis of typical flaws in aerospace Cockpit displayed traffic information study, part 2 structural components using 3-D hybrid fNASA-CB-156115] 1178-20102 displacement finite element method Results of a simulator test comparing two display [AIAA 78-513] A78-29812 concepts for piloted flight-path-angle control ELECTBODYNABICS r NASA-TM-78692] N78-21101I Lifting force of a plane H-polanzed DISTANCE HEASOBING EQOIPHENT electromagnetic wave Desiqn of a collision avoidance system model with A78-32296 statistical interrogation separation and ELECTHOLYTES collision avoidance by nonsynchronous techniques Nickel/cadmium aircraft batteries: Bapid (SECANT) electrolyte exchange technique 1178-20107 [AD-A039335] 1178-20632

A-12 SUBJECT IHDEI EHVIBOBHEHT RODELS

ELECTBOiiGHETIC COflPlTIBIlITT Measuring technigues in high temperature turbines Interference analysis between TBSB microwave N78-21151 landing system and adjacent C-band radars few computation method of turbine blades film CAD-A019882] 1178-20101 cooling efficiency ELECTBOBA6HETIC IBTBBFEBEHCB N78-21151 Interference analysis between TBSB microwave Calculation of temperature distribution in disks landing systen and adjacent C-band radars and cooling flow in a transient state [AD-A019882] 878-20101 H78-21157 ELECTBOBIC COHTBOI EUGIHE DESIGB Osing simulation to determine the transfer General aviation energy-conservation research function of the electronic part of a ccntrol loop programs at BASA-Levis Besearch Center for for gas turbine aircraft engines non-turbine general aviation engines A78-29581 A78-29330 E1ECTBOHIC CODBTBBHEJSOBES Influence of structural components of a by-pass The next generation EH system - ASPJ Airborne engine on its flight characteristics STOL Self Protection Jammer aircraft A78-31700 A78-29582 ELECTHOHIC ECOIP1EBT TESTS Hain characteristics of the PDT 1000-1100 digital Effect of reliability programs on life cycle cost computer for a hybrid computing system for - \ case history of TACAN test set jet engine simulation A78-29178 A78-29589 Joint ASD/AFSAL Combined Environment Eel lability Evolution of the aircraft gas turbine engine Test /CEBT/ Evaluation Program A78-30257 A78-32118 Choice of engine design for small transport aircraft Practical experience in vibration testing external J78-30357 avionics systems The aircraft ducted fan A78-32131 A78-31153 BLECTBOHIC HODOIES Aircraft fuel economy - The propulsion system Stand-alone development system using a KIil-1 contribution microcomputer module A78-31309 rNASA-CB-156067] N78-20100 Energy conserving aircraft from the engine viewpoint ELBCTBOST4TIC SBOBES A78-31310 Further experimental evaluation of the Helicopter freewheel unit design guide electrostatic roll sensor at lach 2.3 and 3.5 IAD-A017559] 878-20121 [AIAA 78-802] A78-32357 Bectangular capture area to circular combustor ELLIPSOIDS scranjet engine Choice of optimal ellipsoid-surface projection [8ASA-TM-78657] 878-21107 onto a sphere in solving problems of air Performance and design of transportation-cooled navigation turbine blading A78-28523 N78-21129 EHEBGY. COHSEBTATIOH High temperature H2-Air variable geometry Aviation fuel usage - Economy and conservation combustor and turbine: Test facility and A78-30698 measurements The NASA Aircraft Energy Efficiency Program B78-21137 A78-31302 Low freguency combustion instability in augmentors Prospects for energy conserving ST01 transports 878-21138 using prop-fans Effects of film injection on performance of a A78-31303 cooled turbine Some aspects of powerplant airframe integration 878-21117 affecting fuel conservation EHGIBB NOISE S78-3130H Investigation of interior noise in a twin-engine Improved energy efficiency for small CT01 light aircraft transport aircraft A78-29611 A78-31305 Aircraft noise and its sources Fuel saving potential of fiach 0.8 twin engine A78-30351 prop-fan transports EFGISE PABTS H78-31306 Gas path sealing in turbine engines Aviation fuels - A supplier's perspective [BASA-TM-73890] N78-21109 A78-31308 The measurement of film cooling effectiveness on Energy conserving aircraft from the engine viewpoint turbine components in short duration wind tunnels A78-31310 878-21152 Thrust computing system applications to increase EHGIBE TESTS engine life and provide fuel conservation 'Chain pooling* model selection as developed for A78-31311 the statistical analysis of a rotor burst Air traffic control and energy conservation in air protection experiment operations A78-29327 A78-3131M Unique test capabilities of the Eglin AFB BcKinley BHEBGY COSVEBSIOB BFFICIEBCY Climatic Laboratory The effect of hub fairings on wind turbine rotor A78-32127 performance An engine nozzle vibration phenomenon encountered A78-30039 in B-1 flight tests EHGISE C08TB01 A78-32129 Determining the reliability reguirements of Design and snbscale tests of a diffuser system for aircraft engine control systems during design a (lach 1 scramjet test facility stage [AIAA 78-771] A78-32332 A78-29590 Hot cascade test results of cooled turbine blades A reliable modular automatic system adapted to and their application to actual engine conditions avionics controls: Design through successive N78-21125 refineoents - Production French book Lightweight, low compression aircraft diesel engine A78-30021 converting a spark ignition engine to the Thrust computing system applications to increase diesel cycle engine life and provide fuel conservation [HASA-CB-135300] N78-21171 A78-31311 EBVIBOBHEHT EFFECTS EHGIBE COOLAITS Hore public consultation on airport plans 1 review of technigues for the thermal protection A78-29208 of the walls of the combustion chamber and E5VIBOIBEIT BODBLS reheating ducts of turboreactors Air guality impact of aircraft at ten D.S. Air N78-21131 Force bases A78-32222

A-13 EBVIBOHHEHT PBOTBCTIOB SUBJECT IHDEX

ENVIBOHBEHT EBOTBCTIOH A fail-safe analysis of a spanwise wing-panel splice Airport/community environmental planning [AIAA 78-1187] A78-2979

A-11 SUBJECT IBDEX FLIGHT BBCBAHICS

Hirage 2000 French flighter aircraft design FIBE PBEVEHTIOH characteristics, SNECHA H53 engine and avionics Some lessons learned fron aircraft accidents - The 478-31755 engineering aspects The Dnal-Flight-Simulator on the evaluation of air A78-29936 combat effectiveness FLABB HOLDEBS [DGLB PAPER 77-080] A78-31918 Catalytic flame stabilization for aircraft Subsonic longitudinal and lateral-directional afterburners static aerodynamic characteristics of a general A78-31955 research fighter configuration employing a jet FLABE PBOPAGATIOB sheet vortei generator Time-dependent fire behavior of aircraft cabin [NASA-TH-70049] R78-20071 materials nulti-variate optimization problems of flight [AD-A050923] H78-2123H vehicle synthesis FIABE BETABDAHTS [PB-276123/7] 178-21103 Fire resistivity and toxicity studies of candidate Hnltiband antenna system for tactical aircraft aircraft passenger seat materials [AD-A049699] N78-21363 [HASA-TH-78«68] R78-21211 FILH COOLIHG FLARE STABILITY Effect of cooling-hole geometry on aerodynamic Catalytic flame stabilization for aircraft performance of a film-ceded turbine vane tested afterburners vith cold air in a two-dimensional cascade A78-31955 [NASA-TP-1136] N78-20080 FLAHBiBILITY Two-dimensional cold-air cascade study of a Fire resistivity and toxicity studies of candidate filn-cooled turbine stator blade. 1: aircraft passenger seat materials Comparison of experimental and analytical [NASA-TH-78U68] N78-212KI aerodynamic results for blade with 12 rows of Aircraft cargo compartment fire test simulation 0.076-centimeter-(0.030-inch-) diameter holes program having streamwise ejection angles [NASA-CR-151951] R78-21223 [BASA-TP-1151] N78-20130 FLAT PLATES Two-dimensional cold-air cascade study of a An analytic study of free molecule flow fields at film-cooled turbine stator tlade. 5: the front and back edges of a plate Comparison of experimental and analytical A78-28972 aerodynamic results for blade with 12 rows of Experimental investigation of effect of jet decay 0.038-centineter-(0.015 inch) diameter coolant rate on jet-induced pressures on a flat plate holes having streamwise ejection angles [NASA-CB-2979] S78-21096 [NASA-TP-120

FLIGBT OPTIBIZiTIOH Results of a simulator test comparing two display The problem of choosing design parameters for concepts for piloted flight-path-angle control unpiloted flight-vehicles control configured [HASA-TH-78692] N78-2110U optimization FLIGHT SIBDLATOBS A78-32258 Current problems of flight simulators for research Optimization of the design parameters of finned A78-2921Q pilotless flight vehicles Handling qualities of aircraft in the presence of 478-32269 simulated turbulence Optimization of linear stabilization systems of A78-29613 flight vehicles on the basis of orthogonal filters The wind and turbulence measuring system of the A78-32270 NAE Airborne V/STOL Simulator PLIGHT PiTHS A78-30850 Hore about flight-path-angle transitions in The HFB 320 airborne simulator of DFVLR as test optimal airplane clmbs instrument for determining flight characteristics A78-32098 [DGLE PAPEB 77-082] A78-319H1 Simulator evaluation of a flight-path-angle Proposal and construction of a hybrid flight-sight control system for a transport airplane vith simulator with large picture projection direct lift control [DGLB PAPEB 77-087] A78-319I15 [NASA-TP-1116] N78-20139 The Dual-Flight-Simulator as an aid for a Results of a simulator test comparing two display government mission specialist concepts for piloted flight-path-angle control [DGLR PAPEB 77-079] A78-31949 [NASA-TN-78692] N78-21101 Summary of NASA landing gear research FLIGHT SiFETT [NASA-TM-78679] K78-20050 Clear air turbulence accidents Expansion of flight simulator capability for study A78-28833 and solution of aircraft directional control Fault tolerant flight controls problems on runways A78-28900 [NHSA-CR-2970] N78-20118 How to make an airport unattractive to birds Simulator evaluation of a flight-path-angle A78-29209 control system for a transport airplane with Systematic analysis of safety in aviation. II direct lift control 1178-296711 [NASA-TP-1116] N78-20139 Some test results concerning visibility of Besults of a simulator test comparing two display obstacle and hazard beacons concepts for piloted flight-path-angle control A78-29907 [NASA-TH-78692] N78-21101I Air traffic safety in the airport near range FLIGHT TESTS CTOBS/SFB58/MII] N78-20103 Integrated Doppler/TACAH navigation through Simulation and development possibilities of the conformity with the least squares method - manual control concept in the near range and Analysis from registered flight data control zone A78-29906 N78-20->Oit Benefits of strapdown over gimbal INS systems for Investigation to support phase 1 of the DSAF aircraft application midair prevention systems program (HAPS) A78-30253 [AD-A0497U3] N78-21066 Performance of the AEAVA aircraft with wing-tip FLIGHT SIHtJLATIOH winglets Advanced flight decks for the 80s cockpit A78-30256 design for transport aircraft Analytical and experimental fatigue program for 178-28835 the Kfir main and nose landing gears Flight simulation - A vital and expanding A78-30259 technology in aircraft development Flight tests of digital data transmission HSK [AIAA PAPIB 78-337] A78-29295 - a quadrature PSK system Acoustic emission detection of fatigue crack A78-31050 growth in a production-size aircraft wing test The HFB 320 airborne simulator of DFVLB as test article under simulated flight loads instrument for determining flight characteristics A78-31733 [DGLR PAPEB 77-082] A78-31914 Use of and experience with simulation in the An engine nozzle vibration phenomenon encountered development of the VFH 61i| and the VAK 191 in B-1 flight tests [DG1H PAPER 77-083] A78-319I12 A78-32129 Simulation in the development of the training and Supersonic aerothermal testing - A new requirement ground-attack aircraft Alpha Jet [AIAA 78-773] A78-32333 A78-31943 The AEDC Range K facility for erosion testing Digital computer program maneuver pilot [AIAA 78-775] A78-32330 A78-319I16 Research on various aspects of atmospheric flight The Dual-Flight-Simulator on the evaluation of air CAD-A033681] N78-20088 combat effectiveness Flight test results of the Strapdown hexad [DGLS PAPEB 77-080] A78-31918 Inertial Beference Dnit (SIRO). Volume 3: New aspects in the movement simulaticn of the Appendices A-G research flight simulator of DF71R [SASA-TB-7322U] N78-20098 [DGLR PAPEB 77-086] A78-31950 A rotor-mounted digital instrumentation system for Simulation tests of anti-flak profiles helicopter blade flight research measurements aircraft flight optimization for ground attack [HASA-TP-1116] F78-20128 mission Flight evaluation of the transonic stability and A78-31951 control characteristics of an airplane Moving ground simulation by tangential blowing incorporating a supercritical wing fAIAA 78-81«l A78-32368 r NASA-IP-1167] N78-201I)0 Cockpit displayed traffic information study, part 2 Hesults of a simulator test comparing two display rNASA-CE-156115] N78-20102 concepts for piloted flight-path-angle control Expansion of flight simulator capability for study [NASA-TH-78692] S78-21101 and solution of aircraft directional control Results from flight and simulator studies of a problems on runways Hach 3 cruise longitudinal autopilot [NASA-CB-2970] N78-2C118 [NASA-TP-1180] N78-21160 Simulated flight effects on noise characteristics FLIGHT VEHICLES of a fan inlet with high throat Hach number Automatic sustainment of resonance conditions in [NASJ-TP-1199] N78-20132 the multipoint excitation of flight-vehicle Pilot-model analysis and simulation study of vibrations effect of control task desired control response A78-32268 [NASA-TP-11HO] 178-201*3 Optimization of linear stabilization systems of Fvaluation of windshield materials subjected to flight vehicles on the basis of orthogonal filters simulated supprscnic flight S78-32270 [AD-AOU9981] N78-21101

A-16 SUBJECT IHDEI FUEL COHSORPTIOB

PlOW CH»BiCTBBISTICS FOKKEB AIRCBAFT } critical examination of expansion tunnel Ose of and experience with simulation in the pefformance development of the 7FH 611 and the VAK 191 [AJAA 78-768] J78-32329 [DGIB PAPEB 77-083] A78-31912 ?n experimental investigation of oscillating flows FOBCE DISTBIBDTIOH over an airfoil rotary vings Influence of spin rate on side force of an 178-20058 axisynmetric body Theoretical flow characteristics of inlets for A78-30690 tilting-nacelle VT01 aircraft FOBEBODIES [HASA-TP-1205] H78-2111U Drag formula for elongated aircraft noses FLOS EQOiTIOBS A78-29718 fn analytic study of free molecule flow fields at A computer-controlled video instrumentation the front and bacX edges of a plate technique for wind tunnel testing of full-scale A78-28972 lifting parachutes Engineering calcnlation uethods for tnrbolent [AIAA 78-785] A78-32303 flow, volume 1 PRACTOGBAEHt [IC-AEEO-77-102-VOL-1 ] R78-20091 Hicrofractographic fracture analysis of some Engineering calcalation methods for turbulent aircraft parts flow, volume 2 A78-28789 [IC-AEBO-77-102-V01-2] S78-20092 PBACTUBE BECBARICS Engineering calculation methods for turbulent Report on aircraft fatigue studies in-flight flow, volume 3 monitoring and stress measurements [IC-AEBO-77-102-VOL-3] N78-20093 [AD-A019876] S78-21102 FLOf 6EOHETBT FBACTDBE STRENGTH Hydroaynaoic effect on a contour produced by an Hicrofractographic fracture analysis of some ideal incompressible flow of constant vorticity aircraft parts A78-28956 A78-28789 FLOH HEASOREBEHT FBEE FLOS Investigation of the flow in a plane diffuser by Onset of condensation effects with a HACA 0012-61 means of a laser Doppler anemometer airfoil tested in the Langley 0.3-meter 478-28969 cryogenic tunnel Tunnel interference assessment by boundary [NASA-TH-78666] N78-20071) measurements The effect of free-stream turbulence upon heat A78-30689 transfer to turbine blading Some measurements in twc-dimensional turbulent wakes S78-21155 878-31836 FBEE JETS A technique for vorticity measurement in unsteady nean velocity, turbulence intensity and turbulence flow convection velocity measurements for a [AIAA 78-801] A78-32356 convergent nozzle in a free jet wind tunnel PlOi STABILITY [HASA-CB-2949] K78-21058 Stability of subsonic gasdynamic flows FBEE BOLBCOLAB FLOW A78-28959 An analytic study of free molecule flow fields at FLOW VBJ.OCIT1 the front and back edges of a plate lean velocity, turbulence intensity and turbulence A78-28972 convection velocity measurements for a FBEOH convergent nozzle in a free ]et wind tunnel Comparison of aerodynamic data measured in air and [NASA-CB-29t9] N78-21058 Freon-12 wind-tunnel test mediums F10» VISDillZATIOH [HASA-TM-78671 ] B78-21052 The induction driven tunnel T2 at ONEBA-CERT - FBEQOEBCY COHTB01 Flow qualities, testing techniques and examples Development of a binary freguency synthesis as of results control element for frequency correction in [AIAA 78-767] A78-32328 time-synchronous collision systems without An experimental investigation of oscillating flows onboard atomic frequency standard avoidance over an airfoil rotary wings M78-20106 N78-20058 FBEQUEBCI SYHCBBONIZATIOH FLUID BOOHDARIBS Development of a binary freguency synthesis as Hydrodynamic effect on a contour produced by an control element for freguency correction in ideal incompressible flow of constant vorticity time-synchronous collision systems without A78-28956 onboard atomic frequency standard avoidance PLDIDIZBD BED PBOCESSCBS N78-20106 The use of fluidized beds for heating air for wind FBEQOEHCT SYHTHESIZEBS tunnels Development of a binary frequency synthesis as [Alii 78-818] A78-32372 control element for frequency correction in FLOTTEB time-synchronous collision systems without The use of transient testing techniques in the onboard atomic frequency standard avoidance Boeing YC-1U flutter clearance program N78-20106 (AIAA 78-505] A78-29806 FRICTIOH Aeroelastic analysis and ground vibration survey Aerodynamic fluid-fiber interactions of the NASA, Grumman American Yankee modified [BT-77-CN-1] N78-20060 for spin testing FDSL COHSOHPTION [SiSA-CR-156119] H78-20109 General aviation energy-conservation research FIOTTBB »H»LISIS programs at RASA-Lewis Besearch Center for Prediction of the unsteady airloads on non-turbine general aviation engines harmonically oscillating spheroids based on an A78-29330 analytical solution of the governing wave equation Aviation fuel usage - Economy and conservation A78-29338 A78-30698 Theory of bending-torsional self-oscillaticns of Improved energy efficiency for small CTQl an aircraft wing system transport aircraft A78-3226U A78-31305 Automatic snstainment of resonance conditions in Fuel saving potential of Bach 0.8 twin engine the multipoint excitation of flight-vehicle prop-fan transports vibrations A78-31306 A78-32268 Fuel efficiency - where we are heading in the FLI BI BIBB COHTBOl design of future jet transports Fly-by-wire flight control A78-31307 H78-29935 Aircraft fuel economy - The propulsion system contribution A78-31309

A-17 FUEL SYSTE8S SUBJECT IHDEI

Thrust computing system applications to increase GAS HEATING engine life and provide fuel conservation The use of fluidized beds for heating air for wind A78-31311 tunnels •5TOL system fuel savings - Ground and air [AIAA 78-818] A78-32372 A78-31312 GAS TOBBINE EHGINES The energy costs of some noise abatement procedures Control of aircraft turbine engine acceleration A78-31313 A78-29583 air traffic control and energy conservation in air Osing simulation to determine the transfer operations function of the electronic part of a control loop A78-3131U for gas turbine aircraft engines Fuel conservation merits of advanced turboprop A78-2958H transport aircraft Evolution of the aircraft gas turbine engine [NASA-CB-152096] N78-21095 A78-30257 FOB! SYSTEBS Energy conserving aircraft from the engine viewpoint Fuel pressure increase limiter A78-31310 [AD-AQU9393] N78-21117 Nitric oxide formation in ga.s turbine engines: A FDEL TANKS theoretical and experimental study Design, fabrication, and testing of a full-scale [NASA-CB-2977] N78-21116 breadboard in nitrogen generator for fuel tank High temperature problems in gas turbine engines inerting application [AGAED-CP-229] N78-21118 [AD-A01I9U59] N78-21097 Project optimisation of military gas turbines with FUEL TESTS respect to turbine life Properties of fuels used in the Czechoslovak N78-21120 aircraft industry Problems concerning high temperatures in small A78-29588 turbomachines FUEI VALVES N78-21121 Dse of a stepping motor for measuring fuel Hot cascade test results of cooled turbine blades gnantity in a digital system for ccntrcl of and their application to actual engine conditions rotational speed N78-21125 A78-29586 Investigations of the local heat transfer FOEL-AIB BATIO coefficient of a convection cooled rotor blade Nitric oxide formation in gas turbine engines: A N78-21126 theoretical and experimental study Investigation on temperature distribution near [VASA-CE-2977] N78-21116 film cooled airfoils FULL SCALE TESTS N78-21127 Status and operational characteristics of the Erosion prevention and film cooling on vanes National Transonic Facility N78-21128 [AIAA 78-770] A78-32331 Performance and design of transportation-cooled Supersonic aerothermal testing - A new requirement turbine blading CAIAA 78-773] A78-32333 S78-21129 A computer-controlled video instrumentation The influence of transpiration cooling on turbine technigue for wind tunnel testing of full-scale blade boundary layer lifting parachutes N78-21130 [AIAA 78-785] A78-32343 Experimental evaluation of a transpiration cooled FOHCTIOHAI ANALYSIS nozzle guide vane variational principles for the transonic airfoil N78-21131 problem Heat transfer characteristics of the closed A78-30891 thermosyphon system FDSELAGES N78-21132 Computation of the pressure on the surface of a Practical solutions to the cooling of combnstors fuselage with a wing in an ideal fluid operating at high temperatures A78-29712 N78-21135 Crashwortbiness of aircraft fuselage structures The influence of coolant turbulence intensity of [AIAA 78-1(77] A78-29785 film cooling effectiveness On souni transmission into a heavily-damped cylinder N78-21136 aircraft noise in fuselage High temperature H2-Air variable geometry A78-31019 combustor and turbine: Test facility and measurements N78-21137 Low freguency combustion instability in augmentors GALEBKIR HBTBOD N78-21138 Unsteady two dimensional airloads acting on New materials for high temperature turbines: oscillating thin airfoils in subsonic ventilated ONEEA's DS composites confronted with the blade wind tunnels problems [NASA-CB-2967] N78-21059 H78-21139 GAS DISCHARGES Cobalt-base alloys for hot corrosion protective Nickel/cadmium aircraft batteries: Multichannel coatings gassiiig-rate meter B78-211II2 [AD-A039735] N78-20636 Evaluation of a ceramic combustion chamber for a GAS EXPABSIOB small gas turbine engine A critical examination of expansion tunnel N78-21U5 performance Systematic studies of heat transfer and film [AIAA 78-768] A78-32329 cooling effectiveness GAS FLOS N78-211U6 Stability of subsonic gasdynamic flows Effects of film injection on performance of a A78-28959 cooled turbine Transonic flows past a lift profile H78-21U7 A78-28961 Pleasuring techniques in high temperature turbines Three-dimensional flow of hypersonic gas past a N78-21151 thin airfoil The measurement of film cooling effectiveness on A78-30002 turbine components in short duration wind tunnels GAS GENEEATOES H78-21152 Design, fabrication, and testing of a full-scale New confutation method of turbine blades film breadboard in nitrogen generator for fuel tank cooling efficiency inerting application R78-21154 [AD-AOU94591 N78-21097 The effect of free-stream turbulence upon heat transfer to turbine blading N78-21155

A-18 SUBJECT INDEX BELICOPTEBS

Calculation of tenperature distribution in disks GTBOSCOPES and cooling flow in a transient state Gyroscopic instruments of orientation and H78-21157 stabilization systems Bussian book G1S TOBBIHBS A78-29859 Effect of boundary layer saction through slits on GTBOSTABIIIZEBS the efficiency of turbomachine outlet diffusors Gyroscopic instruments of orientation and A78-30S72 stabilization systems Bnssian book GBSEBAL AVIATIOH ilBCBAFT A78-29859 General aviation energy-conservation research programs at NASA-Lewis Research Center for non-turbine general aviation engines H 478-29330 HABBOBIC OSCILLATION Aircraft fuel economy - The propulsion system A note on mnlticyclic control by swashplate contribution oscillation A78-31309 [NASA-TH-78

A-19 HIGH FREQUENCIES SUBJECT INDEX

AH-1S high-survivable transmission system HYPEBSOBIC AIBCFBFT [AD-AOU7558] N78-20123 Thermal design for areas of interference heating Helicopter freewheel unit design guide on actively cooled hypersonic aircraft [AD-AOU7559] N78-2012<1 [SASA-CB-2828] N78-20117 A life cycle cost study of contractor versus Experimental and finite element investigation of organic support of aircraft programs the buckling characteristics of a beaded skin [AD-A049U38] N78-210H5 panel for a hypersonic aircraft Research requirements to improve reliability of [BASA-CB-11U863] N78-20534 civil helicopters BYPESSOSIC FLOW [NASA-CB-115335] JJ78-21093 Three-dimensional flow of hypersonic gas past a Optimal control theory (OHEB) applied to a thin airfoil helicopter in the hover and approach phase A78-30002 [NASA-CB-152135] N78-21161 HYPEBSOBIC HEAT TRANSFER HF radiation characteristics of the BH-53D Hypersonic heat transfer test program in the VKI helicopter and the Bark 105 AHCM system longshot facility ogive body configuration [AD-AOK979S] N78-21358 [SD-A050295] N78-20086 HIGH FEEQDEHCIES HYPBB7B10CITI PBOJECTILES HF radiation characteristics of the HH-53D The AEDC Bange K facility for erosion testing helicopter and the Bark 105 ABCB system [AIAA 78-775] A78-32334 [AD-AOU9795] N78-21358 HIGH PBESSOHB Dse of leaning vanes in a two stage fan [NASA-CF-152131] N78-21115 IDEAL FLBIDS HIGH TEHFEBATOBE Hydrodynamic effect on a contour produced by an High temperature problems in gas turbine engines ideal incompressible flow of constant vorticity [AGABD-CP-229] N78-21118 A78-28956 Practical solutions to the cooling of combustors Computation of the pressure on the surface of a operating at high temperatures fuselage with a wing in an ideal fluid N78-21135 A78-29712 HIGH TEBPERATDEE EBVIBOBBEBTS IHPOtSE GEBEBATOBS Problems concerning high temperatures in small Comparison of measured and calculated helicopter turbomachines rotor impulsive noise wind tunnel test data N78-21121 and prediction analysis techniques Measuring technigues in high temperature turbines [NASA-TM-781173] N78-20917 N78-21151 IB-FLIGHT BOBITOBIHG HOLE DISTHIBOTIOH (HECHABICS) Beport on aircraft fatigue studies in-flight Effect of cooling-hole geometry on aerodynamic monitoring and stress measurements performance of a film-cooled turbine vane tested [AD-AOH9876] N78-21102 with cold air in a two-dimensional cascade IHCIDEHT BADIATIOB [NfSA-TP-1136] 1178-20080 lifting force of a plane H-polarized HOBIZOBTAl TAI1 SURFACES electromagnetic wave Optimum tail plane design for artificially A78-32296 stabilized aircraft IBCOSPBESSIBIE PLOW A78-2933I1 Hydrodynamic effect on a contour produced by an HOVEBIHG STABI1ITT ideal incompressible flow of constant vorticity Optimal control theory (OWES) applied to a A78-28956 helicopter in the hover and approach phase On the calculation of the incompressible flow past [NASA-CB-152135] 1178-21161 an aerofoil with a jet flap HOBS A78-31838 The effect of hub fairings on wind turbine rotor IBEBTIAL BAVIGITIOB performance Integrated Doppler/TACAN navigation through A78-30039 conformity with the least squares method - HDHiB FACTOBS EHGISBEBIBG Analysis from registered flight data Advanced flight decks for the 80s cockpit A78-29906 design for transport aircraft Benefits of strapdown over gimbal INS systems for A78-28835 aircraft application HDB&H BE&CTIOBS A78-30253 Current problems of flight simulators for research Flight test results of the Strapdown hexad A78-29211 Inertial Reference Unit (SIBD). Volume 3: Psychological Assessment of Aircraft Noise Index Appendices A-G A78-32058 [NASA-TB-73221] S78-20098 HYBSID COHPBTEBS Sew technigues for low cost strapdown inertial Main characteristics of the ACT 1000-1100 digital systems computer for a hybrid computing system for N78-21073 jet engine simulation IBFOBHATIOH RETRIEVAL A78-29589 TESTPLT: Interactive computer procedure for Proposal and construction of a hybrid flight-sight wind-tunnel-data management, retrieval, simulator with large picture projection comparison, and plotting [DGLR PAPEB 77-087] A78-31945 [NASA-TB-78663] B78-201t9 BYDBiOIIC COHTBOL IBFOBHATIOB THEOBY Properties of hydraulic servomotor controlled by Systematic analysis of safety in aviation. II flapper valve or by edge valve turbojet A78-29671 engine system IB1ET FIOI A78-29587 Ejector-powered engine simulators for small-scale HYDBODYBABIC EQDATIOHS wind tunnel models of high performance aircraft Hydrodynamic effect on a contour produced by an [AIAA 78-826] A78-32388 ideal incompressible flow of constant vorticity Simulated flight effects on noise characteristics A78-28956 of a fan inlet with high throat Bach number BYDBODT8ABICS [NASA-TP-1199] H78-20132 Some specific hydrodynamic and aerodynamic Theoretical flow characteristics of inlets for problems of surface-effect ships with sidewalls tilting-nacelle VTOL aircraft A78-31126 [NASA-TP-1205] N78-21111 BYDBOFOILS IBPOT/ODTSOT BODTIBES Mixed ventilated foils design for immersed A three-dimensional potential-flow program with a hydrofoils geometry package for input data generation A78-31127 [SASA-CR-1115311] K78-210U7 IBSTBOHEBT ASPBOACH A method of calculating ILS approach surfaces A78-29207

A-20 SUBJECT IHDEX IABDIBG LOADS

IHSTBOBEHT L in DUG SYSTEBS JET EB6IBE FOELS A method of calculating ILS approach satfaces Properties of fuels used in the Czechoslovak J78-29207 aircraft industry Doppler BLS - The DK Eolation A78-29588 A78-2993U JET EBGIHES Development of systems and techniques for landing Ham characteristics of the ADT 1000-14100 digital an aircraft using onboard television computer for a hybrid computing system for [BASA-TP-1171] 178-201114 jet engine simulation Inertial smoothing and eitrapolation of ILS beams: A78-29589 Application to the Airhas A 300 B Thrust computing system applications to increase S78-2107I4 engine life and provide fuel conservation IBfAKB SYSTBHS A78-31311 A brief examination of the flow external to an Smoke abatement for DOD test cells F-111 intake at Bach 1.6 [AD-A050223] B78-20148 [ABL/BE-HOTE-357] N78-2105H JET EXBAOST IBTEGBAL EQUATIONS The influence of jets of cooling air exhausted Variational principles for the transonic airfoil from the trailing edges of a supercritical problem turbine cascade on the aerodynamic data S78-30891 B78-211148 ISTEEFEBEBCE DBAS JET FLABS Bodel support system interference on zero-lift On the calculation of the incompressible flow past drag at transonic speeds an aerofoil with a jet flap [AIAA 78-809] A78-32363 A78-31838 I brief examination of the flow external to an The feasibility of the jet-flap rotor as a lift F-111 intake at Mach 1.6 generator for vertical takeoff and landing [ABL/BE-HOTE-357] S78-21051 aircraft IHTBBHATIONAL LAS [AD-A05021<4] B78-20125 Critical considerations on the legal development JET FLOW of personal liability with attention to air On the calculation of the incompressible flow past transportation an aerofoil with a jet flap A78-299D1 A78-31838 Flying over the exclusive economic zone Experimental investigation of effect of jet decay aircraft overflight regulations rate on jet-induced pressures on a flat plate A78-299I45 [NASA-CB-2979] B78-21096 IHTEBBOGiTIOR JET IHPIBGEBEBT Design of a collision avoidance system model with Onsteady loads due to propulsive lift statistical interrogation separation and configurations. Part C: Development of collision avoidance by nonsynchronous techniques experimental techniques for investigation of (SECANT) unsteady pressures behind a cold model jet N78-20107 [NASA-CB-156122] N78-20069 ISOTBEBHAI PROCESSES JET 8IXIBG FLOB Systematic studies of heat transfer and film Effect of turbulent jet mixing on the static lift cooling effectiveness performance of a power augmented ram wing N78-211H6 [AD-AOM9620] B78-21060 JET HOZZIES An engine nozzle vibration phenomenon encountered in B-1 flight tests JABBEBS A78-32129 The next generation ED system - ASPJ Airborne Self Protection Jammer A78-31700 K JET 4IBCBAPT KEBHEL FOFCTIOHS Hew trends and problem areas in automatic flight A lifting surface theory based on an unsteady control linearized transonic flow model A78-30252 [AIAA 78-501] A78-29820 Fuel efficiency - Where we are heading in the KEBOSERE design of future jet transports Aviation fuels - A supplier's perspective A78-31307 A78-31308 Effect of winglets on a first-generation jet transport wing. 3: Pressure and Sfanwise load distributions for a semispan model at Bach 0.30 in the Langley 8 ft transonic tonnel LJBOHATOBY EQOTPBEHT [NASA-TS-D-8B78] N78-20063 The Boeing Aerodynamic Labs data system Effect of winglets on a first-generation jet [AIAA 78-789] A78-32346 transport wing. 1: Longitudinal aerodynamic LABISAB BOOSDABT LAYEB characteristics of a semispan model at subsonic Wind tunnel model and measuring techniques for the speeds IB the Langley 8 ft transonic tunnel investigation of three-dimensional turbulent [NASA-TB-D-8U73] N78-20061 boundary layers Effect of winglets on a first-generation jet [AIAA 78-781] A78-323I40 transport wing. 2: Pressure and spanwise load LABDUG AIDS distributions for a semispan model at high Landing systems - The Bavy viewpoint subsonic speeds in the Langley 8 ft A78-30097 transonic tunnel Precise enroute navigation based on ground-derived [NASA-TS-D-8H714] N78-20065 techniques Effect of winglets on a first-generation jet B78-21078 transport wing. 5: Stability characteristics Definition of tire properties required for landing of a full-span wing with a generalized fuselage system analysis at high subsonic speeds [BASA-CB-156171] N78-21326 [BASf-TP-1163] 878-20081 LEHEIBG GEAB Factors affecting the retirement of commercial Analytical and experimental fatigue program for transport jet aircraft the Kfir main and nose landing gears [HASA-CB-152115] H78-21092 A78-30259 JET AIBCBAFT BOISE Summary of NASA landing gear research The energy costs of some noise abatement procedures [HASA-TH-78679] N78-20050 A78-31313 LABDIBG LOADS Concorde noise-induced building vibrations, John Ground distance covered during airborne horizontal F. Kennedy International Airport deceleration of an airplane [BASA-TB-78676] S78-20919 [NASA-TP-1157] N78-20115

A-21 LANDING SPEED SUBJECT INDEX

LANDING SPEED Simulator evaluation of a flight-path-angle Ground distance covered during airborne horizontal control system for a transport airplane with deceleration of an airplane direct lift control [HASA-TP-1157] 1178-20115 [HASA-TP-1116] B78-20139 LASER ANBHOBBTEBS Unsteady, surface pressure and near-wave hotwire Investigation of the flow in a plane diffuser by measurements of a circulation control airfoil Beans of a laser Doppler anemometer [AD-A050025] N78-21061 478-28969 LIFT iDGBEBTATIOl IASEB APPlICiTIOBS Analysis of empirically determined aerodynamic and laser and optical methods of monitoring in ram coefficients for a power-augmented-ram aircraft construction Russian book wing-in-ground effect 678-30123 [AD-A019636] B78-20087 LASEB DOPPLBB VELOCIHETEBS Effect of turbulent }et mixing on the static lift Correlation of laser velocimeter measurements over performance of a power augmented ram wing a wing with results of tiio prediction techniques [AD-A0119620] N78-21060 in the langley V/STOI tunnel LIFT DEVICES [NASA-TP-1168] S78-21410 Transonic flows past a lift profile LASEBS A78-28961 Runway roughness evaluation laser profilometer Effect of high lift flap systems on the conceptual implementation study design of a 1985 short-haul commercial STOL tilt [AD-AOI19IIHO] N78-21165 rotor transport LATEBAL COHTBOL [BASA-TH-78I|7<(] N78-21094 Wind-tunnel investigation at Hach numbers from LIFT DBAG BATIO 1.90 to 2.86 of a canard-controlled missile with Optimum tail plane design for artificially ram-air-uet spoiler roll control in the stabilized aircraft langley Dnitary Plan Bind Tunnel A78-2933I* rNASA-TP-112iO 1178-20079 LIFT FANS LEADING EDGE SLATS Dynamic response of lift fans subject to varying Effect of leading-edge contour and vertical-tail backpressure for Surface Effect Ships configuration on the low-speed stability [AIAJ PAPEB 78-756] A78-32176 characteristics of a supersonic transport model LIFTING BODIES having a highly-swept arrow wing A lifting surface theory based on an unsteady CHASA-TB-78683] 1178-21051 linearized transonic flow model LEADING EDGES [AIAA 78-501] A78-29820 Normal force of a flat triangular wing in a LIFTING BOTOBS supersonic flow Low-speed test limit of V/STOL model located A78-29720 vertically off-center LEAST SQUARES BETHOD A78-296Q2 Integrated Doppler/TACAN navigation through LIGHT AIBCBAFT conformity with the least squares method - Investigation of interior noise in a twin-engine Analysis from registered flight data light aircraft A78-29906 A78-296U1 LEGAL LIABILITY. A study of lew-cost reliable actuators for light Critical considerations on the legal development aircraft. Part i: Chapters 1-8 of personal liability with attention to air [NASA-CB-156112] 1178-20110 transportation A study of low-cost reliable actuators for light A78-299U« aircraft. Part B: Appendices LIFE (DOBABILITI) [HASA-CB-156113] H78-20111 Effect of noise on life of aircraft structure and LIGHT ALLOYS design of parts resistant to acoustic loads Basic fatigue curves of aircraft structures A78-30352 A78-30356 Trends of future turbine life prediction: Time LIBITEB CIBCDITS phase automated analysis and test verification Fuel pressure increase limiter N78-211U3 [AD-AOU9393] N78-21117 LIFE CYCLE COSTS LINEAB FILTEBS Effect of reliability programs on life cycle cost Optimization of linear stabilization systems of - A case history of TACAN test set flight vehicles on the basis of orthogonal filters A78-29178 A78-32270 The AS/ABC-161 radio - Life-cycle-cost savings LINEAB SYSTEMS UHF communication equipment reliability and Sensitivity reduction in aircraft control systems maintainability improvement A78-3103U &78-29H79 LOADS (FOBCES) Life-cycle analysis of aircraft turbine engines Limitations of the UTTAS helicopter in performing CAD-A0503U9] H78-20135 terrain flying with external loads Fiber Optics Cost Analysis Program (JOCAP) [AD-A017568] N78-20121 [AD-AOU9859] 1178-21105 Analysis and synthesis of operational loads LIFT aircraft structures Lifting force of a plane H-polarized [ISD-193] F78-20551 electromagnetic wave Bearingless tall rotor loads and stability A78-32296 [AD-AOU9579] H78-21098 A constant aerodynamic parameter testing technique LOGIC CIBCOITS with automatic wind tunnel control A reliable modular automatic system adapted to [AIAA 78-781 ] A78-323U2 avionics controls: Design through successive Unsteady loads due to propulsive lift refinements - Production French book configurations. Part A: Investigation of A78-30021 scaling laws LONGITUDINAL CONTBOL [NASA-CB-156120] H78-20067 Analytical design of an automaton for the Unsteady loads due to propulsive lift longitudinal control of an aircraft configurations. Part B: Pressnre and velocity A78-32262 measurements in a three dimensional wall jet Results from flight and simulator studies of a [HASA-CB-156121] N78-20068 Hach 3 cruise longitudinal autopilot Unsteady loads due to propulsive lift [HASA-TP-1180] F78-21160 configurations. Part C: Development of LOB ASPECT BATIO IINGS experimental techniques for investigation of Three-dimensional flow of hypersonic gas past a unsteady pressures behind a cold model ]et thin airfoil [SASA-CP-156122] R78-20069 A78-30002 An improved version of the NASA-Lockheed multielement airfoil analysis computer program [NASA-CB-1U5323] 1178-20077

A-22 SUBJECT IHDEI BISSIIE DBSIGI

LOW SPEED BIRD TOHHEXS Bonvay roughness characterization by DOS approach Determination of high attitude wall corrections in Dynamic Data System a low speed wind tuncel A78-30679 [AIAA 78-810] A78-3236P Nitric oxide formation in gas turbine engines: A Applications of wind tunnels to investigations of theoretical and experimental study wind-engineering problems [NASA-CB-2977] S78-21116 f&IAA 78-812] A78-32366 BEASOBIHG IHSTBOBEHTS Optimum design of wind tunnel contractions Measuring techniques in high teaperature turbines [AIAA 78-819] A78-32373 H78-21151 10BBICATIHG OILS BECBAHICiL FBOPEBTIES Steady-state unbalance response of a three-disk Preliminary design of composite wings for flexible rotor on flexible, damped supports buckling, strength and displacement constraints A78-29326 [AIAA 78-166] A78-29777 Effectiveness of the r«al time ferrograph and Definition of tire properties required for landing other oil monitors as related to oil filtration system analysis [AD-A049331] N78-2013U [HASA-CB-156171] B78-21326 BETAl FATIGUE Some lessons learned from aircraft accidents - The M engineering aspects EACH BUBBEB A78-29936 Analysis and comparison of several methods for BETEOBOtOGICAL IBSTBDREHTS computing aerodynamic compressibility and Ose of US LI1600A as a short-range altimeter interference effects up to critical Bach numbers A78-28880 [AD-A050267] N78-20083 BICBOPBOCESSOHS Simulated flight effects on noise characteristics Stand-alone development system using a KIH-1 of a fan inlet with bigh throat Mach number microcomputer module [SASA-TP-1199] N78-20132 [NASA-CB-156067] N78-20100 Results from flight and Emulator studies of a flICBOWAVB L6HDIB6 STSTEBS Hach 3 cruise longitudinal autopilot (licrowave landing svstems time reference [NASA-TP-1180] N78-21160 scanning beam used to determine aircraft approach BAIHTAINABILITT A78-29221 The AN/ABC-16II radio - life-cycle-cost savings Doppler HLS - The OK solution DBF communication equipment reliability and A78-2993« maintainability improvement Whither HLS Microwave Landing System civil and A78-291479 military applications BAIHTEH4HCB A78-30096 Development of a pavement maintenance system. Interference analysis between TBSB microwave Volume 1: Airfield pavement condition rating landing system and adjacent C-band radars [AD-A04888

A-23 SUBJECT INDEX

HOHITOBS Heasuring noise in aircraft cabins Effectiveness of the real time ferrograph and A78-30353 other oil monitors as related to oil filtration Comparison of measured and calculated helicopter [AD-A019331] N78-20131 rotor impulsive noise wind tunnel test data BOHTABA and prediction analysis techniques ftn evaluation of the bird/aircraft strike hazard, [NASA-TB-78173] N78-20917 Halmstrom AFB, Montana A method for calculating externally blown flap noise [AD-A019637] H78-20095 [NASA-CH-2951] N78-20920 HOTIOH SIBULATOBS BOISE POILUTIOB Current problems of flight simulators for research Psychological Assessment of Aircraft Noise Index 878-29211 A78-32058 BULTISPECTBAL BABD SCABRBBS NOISE BEDOCTIOH Geometric restitution of single coverage aircraft Aircraft noise and its sources multispectral scanner data J78-30351 A78-2985"! Hethods of reducing aircraft noise Investigation of a high speed data handling system A78-30355 for use with multispectral aircraft scanners The problem of the acoustic properties, of the [NASA-TH-78689] N78-20181 propeller and Q-fan type blower with regard to exterior and interior noise in transport aircraft A78-30358 N The energy costs of some noise abatement procedures NACELLES A78-31313 Theoretical flow characteristics of inlets for A new technigue for reducing test section noise in tilting-nacelle 7TOL aircraft supersonic wind tunnels [NASA-TE-1205] 878-21111 [AIAA 78-817] A78-32371 RASA PEOGEABS Dse of leaning vanes in a two stage fan The NASA Aircraft Energy Efficiency Program [NASA-CB-152131] N78-21115 A78-31302 Airport and aircraft noise reduction Summary of NASA landing gear research [GPO-91-591 ] N78-21891 rNASA-TM-78679] N78-20050 BOISE TOLEBABCB A critical evaluation of the predictions of the Aircraft and helicopter cockpit noise NASA-Lockheed multielement airfoil computer A78-29673 program Psychological Assessment of Aircraft Noise Index CUASA-CE-115322] N78-20076 A78-32058 BAVIGATIOR BONEQOTLIBBIUB FLOS Navigation, guidance and control for high Boundary-layer interaction with a noneguilibriura performance military aircraft two-phase stream on a surface being burned out 178-21090 in an axisymmetric Laval nozzle Area navigation systems and procedures A78-28610 N78-21091 NOBLINEAB FILTEBS NAVIGATIOB AIDS Study of the use of a nonlinear, rate-limited Choice of optimal ellipsoid-surface projection filter on pilot control signals onto a sphere in solving problems of air [NASA-TP-1117] N78-20112 navigation BOBLIBE1B SYSTEBS A78-28523 Observability criteria for nonlinear dynamic New techniques for low cost strapdown inertial systems subjected to multiparameter measurements systems noting air navigation applicability N78-21073 A78-29089 Precise enroute navigation based on ground-derived A perturbation method for predicting amplitudes of technigues nonlinear wheel shimmy N78-21078 N78-21161 NAVY BOBBERTOSIAB FLO! OS Navy examining a wide range of V/STOL concepts Basic problem of control of the motion of a A78-29175 non-Newtonian fluid in a gap roll forming of Landing systems - The Navy viewpoint aircraft plastics A78-30097 A78-32257 NEODYHIOH LASEBS ROBUBIFOBB FLOR Space optical communications with the Nd:YAG laser Airfoil profile in a nonuniform flow A78-30886 [NASA-TB-75272] N78-21018 NICKEL CADBIUB BATTEBIES NOZZLE DBSIGB Nickel/cadmium aircraft batteries: Battery alarm A new technigue for reducing test section noise in unit supersonic wind tunnels CAD-A039521] N78-20631 [AIAA 78-817] A78-32371 Nickel/cadmium aircraft batteries: Eapid BOZZLE FLOS electrolyte exchange technigue Boundary-layer interaction with a noneguilibrium [AD-A039335] N78-20632 two-phase stream on a surface being burned out Nickel/cadmium aircraft batteries: Single sensor in an axisymmetric Laval nozzle temperature monitoring A78-28610 [AD-A037722] N78-20635 NOCLEAB EIPIOSIONS Nickel/cadmium aircraft batteries: Hultichannel Correlation study of the OH-18 helicopter blast gassing-rate meter test results from the DICE-THBOH event [AD-A039735] N78-20636 [AD-A050U63] N78-20122 HITBIC OXIDE NDCLEATIOB Nitric oxide formation in gas turbine engines: A Onset of condensation effects with a NACA 0012-61 theoretical and experimental study airfoil tested in the Langley 0.3-meter [NASA-CF-2977] N78-21116 cryogenic tunnel RITBOGEB [NASA-TB-78666] N78-20070 Design, fabrication, and testing of a full-scale breadboard in nitrogen generator for fuel tank inerting application fAD-A0191591 N78-21097 OFFSHOBE PLATFOBBS BOISE GEREBATOBS Looking offshore at the airport future Aircraft noise and its sources A78-30215 A78-30351 OGIVES BOISE SEASUBEBBBT Hypersonic heat transfer test program in the VKI Investigation of interior noise in a twin-engine longshot facility ogive body configuration light aircraft [AD-A050295] N78-20086 A78-29611

A-21 SUBJECT IgDEI PODS (EITEBBAl STOBES)

OPEHIHGS PASSEBGEBS Cotout reinforcement of stiffened cylindrical shells Tandem-queue algorithm for airport user flows [AIAA 78-512] 478-29811 A78-30677 OPTICAL COHnOHICATIOB PAVEBESTS Space optical commanications with the Nd:YAG laser Development of a pavement maintenance system. A78-30886 Volume 1: Airfield pavement condition rating OPTICAL HEJSOBIBG IBSTBOBEBTS [AD-AOU8881] B78-201U7 Laser and optical nethods of monitoring in Development of A pavement maintenance management aircraft construction Bussian book system. Volune 2: Airfield pavement distress J78-30123 identification manual OPTICAL SCASBEBS [AD-A019029] H78-21170 Microwave landing systems time reference PATLOADS scanning bean nsed to determine aircraft approach A-1F Blue Angel flight usage data, 1976 478-29221 [AD-A050161] B78-21100 OPTIMAL COBTBOL PEBFOBBAHCE Sensitivity redaction in aircraft control systems A critical examination of expansion tunnel 478-31031 performance Optimal ccntrol of the longitudinal moticn of a [AIAA 78-768] A78-32329 helicopter on the basis of an operational PEBFOBHABCE PBEDICtlOB algorithm Bode of operation and characteristics of Darriens 478-32272 rotors OPTIBIZATIOB A78-28560 Preliminary design of composite wings for The effect of hob fairings on wind turbine rotor buckling, strength and displacement constraints performance [AIAA 78-H66] 578-29777 478-30039 Semispan wind tunnel test of a computer-controlled A critical evaluation of the predictions of the self-optimizing flenble technology wing NASA-Lockheed multielement airfoil computer [AIAA 78-786] 478-32341 program Optimum design of wind tunnel contractions [NASA-CB-11(5322] B78-20076 [AIAA 78-819] 478-32373 A review of methodologies and concepts to measure System optimization by periodic control and evaluate aircraft survivability/vulnerability [AD-A019522] N78-21162 [AD-A050152] B78-21099 OBBITAL POSITIOB ESTIHATIOB High temperature problems in gas turbine engines Differential altimetry for satellite orbit [AGABD-CP-229] K78-21118 determination PEBTOBBATIOB THEOBT A78-31915 A perturbation method for predicting amplitudes of OBTHOGOSAL FtJBCTIOBS nonlinear wheel shimmy Optimization of linear stabilization systems of N78-21161 flight vehicles en the basis of orthogonal filters PEASE SHIFT KETIBG A78-37270 Flight tests of digital data transmission nSK OSCILliTIBG PLOW - a quadrature PSK system Prediction of the unsteady airloads on A78-31050 harmonically oscillating spheroids based on an PSOTOGBABHETBY analytical solution of the governing wave equation Geometric restitution of single coverage aircraft A78-29338 multispectral scanner data An experimental investigation of oscillating flows 478-29851 over an airfoil rotary wings PILOT PEBFOBHABCE N78-20058 Current problems of flight simulators for research 478-29211 Aircraft and helicopter cockpit noise 478-29673 PABACBDTE DBSCBBT Systematic analysis of safety in aviation. II The aerodynamic behaviour of fully inflated A78-29671 parachutes Digital computer program maneuver pilot A78-29215 A78-31916 The effect of a parachute on the motion of an Study of the use of a nonlinear, rate-limited axisymmetric object dropped from an aircraft filter on pilot control signals A78-31811 [NASA-TP-11U7] N78-20112 PABACBOTES Pilot-model analysis and simulation study of A computer-controlled video instrumentation effect of control task desired control response technigue for wind tunnel testing of full-scale [NASA-TP-1110] N78-20113 lifting parachutes PILOT TBAIBIRG [AIA4 78-785] A78-32313 The Dual-Flight-Simulator as an aid for a PARALLEL FLOR government mission specialist Aerodynamic fluid-fiber interactions [DGLB PAPEB 77-079] A78-31919 [NT-77'CN-1] N78-20060 Expansion of flight simulator capability for study PABTICLE EHISSIOB and solution of aircraft directional control Nickel/cadmium aircraft batteries: Multichannel problems on runways gassing-rate meter [NASA-CB-2970] B78-20118 [AD-A039735] N78-20636 PITOT TUBES PASSBBGBB AIBCBAFT A critical examination of expansion tunnel Weight design and the efficiency of passenger performance aircraft. Volume 2 - Calculation of the center [AIAl 78-768] A7B-32329 of gravity and moments of inertia of aircraft. PLABE SAVES Weight analysis Russian book Lifting force of a plane H-polarized A78-30175 electromagnetic wave Improved energy efficiency for small CTOL A78-32296 transport aircraft PLASTICS A78-31305 Basic problem of control of the motion of a Fnel efficiency - Where we are heading in the non-Newtonian fluid in a gap roll forming of design of future jet transports aircraft plastics 478-31307 478-32257 STOL system fuel savings - Ground and air PODS (EXTERNAL STORES) A78-31312 A test using simulated mission profile environments Fire resistivity and toxicity studies of candidate Airborne instrumentation Subsystem pod aircraft passenger seat materials reliability [NAS4-TB-78168] N78-21211 A78-32126

A-25 POLABIZED ElECTBORAGBETIC BADIATIOB SOBJECt HDEX

POLiBIZED ELECTBOHAGBETIC BADIATIOH Transonic wind tunnel tests on two-dimensional Lifting force of a plane H-polanzed aerofoil sections. Determination of pressure electromagnetic wave distribution and drag for an aerofoil with a 478-32296 modified NACA 65 snb2-215 section in FFA wind POBOOS iALLS tunnel S5, part 2 A parametric experimental study of the [FFi-TN-AO-725] B78-21062 interference effects and the boundary-condition PBESSDSE SEHSOBS coefficient of slotted wind-tunnel walls Ose of US LX1600A as a short-range altimeter [AIAA 78-805] 478-32359 A78-28880 An empirical correction for wind tunnel wall 4 rotor-mounted digital instrumentation system for blockage in two-dimensional transonic flow helicopter blade flight research measurements [AIAA 78-806] A78-32360 [NASA-TP-11H6] N78-20128 POSITIOB (LOCATION) PBODDCT DEVBIOPHEHT Cockpit displayed traffic information study, part 2 Ose of and experience with simulation in the [NASA-CR-156115] N78-20102 development of the VFH 611 and the VAK 191 A multi-sensor implementation for navigation, [DG1E PAPEB 77-083] A78-319U2 position location, position update, PBODOCTIOS BS6ISBEBIHG reconnaissance, and weapon delivery: Laser and optical methods of monitoring in AN/4BS-101 (V) aircraft construction Bussian book N78-21082 A78-30123 POTEHTIAI THEOBY PBOFILOHETEBS Variational principles for the transonic airfoil Bunway roughness evaluation laser profilometer problem implementation study 478-30891 [AD-A019U40] K78-21165 POBEB EFFICIEHCY EBOPELLEB FADS Effect of boundary layer suction through slits on Prospects for energy conserving STOL transports the efficiency of turbcmachine outlet diffusors using prop-fans 478-30572 ~ A78-31303 POWEBED LIFT AIRCBAFT Fuel saving potential of Bach 0.8 twin engine Some aspects of powerplant airframe integration prop-fan transports affecting fuel conservation A78-31306 178-31301 PBOPOISIOB SISTER CONFIGURATIONS PBEDICTIOH AHALYSIS TECHBIQDES Onsteady loads due to propulsive lift Theoretical analysis of aerodynamic configurations. Part D: The development of an characteristics of two helicopter rotor airfoils experimental facility for the investigation of [NASA-TH-78680] N78-20075 scaling effects on propulsive lift configurations Simplified sonic-boom prediction using [N4S4-CB-156123] S78-20070 aerodynamic configuration charts and calculators PHOPOLSIOH SISTER PBBFOBHAHCE or slide rules Evolution of the aircraft gas turbine engine [N4S4-TP-1122] N78-20078 478-30257 Comparison of measured and calculated helicopter Aircraft fuel economy - The propulsion system rotor impulsive noise wind tunnel test data contribution and prediction analysis techniques 478-31309 [NASA-TH-78173] N78-20917 4irflow and thrust calibration of an F100 engine, Correlation of laser velocimeter measurements over S/F P680059, at selected flight conditions a wing with results cf two prediction techniques [NASA-TP-1069] S78-21112 in the Langley V/STOL tunnel PROPULSIVE EFFICIEHCY [N4S4-TP-1168] N78-21110 Evolution of the aircraft qas turbine engine PBESSOBE DISTBIBOTIOH 478-30257 Computation of the pressure on the surface of a Supersonic transports drag minimization fuselage with a wing in an ideal fluid techniques 478-29712 478-31152 Effect of winglets on a first-generation jet The aircraft ducted fan transport wing. 3: Pressure and spanwise load 478-31153 distributions for a semispan model at Hach 0.30 Energy conserving aircraft from the engine viewpoint in the Langley 8 ft transonic tunnel 478-31310 [NASA-TN-D-8178] N78-20063 PBOTECTIOH Effect of winglets on a first-generation jet Protection of cooled blades of complex internal transport wing. 2: Pressure and spanwise load structure distributions for a semispan model at high N78-21111 subsonic speeds in the Langley 8 ft PBOTECTIVB COATINGS transonic tunnel Cobalt-base alloys for hot corrosion protective [NASi-TN-D-81711] H78-20065 coatings Experimental investigation of effect of jet decay N78-21112 rate on jet-induced pressures on a flat plate PSYCHOLOGICAL F4CTOBS [HASA-CB-2979] N78-21096 Psychological Assessment of Aircraft Noise Index Problems concerning high temperatures in small A78-32058 turbomachines POBLIC HEALTB 578-21121 Air quality impact of aircraft at ten O.S. Air PBESSOBE EFFECTS Force bases Dynamic response of lift fans subject tc varying 478-32222 backpressure for Surface Effect Ships POISE DOPP1EB BAOAB [AIAA PAPEB 78-756] 478-32176 Radio interference in helicopter-borne pulse PBESSOBE GBADIBHTS Doppler radars Unsteady loads due to propulsive lift 478-31038 configurations. Part C: Development of experimental techniques for investigation of unsteady pressures behind a cold model jet Q [NASA-CB-156122] N78-20069 QOALIT! COHTBOt PBESSDBE BEASOBBREHTS Laser and optical methods of monitoring in The induction driven tunnel T2 at ONEBA-CEET - aircraft construction Bussian book Flow qualities, testing techniques and examples 478-30123 of results Quality assurance in the fabrication of products [4IAA 78-767] A78-32328 in aviation technology 478-32267 QDEDEING THEOBY Tandem-queue algorithm for airport user flows 478-30677

A-26 SUBJECT IBDEI BOLL

QOIBT ZH6IHB PBOGBiH RELIABILITY E86IBEEBIBG The problem of the acoustic properties of the The AN/ABC-160 radio - Life-cycle-cost savings propeller and Q-fan type blower with regard to DBF communication equipment reliability and exterior and interior noise in transport aircraft maintainability improvement 478-30358 A78-29I179 Determining the reliability reguirements of aircraft engine control systems during design stage RADAR ECHOES A78-29590 On the possibility of classifying radar targets BEBOTE SEBSOBS with a coherently neasured echo signal A spectroradiometer for airborne remote sensing German book for geological, vegetation and hydrological A78-32308 mapping BADAB EQOIPBBHT A78-32396 Fire power fighter aircraft target acquisition BEBOTELT PILOTED VEHICLES and tracking radar Remotely piloted aircraft in the civil environment A78-31Q25 A78-30506 BADAB TBICKIie The problem of choosing design parameters for Improved aircraft tracking using maneaver nnpiloted flight-vehicles control configured statistics enronte and in the terminal area optimization N78-21087 A78-32258 BADAB TBASSBISSIOH Development of systems and techniques for landing Badio interference in helicopter-borne pnlse an aircraft using onboard television Ooppler radars [HASA-TP-1171] N78-2011U *78-31038 RESCOE OPBBBTIOHS BADIO BEACOHS Special study: Emergency locator transmitters, an Special study: Emergency locator transmitters, an overview overview [NTSB-AAS-78-1] F78-21063 [NTSB-AAS-78-1] H78-21063 BESEABCH AIRCRAFT BAOIO EQOTPBEHT Subsonic longitudinal and lateral-directional The AN/ARC-16U radio - life-cycle-cost savings static aerodynamic characteristics of a general DBF conmanication equipment reliability and research fighter configuration employing a jet maintainability improvement sheet vortex generator A78-29179 [NASA-TB-7IIOU9] B78-20071 BADIO FBEQUEHCY IBTEBFEBEBCB BESEABCH AND DEVELOPBEHT Badio interference in helicopter-borne pulse Flight simulation - A vital and expanding Doppler radars technology in aircraft development A78-31038 [AIAA PAPEB 78-337] A78-29295 BADIO TBABSBISSIOS BESEABCH FACILITIES AH-1S high-sarvivable transmission system Unsteady loads due to propulsive lift [AD-AOII7558] N78-20123 configurations. Part D: The development of an RADIOHETBRS experimental facility for the investigation of APL radiometer wind tunnel test program with scaling effects on propulsive lift configurations simulated aircraft radone [NASA-CR-156123] N78-20070 [BSR-U230] H78-21U02 BESOHiBCE TESTIBG RADOHES Automatic sustainment of resonance conditions in APL radiometer wind tunnel test program with the multipoint excitation of flight-vehicle simulated aircraft radome vibrations [BSR-H230] H78-21102 A78-32268 BABJET ENGINES BETIBBHEHt Rectangular capture area tc circular combustor Factors affecting the retirement of commercial scramjet engine transport jet aircraft fNASA-TB-78657] N78-21107 [NASA-CR-152115] N78-21092 BAHDOB 7IBBATIOH BEVEBSED FLOS Practical experience in vibration testing external Evaluation of a ceramic combustion chamber for a avionics systems small gas turbine engine A78-3213H H78-21115 BABEFIED GAS DIBASICS BETBOLDS BOBBER An analytic study of free nolecule flow fields at An intermittent high Reynolds number wind tunnel the front and back edges of a plate [AIAA 78-766] A78-32327 A78-28972 The induction driven tunnel T2 at ONERA-CEBT - BECOBNAISSANCE Flow qualities, testing techniques and examples A multi-sensor implementation for navigation, of results position location, position update, [AIAA 78-767] A78-32328 reconnaissance, and weapon delivery: The shock tube as a device for testing transonic WABN-101 (V) airfoils at high Reynolds numbers N78-21082 [AIAA 78-769] A78-32330 BEIHFOBCED SHELLS BIGID BOTOBS Cutout reinforcement of stiffened cylindrical shells A theoretical technique for analy2ing aeroelastic [AIAA 78-512] A78-29811 stability of bearingless rotors BEIHFOBCEBBHT |SIBDCTOBES) [AIAA 78-503] A78-29805 Cutout reinforcement of stiffened cylindrical shells BOCKET FLI6BT [AIAA 78-512] A78-29811 Optimization of the design parameters of finned RELIABILITY AHALTSIS pilotless flight vehicles Effect of reliability programs on life cycle cost A78-32269 - A case history of TACAN test set Optimization of linear stabilization systems of A78-29478 flight vehicles on the basis of orthogonal filters A fail-safe analysis of a spanwise wing-panel splice A78-32270 [AIAA 78-U87] A78-2979I1 BOLL Joint ASD/AFRAL Combined Environment Reliability Further experimental evaluation of the Test /CEBT/ Evaluation Program electrostatic roll sensor at Hach 2.3 and 3.5 A78-32118 [AIAi 78-802] A78-32357 A test using simulated mission profile environments Subsonic roll damping of a model with swept-back Airborne Instrumentation Subsystem pod and swept-forward wings reliability [HASA-TH-78677] N78-20061 178-32126 Sellable dnal-rednndant sensor failure detection and identification for the NASA F-8 DFEB aircraft [NASA-CR-29<|(|] 078-20111

A-27 BOLL FOBBING SUBJECT IRDEX

BOLL FOBBING BOTOB BLADES (TOBBOSACHIHBBY) Basic problem cf control of the notion of a Mode of operation and characteristics of Darrieus non-Newtonian fluid in a gap roll forming of rotors aircraft plastics A78-28560 A78-32257 A note on multicyclic control by swashplate ROLLING oscillation Boiling-element fatigue life of *ISI H-50 and [NASA-TH-78175] N78-21159 18-1-1 balls BOTORS [NASA-TP-1202] N78-21173 Steady-state unbalance response of a three-disk BOTABY STABILITY flexible rotor on flexible, damped supports Dynamic stability of a two blade rotor A78-29326 A78-32037 The feasibility of the jet-flap rotor as a lift New rotation-balance apparatus for measuring generator for vertical takeoff and landing airplane spin aerodynamics in the wind tunnel aircraft CAIAA 78-835] A78-32386 [AD-A05021I4] N78-20125 BOTABY WING AIBCBAFT BONBAY CONDITIONS Fotorcraft linear simulation model. Volume 1: A method of calculating ILS approach surfaces Engineering documentation A78-29207 fNASA-CR-152079-VOL-1] N78-20136 Runway roughness characterization by DDS approach Rotoccraft linear simulation model. Volume 2: Dynamic Data System Computer implementation J78-30679 [NASA-CR-152079-VOL-2] N78-20137 Aircraft takeoff from dirt airstrips Rotorcraft linear simulation model. Volume 3: A78-32273 User's manual Summary of NASA landing gear research [NASA-CB-152079-VOL-3] N78-20138 [NASA-TH-78679] N78-20050 BOTABY RINGS HOKBAYS The helicopter as a control object Russian book Expansion of flight simulator capability for study A78-291I01 and solution of aircraft directional control Helicopters: Calculation of integral aerodynamic problems on runways performance and air-technical data Russian [NASA-CR-2970] N78-20118 book Development of a pavement maintenance system. A78-3012U Volume 1: Airfield pavement condition rating Dynamic stability of a two blade rotor [AD-AOQ888«] N78-20117 A78-32037 Runway roughness evaluation laser profilometer An experimental investigation of oscillating flows implementation study over an airfoil rotary wings [AD-A019imO] N78-21165 N78-20058 Development of a pavement maintenance management Theoretical analysis of aerodynamic system. Volume 2: Airfield pavement distress characteristics of two helicopter rotor airfoils identification manual [NASA-TH-78680] N78-20075 [AD-AOU9029] N78-21170 A simple method for estimating minimum autorotative descent rate of single rotor helicopters fNASA-TH-78l|52] N78-20113 S-N DIAGBASS A rotor-mounted digital instrumentation system for Basic fatigue curves of aircraft structures helicopter blade flight research measurements A78-30356 [NASA-TP-11II6] N78-20128 SAFETY DEVICES Comparison of measured and calculated helicopter Some test results concerning visibility of rotor impulsive noise wind tunnel test data obstacle and hazard beacons and prediction analysis techniques A78-29907 [NASA-TM-78U73] N78-20917 SAFETY RANAG2HENT Acoustical effects of blade tip shape changes on a How to make an airport unattractive to birds full scale helicopter rotor in a wind tunnel A78-29209 fNASA-CR-152082] N78-20918 SATELLITE ANTENNAS ROTATING CYLINDEBS Special problems in the determination of the Basic problem of control of the motion of a radiation characteristics of antennas on non-Newtonian flnid in a gap roll forming of aircraft and satellites with the aid of aircraft plastics geometric diffraction theory A78-32257 A78-31582 BOTATING DISKS SATELLITE OBBITS Steady-state unbalance response of a three-disk Differential altimetry for satellite orbit flexible rotor on flexible, damped supports determination A78-29326 A78-31915 Calculation of temperature distribution in disks SATELLITE TBAHSHISSIOB and cooling flow in a transient state Space optical communications with the Nd:YAG laser N78-21157 A78-30886 BOTOB AERODYNAMICS SATBLLITB-BOBNB INSTBOHENTS Mode of operation and characteristics of Darriens Differential altimetry for satellite orbit rotors determination A78-28560 A78-31915 Low-speed test limit of 7/STO1 model located SCALE EFFECT vertically off-center Unsteady loads due to propulsive lift A78-29612 configurations. Part D: The development of an Helicopters: Calculation of integral aerodynamic experimental facility for the investigation of performance and air-technical data Russian scaling effects on propulsive lift configurations book [NASA-CR-156123] N78-20070 A78-3012II SCALE 80DSLS Rotorcraft linear simulation model. Volume 1: Design and snbscale tests of a diffuser system for Engineering documentation a nach 1 scramjet test facility [NASA-CR-152079-VOL-1] N78-20136 [AIAA 78-771] A78-32332 Rotorcraft linear simulation model. Volume 2: Subsonic longitudinal and lateral-directional Computer llplementation static aerodynamic characteristics for a CNASA-CH-152079-VOL-2] H78-20137 close-coupled wing-canard model in both swept Rotorcraft linear simulation model. Volume 3: back and swept forward configurations User's manual [NASA-TH-7q092] N78-210H9 [NASA-CR-152079-VOL-3] N78-20138

A-28 SUBJECT IBDBI SOVEBEIGHTT

Effect of leading-edge contour and vertical-tail Improved energy efficiency for snail CTOL configuration on the low-speed stability transport aircraft characteristics of a supersonic transport model A78-31305 having a highly-swept arrow wing Effect of high lift flap systems on the conceptual [HASA-TH-786831 F78-21051 design of a 1985 short-haul commercial STOL tilt SCHEDDIIHG rotor transport Factors influencing schedule reliability in [FASA-TB-7847H] B78-2109U international operations SHOBT TAKEOFF AIBCBiFT A78-29213 Influence of structural components of a by-pass SEALS (STOPPEBS) engine on its flight characteristics STOL Gas path sealing in turbine engines aircraft [NASA-TH-73890] N78-21109 A78-29582 SEABCHIHG Handling gualities of aircraft in the presence of Special study: Emergency locator transmitters, an simulated turbulence overview A78-296«3 [NTSB-AAS-78-1] N78-21063 New trends and problem areas in automatic flight SEAS control Flying over the exclusive economic zone A78-30252 aircraft overflight regulations Performance of the ARAVA aircraft with wing-tip A78-299II5 winglets SEATS A78-30256 Fire resistivity and toiicity studies of candidate Prospects for energy conserving STOL transports aircraft passenger seat tatenals using prop-fans [FASA-TB-78068] H78-212111 A78-31303 SELF OSCILliTIOH Some aspects of powerplant airframe integration Theory of bending-torsional self-oscillations of affecting fuel conservation an aircraft wing system A78-3130U A78-32264 STOL system fuel savings - Ground and air SEHISPAH HODELS A78-31312 Effect of winglets on a first-generation jet Effect of high lift flap systems on the conceptual transport wing. 3: Pressure and spanwise load design of a 1985 short-haul commercial STOL tilt distributions for a semispan model at Bach 0.30 rotor transport in the Langley 8 ft transonic tunnel [NASA-TB-78tt7U] N78-21091 [SASA-TN-D-8178] N78-20063 SIGBAL HEASUBEHEHT Effect of winglets on a first-generation jet On the possibility of classifying radar targets transport wing. 1: longitudinal aerodynamic with a coherently measured echo signal characteristics of a semispan model at subsonic German book speeds in the Langley 8 ft transonic tunnel A78-32308 [HASA-TN-D-8473] N78-2006U SIGHJTDBE AHALTSIS Effect of winglets on a first-generation jet On the possibility of classifying radar targets transport wing. 2: Pressure and spanwise load with a coherently measured echo signal distributions for a senispan model at high German book subsonic speeds in the Langley 8 ft A78-32308 transonic tunnel SIHULATIOH [NASA-TN-D-8174 ] N78-20065 Aircraft cargo compartment fire test simulation SENSOBS program Reliable dual-redundant sensor failure detection [NASA-CR-151951 ] H78-21223 and identification for the NASA F-8 DFBW aircraft SKIN (STBUCTOBAL HEHBEB) [HASA-CR-29U1] N78-20141 Experimental and finite element investigation of SERVICE IIFE the buckling characteristics of a beaded skin Analytical and experimental fatigue program for panel for a hypersonic aircraft the Kfir main and nose landing gears [HASA-CR-1UII863] N78-2053Q A78-30259 SLEBDER BODIES Project optimisation of military gas turbines with Drag formula for elongated aircraft noses respect to turbine life A78-29718 N78-21120 SLIBDEE 8INGS SEBVOCOHTB01 Preliminary design of composite wings for New aspects in the movement simulation of the buckling, strength and displacement constraints research flight simulator of DF7LR [AIAA 78-1166] A78-29777 [DGLR PAPER 77-0861 *7S-31950 SHALL PERTURBATION FLOI SEBVCBOTOES Stability of subsonic gasdynamic flows Use of a stepping motor for measuring fuel A78-28959 guantity in a digital system for contrcl of SHORE ABATEHBNT rotational speed Smoke abatement for DOD test cells A78-29586 [AD-A050223] N78-201U8 Properties of hydraulic servomotor controlled by SBOOTBING flapper valve or by edge valve turbojet Inertial smoothing and extrapolation of ILS beams: engine system Application to the Airbus A 300 B A78-29587 N78-2107U SHAFTS (HACHISE E1EBESTS) SOCIAL FiCTOBS Rolling-element fatigue life of AISI B-50 and More public consultation on airport plans 18-11-1 tails A78-29208 [BASA-TP-1202] H78-21473 SONIC BOOBS SHOCK TUBES Simplified sonic-boom prediction using The shock tube as a device for testing transonic aerodynamic configuration charts and calculators airfoils at high Reynolds numbers or slide rules [AIAA 78-769] A78-32330 [NASA-IP-1122] N78-20078 SHOCK RAVE PROFILES SODND PROPAGATION The shock tube as a device for testing transonic Acoustical effects of blade tip shape changes on a airfoils at high Reynolds numbers full scale helicopter rotor in a wind tunnel [AIAA 78-769] A78-32330 [NASA-CR-152082] N78-20918 SHOCK RAVES SOUND TRANSHISSION Normal force of a flat triangular wing in a On sound transmission into a heavily-damped cylinder supersonic flow aircraft noise in fuselage A78-29720 A78-31019 SHOUT BAD1 AIRCRAFT SOVEREIGNTY The division of air transport markets between Flying over the exclusive economic zone carriers - Local service operations aircraft overflight regulations A78-30697 A78-2998S

A-29 SPACE COHHONICATIOH SUBJECT IHDBI

SPACE CORHDNICATION Transonic static and dynamic stability Space optical communications with the Nd:YAG laser characteristics of a finned projectile 478-30886 configuration SPACECRAFT STBOCTDRES [NASA-TH-711058] N78-20072 Stress analysis of typical flaws in aerospace STATISTICAL ANALYSIS structural components using 3-D hybrid 'Chain pooling1 model selection as developed for displacement finite element method the statistical analysis of a rotor burst [AIAA 78-513] A78-29812 protection experiment SPABK IGNITION J78-29327 Lightweight, low compression aircraft diesel engine Geometric restitution of single coverage aircraft converting a spark ignition engine to the multispectral scanner data diesel cycle A78-29851 [NASA-CB-135300] N78-21471 The error function of analytical structural design SPECTBOBADIOHETBBS in aircraft component failure in static tests A spectroradiometer for airborne remote sensing A78-32123 for geological, vegetation and hydrological STATISTICAL DISTBIBOTIOSS mapping Design of a collision avoidance system model with A78-32396 statistical interrogation —*- separation and SPEED CONTBOL collision avoidance by nonsynchronous technigues Control of aircraft turbine engine acceleration (SECANT) A78-29583 N78-20107 Use of a stepping motor for measuring fuel STATOB BLADES guantity in a digital system for control of Two-dimensional cold-air cascade study of a rotational speed film-cooled turbine stator blade. 1: 478-29586 Comparison of experimental and analytical SPBEBES aerodynamic results for blade with 12 rows of Choice of optimal ellipsoid-surface projection 0.076-centimeter-(0.030-inch-) diameter holes onto a sphere in solving problems of air having streamwise ejection angles navigation [NASA-TP-1151] N78-20130 A78-28523 Use of leaning vanes in a two stage fan SPBEBOIDS [NASA-CB-15213U] N78-21115 Prediction of the unsteady airloads on The influence of jets of cooling air exhausted harmonically oscillating spheroids based on an from the trailing edges of a supercritical analytical solution of the governing wave equation turbine cascade on the aerodynamic data A78-29338 N78-21118 SPIN DYNARICS STOBAGE BATTBBIES Influence of spin rate on side force of an nickel/cadmium aircraft batteries: Battery alarm axisymmetnc body unit A78-30690 [AD-A039521] H78-20631 Going for a spin - Fighter style STRAPDORN INEBTIAL GUIDANCE A78-317U5 Benefits of strapdown over gimbal INS systems for New rotation-balance apparatus for measuring aircraft application airplane spin aerodynamics in the wind tunnel A78-30253 [AIAA 78-835] A78-32386 Flight test results of the Strapdown hexad SPLASHING Inertial Reference Unit (SIBD). Volume 3: A note on multicyclic control by swashplate Appendices A-G oscillation [NASA-TH-73221] N78-20098 [N*SA-TH-78U75] H78-21159 New techniques for low cost strapdown inertial SPOILEBS systems Wind-tunnel investigation at Bach numbers from N78-21073 1.90 to 2.86 of a canard-controlled missile with STBESS ANALYSIS ram-air-jet spoiler roll control in the Stress analysis of typical flaws in aerospace langley Unitary Plan Wind Tunnel structural components using 3-D hybrid [HASA-TP-1124] N78-20079 displacement finite element method STABILITY SDGHENTATION [AIAA 78-513] A78-29812 Optimum tail plane design for artificially STBESS REASUBBHENT stabilized aircraft Report on aircraft fatigue studies in-flight A78-29331 monitoring and stress measurements Fly-by-wire flight control [AD-AO<19876] N78-21102 A78-29935 STROCTOBAL ANALYSIS STABILITY DEBIVATIVES Aeroelastic analysis and ground vibration survey Transonic static and dynamic stability of the NASA, Grumman American Yankee modified characteristics of a finned projectile for spin testing configuration [NASA-CR-156119] N78-20109 [NASA-TH-71058] N78-20072 Study of advanced composite structural design STABILITY TESTS concepts for an arrow wing supersonic cruise Transonic static and dynamic stability configuration, task 3 characteristics of a finned projectile [NASA-CB-KI5192] N78-20112 configuration Thermal design for areas of interference heating [NASA-TB-714058] N78-20072 on actively cooled hypersonic aircraft STANDABDIZATION [NASA-CB-2828] B78-20117 Microwave landing systems time reference STBOCTDBAL DESIGN scanning beam used to determine aircraft approach Preliminary design of composite wings for A78-29221 buckling, strength and displacement constraints STATIC ABBODYNABIC CHABACTEBISTICS [AIAA 78-U66] A78-29777 Subsonic longitudinal and lateral-directional Future trends in aircraft structural design and static aerodynamic characteristics of a general materials research fighter configuration employing a jet [AIAA 78-U65] A78-29822 sheet vortex generator Alloy needs and design - The airframe [NASA-TH-7HOII9] N78-20071 A78-30856 Effect of turbulent jet mixing on the static lift Hirage 2000 French flighter aircraft design performance of a power augmented ram ving characteristics, SNECRA H53 engine and avionics [AD-A049620] S78-21060 A78-31755 STATIC TESTS The error function of analytical structural design The error function of analytical structural design in aircraft component failure in static tests in aircraft component failure in static tests A78-32123 A78-32123 Optimum design of wind tunnel contractions [AIAA 78-819] A78-32373

A-30 SUBJECT IHDBX SOPEBSORIC HISD TORHELS

Study of advanced composite structural design Effect of winglets on a first-generation jet concepts for an arrow wing supersonic cruise transport wing. 5: Stability characteristics configuration, task 3 of a full-span wing with a generalized fuselage [BASA-CB-1115192] H78-20112 at high subsonic speeds Study of advanced conposite structural design [HASA-TP-1163] B78-200B1 concepts for an arrow wing supersonic cruise SOBSOHIC HIBD TOBBELS configuration Unsteady two dimensional airloads acting on [NASA-CB-2825] H78-20116 oscillating thin airfoils in subsonic ventilated Nodern wing technology for general aviation aircraft wind tunnels fBHFT-FB-H-77-111] H78-20127 [HASA-CB-2967] H78-21059 STBOCTORAL DESIGH CBITEBIA SOCTIOH Basic fatigue curves of aircraft structures Effect of boundary layer suction through slits on A78-30356 the efficiency of turbooachine outlet diffusors Some specific bydrodynamic and aerodynamc A78-30572 problems of surface-effect ships with sidewalls SOPEBCBITICAL PLOW A78-31126 Experiments on supercritical flows in a Quality assurance in the fabrication of products self-correcting wind tunnel in aviation technology A78-3231I5 478-32267 SOPEBCBITICAL BIBGS Trends of future turbine life prediction: Time Flight evaluation of the transonic stability and phase automated analysis and test verification control characteristics of an airplane N78-211K3 incorporating a supercritical wing STBOCTOBiL FJIIDEE [HASA-TP-1167] H78-201UO Experimental investigation of composite wing failure SOPEBSOHIC ilBCBAPT [AIAA 78-509] A78-29809 Study of advanced composite structural design Some lessons learned from aircraft accidents - The concepts for an arrow wing supersonic crnise engineering aspects configuration, task 3 A78-29936 [NASA-CB-1U5192] H78-20112 The error function of analytical structural design SOPEBSOHIC BOOHDABI LAIEBS in aircraft component failure in static tests Sting effects as determined by the measurement of A78-32123 pitch-damping derivatives and base pressures at STBOCTOBiL IHFLOEHCE COEPFICIEHTS nach number 3 Influence of structural components of a by-pass [AIAA 78-830] A78-32381 engine on its flight characteristics STOL SOPEBSOHIC COHBOSTIOB aircraft Bectangnlar capture area to circular comfcustor 178-29582 scramjet engine STBOCTOBiL BEIIABI1ITY [HASA-TH-78657] N78-21107 A-«F Blue Angel flight usage data, 1976 SOPEBSOHIC COHBOSTIOB BiHJET EHGIHES [ AD-A05016

A-31 SUPPORT INTBBFEBENCE SUBJECT INDEX

A new technique for reducing test section noise in A UD approach control using VOR/DME/ILS guidance supersonic wind tunnels B78-21083 [AIAA 78-817] A78-32371 SYSTEHS ENGINEERING SOPPOBT INTBBFBBEBCE Gondola system for helicopter transport of Sting effects as determined by the measurement of external cargo pitch-damping derivatives and base pressures at [AD-AOU7560] B78-20120 Hach number 3 [AIAA 78-830] A78-32381 SOPPOBT SISTEHS Model support system interference on zero-lift TACAN drag at transonic speeds Effect of reliability programs on life cycle cost fAIAA 78-809] A78-32363 - A case history of TACAS test set SOBFACE COOLIHG A78-29178 Protection of cooled blades of complex internal Integrated Doppler/TACAN navigation through structure conformity with the least squares method - 878-21111 Analysis from registered flight data SOBFACE CRACKS A78-29906 Hicrofractographic fracture analysis of some TAIL SURFACES aircraft parts Fatigue life analysis of the L 13 /BlaniJt/ glider A78-28789 A78-30360 SDBF1CE EFFECT SHIPS TAKEOFF Some specific hydrodynamic and aerodynamic The energy costs of some noise abatement procedures problems of surface-effect ships vith sidewalls A78-31313 A78-31126 TAKEOFF BONS Dynamic response of lift fans subject to varying Aircraft takeoff from dirt airstrips backpressure for Surface Effect Ships A78-32273 [AIAA PAPEB 78-756] A78-32176 TARGET RECOGNITION SOBFACE FINISHING On the possibility of classifying radar targets Quality assurance in the fabrication of products with a coherently measured echo signal in aviation technology German book A78-32267 A78-32308 SUBFACE BODGBNBSS TECHNOLOGICAL FORECASTING Runway roughness characterization by DDS approach OS Navy examining a wide range of 7/STOL concepts Dynamic Data System A78-29175 A78-30679 General aviation energy-conservation research SURVEILLANCE BADAR programs at BASA-Lewis Research Center for Ground radar - Vital tocl or luxury for non-turbine general aviation engines aircraft surface movements A78-29330 A78-31869 Future trends in aircraft structural design and SHEDEN materials Sweden's latest- and last airport [AIAA 78-165] A78-29822 A78-31868 Fuel efficiency - where we are heading in the SWEPT FOBRAHD RINGS design of future jet transports Subsonic roll damping of a model with swept-back A78-31307 and swept-forward wings Area navigation systems and procedures [BASA-TH-78677] B78-20061 N78-21091 Subsonic longitudinal and lateral-directional TECHNOLOGY ASSBSSHENT static aerodynamic characteristics for a model Flight simulation - A vital and expanding with swept back and swept forward wings technology in aircraft development [NASA-TB-71093] N78-20073 [AIAA PAPER 78-337] A78-29295 SWEPT RINGS Landing systems - The Bavy viewpoint Subsonic longitudinal and lateral-directional A78-30097 static aerodynamic characteristics for a Technical and economic evaluation of advanced air close-coupled wing-canard model in both swept cargo systems back and swept forward configurations [NASA-TB-78672] B78-20108 [BASA-TB-71092] N78-210U9 Special study: Emergency locator transmitters, an A vectori2ation of the Jaueson-caughey NYO overview transonic swept-wing computer program FLO-22-V1 [STSB-AAS-78-1] S78-21063 for the STAR-100 computer Research requirements to improve reliability of [BASA-TM-78665] N78-21050 civil helicopters Effect of leading-edge contour and vertical-tail [BASA-CR-145335] B78-21093 configuration on the low-speed stability TECHNOLOGY TBANSFEB characteristics of a supersonic transport model Remotely piloted aircraft in the civil environment having a highly-swept arrow wing A78-30506 [NASA-TB-78683J H78-21051 TELEVISION EQOIPBEBT SRBPTBACK RINGS Proposal and construction of a hybrid flight-sight Subsonic roll damping of a model with swept-back simulator with large picture projection and swept-forward wings [DGLR PAPER 77-087] A78-319D5 [BASA-TM-78677] B78-20061 TELEVISION SYSTBBS Subsonic longitudinal and lateral-directional Development of systems and techniques for landing static aerodynamic characteristics for a model an aircraft using onboard television with swept back and swept forward wings [NASA-TP-1171] B78-20im [NASA-TB-7II093] B78-20073 TEBPEBATOBE DISTBIBDTION SYSTEB FAILOBES Investigation on temperature distribution near Effect of reliability programs on life cycle cost film cooled airfoils - P case history of TACAB test set N78-21127 B78-29178 Calculation of temperature distribution in disks Flight test results of the Strapdown heiad and cooling flow in a transient state Inertial Reference Dnit (SIRD). Volume 3: K78-21157 Appendices A-G TEBPEBATOBE EFFECTS [NASA-TM-73221] B78-20098 Thermal design for areas of interference heating Reliable dual-redundant sensor failure detection on actively cooled hypersonic aircraft and identification for the NASA F-8 DFBH aircraft [BASA-CE-2828] B78-20117 [KASA-CR-29UU] N78-20111 TEBPEBATORE SENSORS SYSTBBS ANALYSIS Bickel/cadmium aircraft batteries: Single sensor Accuracy considerations on new Bicrowave Landing temperature monitoring Systems (BLS) from an operational point of view [AD-A037722] U78-20635 B78-21081

A-32 SUBJECT 1BDEI TBABSOBIC SPEED

TEBSILE TESTS TILTIBG BOTOBS Experimental investigation of coaposite wing failure Effect of high lift flap systems on the conceptual [AIAA 78-509] A78-29809 design of a 1985 short-haul commercial STOL tilt TEBBIBAL COBFIGOBBD VEHICLE PBOGBAB rotor transport Tereinal-area flight experience with the NASA [NASA-TB-78H70] N78-21094 Terninal Configured Vehicle TIDE DBPBBDEBCE 178-31972 Time-dependent fire behavior of aircraft cabin TEBBAIB FOLLOWING AIBCBAFT materials Limtations of the OTTfS helicopter in perforning [AD-A050923] N78-2123* terrain flying with external loads TIRE BEASOBEBEBT [AD-A047568] 878-20121 Estimating times to early failures using finite TEST CHAHBEBS data to estimate the Beibull scale parameter Unique test capabilities of the Eglin AFE HcKinley [AD-A050263] B78-2052H climatic Laboratory TITABIOB ALLOTS A78-32127 Alloy needs and design - The airframe TEST EQDIPBBBT A78-308S6 Effect of reliability programs on life cycle cost TOBOIDAL IBEELS - A case history of TACAN test set Aircraft takeoff from dirt airstrips A78-29II78 A78-32273 TEST FACILITIES TRAILING EDGES A critical examination of expansion tannel Calculation of supersonic flows past wings with performance allowance for trailing tangential [AIAA 78-768] A78-32329 discontinuities within the framework of a model Status and operational characteristics of the employing a system of Euler eguations National Transonic Facility A78-28958 [AIAA 78-770] - A78-32331 The influence of jets of cooling air exhausted Design and subscale tests of a diffuser system for from the trailing edges of a supercritical a Bach t scramjet test facility turbine cascade on the aerodynamic data [AIAA 78-771] A78-32332 N78-21118 ?n experimental facility for vind engineering TBAILIBG-EDGB FLAPS research On the calculation of the incompressible flow past [AIAA 78-813] A78-32367 an aerofoil with a jet flap Hypersonic heat transfer test program in the VKI A78-31838 longshot facility ogive body configuration TBAIBIBG SIBDLATOBS [AD-A050295] N78-20086 Simulation in the development of the training and Smoke abatement for DOD test cells ground-attack aircraft Alpha Jet [AD-A050223] N78-20118 A78-31913 A sub-scale turbojet test cell for design TBAJECTOBY OPTIMIZATION evaluations and analytical model validation [lore about flight-path-angle transitions in [AD-AOU9862] N78-21166 optimal airplane climbs TEXTILES A78-32098 Aerodynamic fluid-fiber interactions TBABSFEB FORCTIOBS [NT-77-CN-1] H78-20060 Dsing simulation to determine the transfer TBEBBAL CYCLIBG TESTS function of the electronic part of a control locp Pressure cycling fatigue tests of F-111 crew for gas turbine aircraft engines module glass transparencies A78-29584 [AD-AOU9625] N78-20119 TBABSIEBT BESPOBSE TBEBBAL PBOTECTIOB The use of transient testing techniques in the A review of technigues for the thermal protection Boeing YC-11 flutter clearance program of the vails of the combustion chamber and [AIAA 78-505] A78-29806 reheating ducts of turboreactors THABSBISSIOB EFFICIENCY N78-21131 Space optical communications with the Nd:YAG laser THERHAL BESISTABCE A78-30886 Fire resistivity and toxicity studies of candidate Radio interference in helicopter-borne pulse aircraft passenger seat materials Doppler radars [NASA-TM-78468] K78-21214 A78-31038 TREEBOOTBABIC EQOILIBBIOH TRABSBISSIOBS (BACHIBE ELEBEBTS) Problems ccncerning high temperatures in small Helicopter freewheel unit design guide tarbomachines [AD-AOM7559] B78-20121 N78-21121 TBABSOBIC FLOI TBIB SINGS Transonic flows past a lift profile Calculation of supersonic flows past wings with A78-28961 allowance for trailing tangential A lifting surface theory based on an unsteady discontinuities within the framework of a model linearized transonic flow model employing a system of Enler equations [AIAA 78-501] A78-29820 A78-28958 Vanational principles for the transonic airfoil Three-dimensional flow of hypersonic gas past a problem thin airfoil A78-30891 A78-30002 The shock tube as a device for testing transonic TBBEE DIBEBSIOBAL BOOBDABT L1TE8 airfoils at high Reynolds numbers Hind tunnel model and measuring technigues for the [AIAA 78-769] A78-32330 investigation of three-dimensional turbulent An empirical correction for wind tunnel wall boundary layers blockage in two-dimensional transonic flow [AIAA 78-781] A78-32340 [AIAA 78-806] A78-32360 TBBEB DIHEBSIOBAL FLOi A vectorization of the Jameson-Caughey NYU Three-dimensional flow of hypersonic gas past a transonic swept-wing computer program FLO-22-V1 thin airfcil for the STAB-100 computer A78-30002 [NASA-TB-78665] N78-21050 A three-dimensional potential-flow program with a Numerical study of transonic flow over oscillating geometry package for input data generation airfoils using the full potential equation [NASA-CF-iq5311] 178-210U7 [BASA-TP-1120] N78-21055 THBDST BEASOBBHEBT TBABSOBIC SPEED Thrust computing system applications to increase Hodel support system interference on zero-lift engine life and provide fuel conservation drag at transonic speeds A78-31311 [AIAA 78-809] A78-32363 Airflow and thrust calibration of an F100 engine, Flight evaluation of the transonic stability and S/N P680059, at selected flight conditions control characteristics of an airplane [HASA-TP-1069] N78-21112 incorporating a supercritical wing [NASA-TP-1167] H78-20140

A-33 THAHSOHIC «IBD TOHHEIS SUBJECT IBOEX

TBAHS011IC BIRD TOHHEIS Effect of high lift flap systems on the conceptual An intermittent high Reynolds number wind tunnel design of a 1985 short-haal commercial STOL tilt [AIAA 78-766] A78-32327 rotor transport The induction driven tunnel T2 at OUEBA-CEBT - [BASA-TH-78U7U ] H78-21094 Flow qualities, testing techniques and examples Fuel conservation merits of advanced turboprop of results transport aircraft CAIAA 78-767] S78-32328 [HASA-CH-152096] B78-21095 Status and operational characteristics of the TBABSPOETATION National Transonic Facility Performance and design of transportation-cooled UlAA 78-770] 1178-32331 turtine blading A constant aerodynamic parameter testing technique H78-21129 with automatic wind tunnel control TBABSPOBTATIOH ESEKGT [AIAA 78-78U] A78-323M2 Aviation fuel usage - Economy and conservation The Boeing Aerodynamic Labs data system A78-30698 [AIAA 78-789] A78-32316 TBIAIGDLATIOH A parametric experimental study of the DBF DF triangulation system for control and interference effects and the boundary-condition guidance of military aircraft coefficient of slotted wind-tunnel walls H78-21077 [AIAA 78-805] 478-32359 TOBBIRE BLADES Condensation and its growth down the test-section The effect of hub fairings on wind turbine rotor of the Langley 0.3-m transonic cryogenic tunnel performance [AIAA 78-811] A78-32365 A78-30039 Transonic static and dynamic stability Effect of cooling-hole geometry on aerodynamic characteristics of a finned projectile performance of a film-cooled turbine vane tested configuration with cold air in a two-dimensional cascade [NASA-TH-7Q058] N78-20072 [NASA-TP-1136] S78-20080 TRiHSPlBATIOH Two-dimensional cold-air cascade study of a The influence of transpiration cooling on turbine film-cooled turbine stator blade. 5: blade boundary layer Comparison of experimental and analytical N78-21130 aerodynamic results for blade with 12 rows of Experimental evaluation of a transpiration cooled 0.038-centineter-(0.01S inch) diameter coolant nozzle guide vane holes having streamwise ejection angles N78-21131 [HASA-TP-120U] N78-20133 TBAHSPOBT AIBCBAFT Project optimisation of military gas turbines with The An-26 aircraft: Construction and use respect to turbine life Russian book 1178-21120 A78-30273 Hot cascade test results of cooled turbine blades Choice of engine design for small transport aircraft and their application to actual engine conditions A78-30357 N78-21125 The problem of the acoustic properties of the Investigations of the local heat transfer propeller and Q-fan type blower with regard to coefficient of a convection cooled rotor blade exterior and interior noise in transport aircraft N78-21126 A78-30358 Investigation on temperature distribution near The SASA Aircraft Energy Efficiency Program film cooled airfoils A78-31302 N78-21127 Prospects for energy conserving STOL transports Erosion prevention and film cooling on vanes using prop-fans N78-21128 A78-31303 Performance and design of transportation-cooled Fuel saving potential of Hach 0.8 twin engine turbine blading prop-fan transports 1178-21129 A78-31306 The influence of transpiration cooling on turbine Fuel efficiency - Where we are heading in the blade boundary layer design of future jet transports 1178-21130 A78-31307 Heat transfer characteristics of the closed STOt, system fuel savings - Ground and air thermosyphon system A78-31312 H78-21132 The energy costs of some noise abatement procedures New materials for high temperature turbines: A78-31313 ONEBA's DS composites confronted with the blade Air traffic control and energy conservation in air problems operations H78-21139 A78-3131H Protection of cooled blades of complex internal Effect of winglets on a first-generation jet structure transport wing. 3: Pressure and spanwise load H78-211U1 distributions for a semspan model at Bach 0.30 Hew computation method of turbine blades film in the Langley 8 ft transonic tnnnel cooling efficiency [HASA-TH-D-8U78] N78-20063 117 8-21154 Effect of winglets on a first-generation jet The effect of free-stream turbulence upon heat transport wing. 1: Longitudinal aerodynamic transfer to turbine blading characteristics of a semispan model at subsonic 1178-21155 speeds in the Langley 8 ft transonic tunnel TOBBIBE EBGIHES [HASA-TN-D-8U73] N78-2006I1 'Chain pooling1 model selection as developed for Effect of winglets on a first-generation jet the statistical analysis of a rotor burst transport wing. 2: Pressure and spanvise load protection experiment distributions for a semispan model at high A78-29327 subsonic speeds in the Langley 8 ft Protection of cooled blades of complex internal transonic tnnnel structure [NASA-TN-D-817II] N78-20065 H78-211U1 A new method for estimating current and future Trends of future turbine life prediction: Time transport aircraft operating economics phase automated analysis and test verification [KASA-CB-1«5190] N78-20091 1178-2111(3 Simulator evaluation of a flight-path-angle TOBBI8E SBEELS control system for a transport airplane with An experimental facility for wind engineering direct lift control research [NASA-TP-1116] 1178-20139 [AIAA 78-813] A78-32367 Factors affecting the retirement of commercial TDBBOPAB AIBCBAFT transport jet aircraft The aircraft ducted fan rNASA-CB-152115] H78-21092 A78-31153

A-3* SUBJECT IHDBX VEBTItATIOB

TOBBOPAB EH6IBES An empirical correction for wind tunnel wall Giants battle in OS snail turbine aarket jet blockage in two-dimensional transonic flow engines for small aircraft [AIAA 78-806] A78-32360 478-291711 TBO FBASE PlOi The problem of the acoustic properties of the Boundary-layer interaction with a nonegnilibrium propeller and Q-fan type blower with regard to two-phase stream on a surface being burned out exterior and interior noise in transport aircraft in*an axisymmetric Laval nozzle A78-30358 A78-28610 The aircraft ducted fan A78-31153 Life-cycle analysis of aircraft turbine engines u [AD-A0503Q9] B78-20135 OH-1 HE1ICOPTEB TOBBOGEBEBATOBS Correlation study of the OH-18 helicopter blast Mode of operation and characteristics of Darneos test results from the DICE-TBBOB event rotors [AD-A050U631 H78-20122 A78-28560 OLTBJHIGB PBEQOEBCIES TOBBOJET EBGIBE COITBOL The AB/AEC-16t radio - Life-cycle-cost savings Control of aircraft turbine engine acceleration UHP communication equipment reliability and A78-29583 maintainability improvement Using simnlation to determine the transfer A78-29179 function of the electronic part of a control loop DBSTEADT FLOS for gas turbine aircraft engines A lifting surface theory based on an unsteady AT8-2958H linearized transonic flow model Properties of hydraulic servomotor controlled by [AIAA 78-501] A78-29820 flapper valve or by edge valve turbojet A technique for vorticity measurement in unsteady engine system flow A78-29587 [AIAA 78-801] A78-32356 TOBBOJET EHGIHES OBSBEPT RINGS Fuel pressure increase limiter Correlation of laser velocimeter measurements over [AD-A019393] N78-21117 a wing with results of two prediction techniques A sub-scale turbojet test cell for design in the Langley V/STOL tunnel evaluations and analytical model validation [NASA-TP-1163] B78-21110 [AD-AOH9862] N78-21166 OPPEB ATHOSPBEBE TDBBOPBOP AIBCBAFT Research on various aspects of atmospheric flight The An-26 aircraft: Construction and use [AD-A033681] 1178-20088 Russian book DPPEB SOBFACE BLOBH FLAPS A78-30273 Unsteady loads due to propulsive lift TOB60PBOF EHGIBES configurations. Part B: Pressure and velocity Giants battle in DS small turbine market jet measurements in a three dimensional wall jet engines for small aircraft [SASA-CR-156121] B78-20068 978-29171 DSEB BABOALS (COBPUTEB PBOGBABS) Influence of structural components of a by-pass Eotorcraft linear simulation model. Volume 3: engine on its flight characteristics ST01 User's manual aircraft [N&SA-CB-152079-VOL-3] 1178-20138 A78-29582 Choice of engine design for small transport aircraft A78-30357 TUBBOIEHCE EFFECTS V/STOL AIBCBAFT Handling gualities of aircraft in the presence of OS Navy examining a wide range of V/STOL concepts simulated turbulence A78-29175 A78-296U3 Low-speed test limit of V/ST01 model located TDBBD1ENCE BBTBBS vertically off-center Hean velocity, turbulence intensity and turbulence H78-296U2 convection velocity measurements for a New trends and problem areas in automatic flight convergent nozzle in a free jet wind tunnel control [NASA-CR-29I)9] H78-21058 ' A78-30252 TDBBOLEST BOOBDABY LATBB The wind and turbulence measuring system of the Hind tunnel model and measuring techniques for the BAE Airborne V/STOL Simulator investigation of three-dinensional turbulent A78-30850 boundary layers TABES [AIAA 78-781] A78-323HO Effect of cooling-hole geometry on aerodynamic TOBBOTEHT FLOS performance of a film-cooled turbine vane tested Investigation of the flov in a plane diffuser by with cold air in a two-dimensional cascade means of a laser Doppler anemometer [NASA-TP-1136 ] B78-20080 - A78-28969 VABIABLE GEOBEIBT STBOCTOBES Engineering calculation methods for turbulent High temperature H2-Air variable geometry flow, volume 1 combustor and turbine: Test facility and [IC-AEBO-77-102-VOL-1] 1178-20091 measurements Engineering calculation methods for turbulent B78-21137 flov, volume 2 VABIJTIOHAL PBIBCIPLES [•IC-AERO-77-102-VOL-2] 1178-20092 Variational principles for the transonic airfoil Engineering calculation methods for turbulent problem flow, volume 3 178-30891 [IC-AERO-77-102-VOL-3] 1178-20093 VEHICLE IBEELS Effect of turbulent ]et mixing on the static lift Aircraft takeoff from dirt airstrips performance cf a pover augmented ram wing A78-32273 [AD-AOH9620] H78-21060 A perturbation method for predicting amplitudes of The influence of coolant turbulence intensity of nonlinear wheel shimmy film cooling effectiveness B78-21060 1178-21136 VELOCITY BBASOHBBEHT The effect of free-streaa turbulence upon neat Unsteady loads due to propulsive lift transfer to turbine blading configurations. Part B: Pressure and velocity N78-21155 measurements in a three dimensional wall jet TUBBOLEHT IAKES [NASA-CB-156121] N78-20068 Some measurements in two-dimensional turbulent wakes VEBTHATIOH A78-31836 flixed ventilated foils design for mmersed THO DIBESSIOBAL FLO! hydrofoils Some measurements in two-dimensional turbulent wakes A78-31127 A78-31836

A-35 VEBTICAL TAKEOFF AIBCBAFT SUBJECT INDEX

VBBtlCiL TAKEOFF AIBCBAFT WAVE DIFFBACTION The feasibility of the jet-flap rotor as a lift Special problems in the determination of the generator for vertical takeoff and landing radiation characteristics of antennas on aircraft aircraft and satellites with the aid of [AD-A05021U] H78-20125 geometric diffraction theory Experimental investigation of effect of jet decay A78-31582 rate on 3et-induced pressures on a flat plate BAVE EQUATIONS [NASA-CB-2979] H78-21096 Prediction of the unsteady airloads on Theoretical flow characteristics of inlets for harmonically oscillating spheroids based on an tilting-nacelle VTOL aircraft analytical solution of the governing wave equation [NASA-TP-1205] B78-2111U A78-29338 VIB8ATIOH DABPIHG BEAPOB SYSTEBS On soand transmission into a heavily-damped cylinder Life-cycle analysis of aircraft turbine engines aircraft noise in fuselage [AD-A0503U9] K78-20135 A78-31019 A multi-sensor implementation for navigation, VIBBATIOH SIBOLATORS position location, position update, Automatic sustainment of resonance conditions in reconnaissance, and weapon delivery: the multipoint excitation of flight-vehicle AN/ABN-101 (V) vibrations S78-21082 A78-32268 BEIB0LL DENSITY FUNCTIONS VIB8ATIOH TESTS Estimating times to early failures using finite The use of transient testing techniques in the data to estimate the Weibull scale parameter Boeing YC-1t flutter clearance program [AD-A050263] N78-205211 [AIAA 78-505] A78-29806 WEIGHT AHALYSIS An engine nozzle vibration phenomenon encountered Weight design and the efficiency of passenger in B-1 flight tests aircraft. Volume 2 - Calculation of the center A78-32129 of gravity and moments of inertia of aircraft. Practical experience in vibration testing external Weight analysis Russian book avionics systems A78-30175 A78-3213U BEIGBT REDUCTION VIBBATOHI LOADS Weight design and the efficiency of passenger Effect of noise on life of aircraft structure and aircraft. Volume 2 - Calculation of the center design of parts resistant to acoustic loads of gravity and moments of inertia of aircraft. A78-30352 Weight analysis Russian book VISIBILITY A78-30175 Some test results concerning visibility of Remotely piloted aircraft in the civil environment obstacle and hazard beacons A78-30506 A78-29907 Optimization of the structure of a multibulkhead VISUAL TASKS large-aspect-ratio wing Current problems of flight simulators for research A78-32275 A78-2921U BELD STRENGTH VOBTEI 6EBBBATOBS Basic fatigue curves of aircraft structures Subsonic longitudinal and lateral-directional A78-30356 static aerodynamic characteristics of a general BIBD EFFECTS research fighter configuration employing a jet Applications of wind tunnels to investigations of sheet vortex generator wind-engineering problems [NASA-TB-71IOU9] H78-20071 [AIAA 78^812] A78-32366 VOBTEX SHEETS BIND EBOSION Subsonic longitudinal and lateral-directional The AEDC Range K facility for erosion testing static aerodynamic characteristics of a general [AIAA 78-775] A78-32331 research fighter configuration employing a jet BIBD BEASUBEBEBT sheet vortex generator The wind and turbulence measuring system of the [NASA-TH-7UOU9] N78-20071 DAE Airborne V/STOL Simulator VOBIICES A78-30850 Hydrodynamic effect on a contour produced by an »n experimental facility for wind engineering ideal incompressible flow of constant vorticity research 478-28956 [AIAA 78-813] A78-32367 VOBTICITI BIND TUNNEL APPABATUS A technique for vorticity measurement in unsteady New rotation-balance apparatus for measuring flow airplane spin aerodynamics in the wind tunnel fAIAA 78-801] A78-32356 [AIAA 78-835] A78-32386 BIND TUNNEL CALIBRATION Determination of high attitude wall corrections in w a lew speed wind tunnel WALL FLOS [AIAA 78-810] A78-3236U Experiments on supercritical flows in a BIND TUNBEL DBIVES self-correcting wind tunnel The use of fluidized beds for heating air for wind A78-323115 tunnels BAIL JETS [AIAA 78-818] A78-32372 Unsteady loads due to propulsive lift BIBD TUNBBL MODELS configurations. Part B: Pressure and velocity Hind tunnel model and measuring techniques for the measurements in a three dimensional va11 jet investigation of three-dimensional turbulent [HASA-CR-156121] 1178-20068 boundary layers BAILS [AIAA 78-781] A78-323DO A review of techniques for the thermal protection Ejector-powered engine simulators for small-scale of the walls of the combustion chamber and wind tunnel models of high performance aircraft reheating ducts of turboreactors [AIJA 78-826] A78-32388 N78-21131 A brief examination of the flow external to an WASHING SYSTEBS F-111 intake at Bach 1.6 Clear air turbulence accidents [~ABL/BE-NOTE-357] H78-2105II A78-28833 Transonic wind tunnel tests on two-dimensional BATEB EBOSIOH aerofoil sections. Determination of pressure The AEDC Range K facility for erosion testing distribution and drag for an aerofoil with a [AIAA 78-775] A78-3233Q modified NACA 65 sub2-215 section in FFA wind tunnel S5, part 2 [FFA-TN-AU-725] B78-21062

A-36 SUBJECT IBDEI 9IHG P1BELS

SIBD TOBBBL BOSZ1ES Hean velocity, turbulence intensity and turbulence £ new technique for reducing test section noise in convection velocity measurements for a supersonic wind tunnels convergent nozzle in a free jet wind tunnel [Alii 78-817] i78-32371 [BiSi-CB-2919] H78-21058 BIBD TOBBEL STABILITY TESTS APL radiometer wind tunnel test program with Status and operational characteristics of the simulated aircraft radome National Transonic Facility [BSB-1230] H78-21102 [ilii 78-770] i78-32331 Correlation of laser velocimeter measnreaents over WIBD TUBBEL TESTS a wing with results of two prediction techniques low-speed test limit of V/ST01 model located in the Langley V/STOL tunnel vertically off-center [HASi-TP-1168] H78-21110 i78-296i(2 BIHD TOBBEL BAILS Performance of the iEiVi aircraft with wing-tip Tunnel interference assessment by boundary vinglets measurements i78-30256 i78-30689 Dynamic response of lift fans subject to varying Experiments on supercritical flows in a backpressure for Surface Effect Ships self-correcting wand tunnel [ilii P1PEE 78-756] A78-32176 i78-323«5 in intermittent high Reynolds nnnber wind tunnel i parametric experimental study of the [ilii 78-766] A78-32327 interference effects and the boundary-condition The induction driven tunnel T2 at ONEEA-CEBT - coefficient of slotted wind-tunnel walls Flow qualities, testing technigues and examples [ilii 78-805] A78-32359 of results An empirical correction for wind tunnel wall [ilii 78-767] A78-32328 blockage in two-dimensional transonic flow Design and subscale tests cf a diffuser system for [ilii 78-806] A78-32360 a nach 1 scramjet test facility Determination of high attitude wall corrections in [iliA 78-771] A78-32332 a low speed wind tunnel Supersonic aerothermal testing - A new reguirement [AIAi 78-810] A78-32361 [Alii 78-7731 A78-32333 Optimum design of wind tunnel contractions Wind tunnel model and measuring technigues for the [AIAA 78-819] A78-32373 investigation of three-dimensional turbulent WIBD TDBBELS boundary layers TESTPLT: Interactive computer procedure for [ilii 78-781] A78-32310 wind-tunnel-data management, retrieval, A constant aerodynamic parameter testing technique comparison, and plotting with automatic wind tunnel control [SASA-1H-78663] N78-20111 [AIAA 78-781] A78-32312 WISH VELOCIT? BBASOBEBEBT A computer-controlled video instrumentation Hind tunnel model and measuring techniques for the technigue for wind tunnel testing of full-scale investigation of three-dimensional turbulent lifting parachutes boundary layers [AIAA 78-785] A78-32313 [AIAA 78-781] A78-32310 Semispan wind tunnel test cf a computer-controlled 8IHDBILLS (WIBDPORBBED BiCBISBS) self-optinizing flexible technology wing The effect of hob fairings on wind turbine rotor [Alii 78-786] A78-32311 performance Experiments on supercritical flows in a A78-30039 self-correcting wind tunnel WIHDFOBBBED GENEBITOBS A78-32315 Mode of operation and characteristics of Darrieus The Boeing Aerodynamic Labs data system rotors [ilii 78-789] A78-32316 A78-28560 Further experimental evaluation of the WIBDSBIE1DS electrostatic roll sensor at Hach 2.3 and 3.5 Evaluation of windshield materials subjected to [AIAA 78-802] A78-32357 simulated supersonic flight Model support system interference on zero-lift [iD-i019981] N78-21101 drag at transonic speeds WIBG FLAPS [Alii 78-809] A78-32363 Effect of high lift flap systems on the conceptual Applications of wind tunnels to investigations of design of a 1985 short-haul commercial STOL tilt wind-engineering problems rotor transport [ilii 78-812] i78-32366 [BiSi-TH-78170] K78-21091 in experimental facility for wind engineering HIBG FLOW BETBOD TESTS research On the calculation of the incompressible flow past [ilii 78-813] A78-32367 an aerofoil with a jet flap Moving ground simulation by tangential blowing A78-31838 [ilii 78-814] ( A78-32368 WIBG LOADIBG Sting effects as determined by the measurement of Experimental investigation of composite wing failure pitch-damping derivatives and base pressures at [Alii 78-509] A78-29809 nach number 3 Acoustic emission detection of fatigue crack [Alii 78-830] A78-32381 growth in a production-size aircraft wing test Onset of condensation effects with a NiCi 0012-61 article under simulated flight loads airfoil tested in the langley 0.3-meter A78-31733 cryogenic tunnel Effect of winglets on a. first-generation jet [NASi-TH-78666] N78-20071 transport wing. 3: Pressure and spanwise load Wind-tunnel investigation at nach numbers from distributions for a semispan model at Hach 0.30 1.90 to 2.86 of a canard-controlled missile with in the Langley 8 ft transonic tunnel ram-air-^et spoiler rcll control in the [HASA-TN-D-8178] N78-20063 Langley Unitary Plan Wind Tunnel Effect of winglets on a first-generation jet fNiSi-TP-1121] S78-20079 transport wing. 2: Pressure and spanwise load Comparison of measured and calculated helicopter distributions for a semispan model at high rotor impulsive noise wind tunnel test data subsonic speeds in the Langley 8 ft and prediction analysis technigues transonic tunnel [NASA-TB-78173] R78-20917 [HiSA-TII-D-8171] H78-20065 Acoustical effects of blade tip shape changes on a WIBG OSCILLATIOHS full scale helicopter rotor in a wind tunnel Theory of bending-torsional self-oscillations of [»ASi-CS-152082] B78-20918 an aircraft wing system Comparison of aerodynamic data measured in air and 178-32261 Freon-12 wind-tunnel test mediums WIRG PAHELS [NiSi-TH-78671] B78-21052 i fail-safe analysis of a spanwise wing-panel splice Low-speed aerodynamic characteristics from [iliA 78-187] A78-29791 wind-tunnel tests of a large-scale advanced Optimization of the structure of a mnltinulkhead arrow-wing supersonic-cruise transport concept large-aspect-ratio wing [HiSi-CB-115280] N78-21053 i78-32275

A-37 BIHG PLAHPOBBS SUBJECT IHDBX

»ING PLJNPOBHS Effect of tnrbulent jet nixing on the static lift performance of a power augnented ram wing [AD-A009620] N78-21060 »ISG PBOFI1ES Effect of winglets on a first-generation jet transport wing. 3: Pressure and spanwise load distributions for a semispan model at Bach 0.30 in the Langley 8 ft transonic tunnel [SASA-TN-D-8178] N78-20063 Effect of vinglets on a first-generation jet transport wing. 2: Pressure and spanmse load distributions for a semispan model at high subsonic speeds in the Langley 8 ft transonic tunnel [NASA-TN-D-817H] N78-20065 WING SPAN Effect of winglets on a first-generation jet transport wing. 5: Stability characteristics of a full-span wing with a generalized fuselage at high subsonic speeds [NASA-TP-1163] N78-20081 HING TIPS Performance of the ABAVA aircraft with wing-tip mnglets A78-30256 RING-FUSELAGE STOBES Prediction of the unsteady airloads on harmonically oscillating spheroids based on an analytical solution of the governing wave eguation A78-29338 "INSISTS Performance of the AHA7A aircraft with wing-tip winglets A78-30256 Effect of winglets on a first-generation jet transport wing. 3: Pressure and spanwise load distributions for a semispan nodel at Bach 0.30 in the Langley 8 ft transonic tunnel fNASA-TN-D-8U78] N78-20063 Effect of winglets on a first-generation jet transport wing. 1: Longitudinal aerodynamic characteristics of a semispan model at subsonic speeds in the Langley 8 ft transonic tunnel [SASA-TN-D-8U73'] N78-2006U Effect of winglets on a first-generation jet transport wing. 2: Pressure and spanwise load distributions for a semispan nodel at high subsonic speeds in the Langley 8 ft transonic tunnel [NASA-T1-D-81711] B78-20065 BIBGS Fatigue life analysis of the L 13 /Blanik/ glider 178-30360 Analysis of empirically determined aerodynamic and ram coefficients for a pcwer-augmented-ram wing-in-ground effect CAD-AOI)9636] N78-20087 Hodern wing technology for general aviation aircraft fBI!FT-FE-B-77-la] N78-20127

TIG LASEES Space optical communications with the Nd:YAG laser A78-30886 YC-1

ZEBO LIFT Hodel support system interference on zero-lift drag at transonic speeds [AIAA 78-809] A78-32363

A-38 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 98) JULY 1978

Typical Personal Author Index Listing

PERSONALAUTHOR BBASLBT, i. D. An exploratory investigation of the effects of a ARDBIBS, J. thin plastic film cover on the profile drag of Heat transfer characteristics of the closed an aircraft wing panel thermosyphon system [NASA-TB-7U073] F78-10023 H78-21132 1 ABGYBIS, J. H. 1 Analysis and synthesis of operational loads [ISD-193] B78-20551 TITLE REPORT ABDLP, C. L. NUMBER An engine nozzle vibration phenomenon encountered in B-1 flight tests A78-32129 ATLOBI, S. S. Listings in this index are arranged alphabetically by personal author The title Stress analysis of typical flaws in aerospace of the document provides the user with a brief description of the subject matter structural components using 3-D hybrid The report number helps to indicate the type of document cited (e g NASA displacement finite element method report translation NASA contractor report) The accession number is located [AIAA 78-513] A78-29812 ATBBS, B. H. beneath and to the right of the title e g N78-10023 Under any one authors The aerodynamic behaviour of fully inflated name the accession numbers are arranged in sequence with the IAA accession parachutes numbers appearing first A78-29215 B BACBTE, C. f. ABBOTT, J. H. Lightweight, low compression aircraft diesel engine Simulated flight effects on noise characteristics . [BASA-CB-135300] N78-21U71 of a fan inlet vith high throat Hach number BAILEY, C. D. [NASA-TP-1199] 878-20132 Acoustic emission detection of fatigue crack ABEBHATBY, 3. growth in a production-size aircraft wing test Space optical communications with the Bd:YAG laser article under simulated flight loads A78-30886 A78-31733 ABHABAB, B. BAKH07, O. P. analytical and experimental fatigue program for The helicopter as a control object the Kfir main and nose landing gears A78-29401 A78-30259 BALL, J. C. ADAHS, 6. A. The feasibility of the jet-flap rotor as a lift Improved energy efficiency for small CTOI generator for vertical takeoff and landing transport aircraft aircraft A78-31305 [AD-A05021U] B78-20125 ADABS, J. 3. BALQDET, B. 3. Stndy of the use of a nonlinear, rate-limited Some specific hydrodynamic and aerodynamic filter on pilot control signals problems of surface-effect ships with sidewalls [NASA-TP-11M7] N78-20112 A78-31126 Pilot-model analysis and simulation study of BABKOV, V. H. effect of control task desired control response Laser and optical methods of monitoring in [NASA-TP-11UOJ H78-201B3 aircraft construction AHH8D, S. A78-30123 lodel support system interference on zero-lift BABHBTT, T. drag at transonic speeds Heavy lift helicopter flight control system. [AIAi 78-809] A78-32363 Volume 3: Automatic flight control system AICBEB. 8. development and feasibility demonstration Analysis and synthesis of operational loads [AD-A050059] B78-2116U [ISD-193] N78-20551 BAHHBELL, B. 8. AKBBETOV, T. B. A parametric experimental study of the Fuel pressure increase limiter interference effects and the boundary-condition [AD-A019393] H78-21117 coefficient of slotted wind-tunnel walls ALABSKT, I. B. [AIAA 78-805] A78-32359 Limitations of the OTTAS helicopter in performing BABBETT, L. D. terrain flying with external loads Besearch reguirements to improve reliability of [AD-AOU7568] N78-20121 civil helicopters AHDEBS, 3. B. [HASA-CB-105335] H78-21093 A new technique for reducing test section noise in BABBT, J. D. supersonic wind tunnels Space optical communications with the NdrYAG laser [AIAA 78-817] A78-32371 A78-30886 AHDBBSBH, B. B. D. BABTOB, C. K. The division of air transport markets between Investigation of interior noise in a tvin-engine carriers - Local service operations light aircraft A78-30697 A78-29601 ABDBBS01, J. B. BiBTOH, 3. A fail-safe analysis of a spanvise wing-panel splice Using simulation to determine the transfer [AIAA 78-H87] - A78-2979II function of the electronic part of a control loop AHDBEBS, B. B., JB. A78-29S80 Design and sabscale tests of a diffuser system for a Hach 1 scranjet test facility [AIAA 78-771] A78-32332

B-1 BASOVSKAH, i. 1. PB8SOSAL 40TBOE IBDEI

BASOVSKAIi, A. ». BOBYE, R. I. Effect of boundary layer suction throngh slits on The division of air transport markets between the efficiency of turbomachine outlet diffusors carriers - Local service operations A78-30572 A78-30697 BAYLEY, F. J. BODES, R. B. Performance and design of transportation-cooled The AN/ABC-161 radio - Life-cycle-cost savings turbine blading A78-29M79 N78-21129 BOECKEE, B. B. The effect of free-stream turbulence upon heat Design of a collision avoidance system model with transfer to turbine blading statistical interrogation N78-21155 N78-20107 BECKER, 1. BOGSS, D. B. Accuracy considerations on new Microwave Landing Differential altimetry for satellite orbit Systems (HLS) from an operational point of view determination N78-21081 A78-31915 BECKRITB, I. E. BOHANBON, G. 1. ft new technique for reducing test section noise in A-1P Blue Angel flight usage data, 1976 supersonic wind tunnels [AD-A05016U] N78-21100 [AliA 78-817] A78-32371 BOLES, R. A. BBIHB, B. Theoretical flow characteristics of inlets for Critical considerations on the legal development tilting-nacelle VTOL aircraft of personal liability with attention to air [NASA-TP-1205] N78-21114 transportation BOLES, B. A. A78-29911 Moving ground simulation by tangential blowing BELAYGOE, F. [AIAA 78-8U] A78-32368 Problems concerning high temperatures in small BOLSBAGIJ, V. I. turbomachines Fuel pressure increase limiter N78-21121 [AD-A019393] N78-21117 BEODSBS, C. BOEH, G. J. A reliable modular automatic system adapted to Optimal control theory (OHEB) applied to a avionics controls: Design through successive helicopter in the hover and approach phase refinements - Production [BASA-CE-152135] N78-21161 A78-30021 BOTTBELL, H. S. BBBHSTEIS, S. Lightweight, low compression aircraft diesel engine Improved energy efficiency for small CTOL [HftSA-CH-135300] N78-21471 transport aircraft BOYDBH, B. P. A78-31305 Subsonic roll damping of a model with swept-back BEBTSCHT, B. G. and swept-forward wings Effect of reliability programs on life cycle cost [NASA-TH-78677] N78-20061 - A case history Transonic static and dynamic stability A78-29U78 characteristics of a finned projectile BEST, B. configuration The influence of coolant turbulence intensity of [NASA-TB-7I4058] N78-20072 film cooling effectiveness BBADSBAI, F. N78-21136 Engineering calculation methods for turbulent BIBBING, B. flow, volume 1 New materials for high temperature turbines: [IC-AEEO-77-102-VOL-1] H78-20091 ONEEA's DS composites confronted with the blade Engineering calculation methods for turbulent problems flow, volume 2 N78-21139 [IC-AEBO-77-102-70L-2] N78-20092 BIESIADNY, T. J. Engineering calculation methods for turbulent Airflow and thrust calibration of an F100 engine, flow, volume 3 S/N P680059, at selected flight conditions [IC-AEEO-77-102-VOL-3] N78-20093 [NASA-TP-1069] N78-21112 BBBAKRELL, 3. V. BIGGEBS, J. C. nore about flight-path-angle transitions in A note on mnlticyclic control by swashplate optimal airplane climbs oscillation A78-32098 [NASA-TB-78H75] N78-21159 BBODIE, F. H. BIOT, B. New techniques for low cost Strapdown inertial Aerodynamic fluid-fiber interactions systems TNT-77-CN-1] N78-20060 N78-21073 BJOEKHAN, R. S. BEOKOF, 0. Plight test results of the Strapdown hexad Improved aircraft tracking using maneuver Inertial Reference Onit (SIBO). Volume 3: statistics enroute and in the terminal area Appendices A-G N78-21087 [NASA-TB-73221] N78-20098 BROOKS, C. R., JB. BLACKHELL, J. A., JR. Transonic static and dynamic stability An empirical correction for wind tunnel wall characteristics of a finned projectile blockage in two-dimensional transonic flow configuration [AIAA 78-806] A78-32360 [NASA-TB-7«058] H78-20072 B1AIB, A. B., JB. BBOCKBEE, J. H. B. Hind-tunnel investigation at Bach numbers from A ID approach control using VOB/DBE/ILS guidance 1.90 to 2.86 of a canard-controlled missile with N78-21083 ram-air-jet spoiler roll control BBOHE, G. R. [NASA-TP-112"] N78-20079 ft critical evaluation of the predictions of the BLANKS, J. B. SASA-Lockheed multielement airfoil computer The >EDC Range K facility for erosion testing program TAIAA 78-775] A78-3233U [NiSA-CB-115322] N78-20076 BLASCBKE, G. An improved version of the NASA-Lockheed Precise enroute navigation based on ground-derived multielement airfoil analysis computer program techniques [NASA-CB-115323] N78-20077 N78-21078 BBONBEB, D. BLHBKE, B. E. Simulation and development possibilities of the Aircraft cargo compartment fire test simulation manual control concept in the near range and program control zone [NASA-CB-151951] "O8-21223 H78-20101

B-2 PEBSONAL AOTHOB IHDEX CBOB, F.

Program fof simulation of air traffic and air CEBViHTES, J. A. space structure of the FranXfnrt near range, a Cutout reinforcement of stiffened cylindrical shells planning control and a collision avoidance [AIAA 78-512] A78-29811 systen with situation dependent avoidance CBAHTOOS, I. H. maneuvers Erosion prevention and film cooling on vanes H78-20105 N78-21128 BB0BSTEIH, A. I. CBAO, K.-t. Clear air turbulence accidents Prediction of the unsteady airloads on A78-28833 harmonically oscillating spheroids based on an BOEL1, B. B. analytical solution of the governing wave egnation Some test results concerning visibility of A78-29338 obstacle and hazard beacons CBAPLIB, B. B. A78-29907 Effect of turbulent }et mixing on the static lift BOISSON, D. performance of a power augmented ram wing Inertial smoothing and extrapolation of ILS beans: [AD-A019620] H78-21060 Application to the Airbus A 300 B CHAPBAi, G. T. H78-2107H The shock tube as a device for testing transonic BOISSOB, B. airfoils at high Reynolds numbers A review of techniques for the thermal protection [AIAA 78-769] A78-32330 of the vails of the combustion chamber and CHABPE1EL, B. reheating1 ducts of turboreactors Heasunng techniques in high temperature turbines N78-21131 H78-21151 BOLLABD, J. B. CHEHOIETH, B. B. Experimental evaluation of a transpiration cooled The error function of analytical structural design nozzle guide vane A78-32123 U78-21131 CHERHEBKO, ZB. S. BUBK, D. 0. The An-26 aircraft: Construction and use Bunvay roughness evaluation laser prcfilometer A78-30273 implementation study CBIO, B.-I. [AD-AOU9

B-3 COLLET, B. PEBSOHAL ADTHOB IIDEI

COLLKY, B. DIHI, 0. f brief examination of the flow external to an High temperature H2-Air variable geometry F-111 intake at Hach 1.6 combustor and turbine: Test facility and [ABL/ME-NOTE-357] N78-21051 measurements COBNIBGH4B, B. E. 878-21137 Steady-state unbalance response of a three-disk DHITBIEV, I. S. flerible rotor on flexible, damped supports The helicopter as a control object A78-29326 A78-29101 DOBBS, S. K. An engine nozzle vibration phenomenon encountered in B-1 flight tests DALEY, P. S. A78-32129 J ir quality impact of aircraft at ten D.S. Air DODGE, B. H. Force bases Definition of tire properties required for landing A78-32222 system analysis DA8TER, B. I. [HASA-CH-156171] H78-21326 Development of a pavement maintenance system. DODGBEBTY, J. J., Ill Volume 1: Airfield pavement condition rating Besearch requirements to improve reliability of [AD-A01888U1 S78-201U7 civil helicopters Development of a pavement maintenance management [BASA-CB-115335] B78-21093 system. Volume 2: Airfield pavement distress DOIOH, L. B. identification manual A review of methodoloqies and concepts to measure [AD-AOU9029] N78-21170 and evaluate aircraft survivability/vulnerability DAVEHPOBT, B. E. [AD-A050152] B78-21099 Transonic static and dynamic stability DBAKE, I. characteristics of a finned projectile Dnigue test capabilities of the Eglin AFB BcKinley configuration Climatic Laboratory [NASA-TH-7B058] U78-20072 A78-32127 DA7ENPOBT, P. J. DBiPIBB, J. B. Fuel saving potential of Hach 0.8 twin engine Cobalt-base alloys for hot corrosion protective prop-fan transports coatings 478-31306 N78-211U2 DA7IS. A. DOBLAT, B. J., JB. Cobalt-base alloys for hot corrosion protective Tandem-queue algorithm for airport user flows coatings A78-30677 H78-211U2 DUBKIB, J. B. DAVIS, J. H. Dynamic response of lift fans subject to varying Limitations of the DTTAS helicopter in performing backpressure terrain flying with external loads [AIAA PAPEB 78-756] A78-32176 [AD-AO

ELIBAZ, T. FLECHIEB, S. G. Performance of the AEiVA aircraft with wing-tip Effect of winglets on a first-generation jet winglets transport wing. 3: Pressure and spanwise load A78-30256 distributions for a semispan model at Bach 0.30 ELIZABOV, V. I. [HASA-TH-D-8a78] H78-20063 Basic problem of cootrol of the motion of a Effect of winglets on a first-generation jet non-Hewtonian fluid in a gap transport wing. 1: Longitudinal aerodynamic A78-32257 characteristics of a semspan model at subsonic Ells, C. P. speeds The AEDC Bangs K facility for erosion testing [RASA-TN-D-8H73] 878-2006U CAIAA 78-7751 A78-3233U Effect of winglets on a first-generation jet EBDHABB, F. transport wing. 2: Pressure and spanwise load new aspects in the movement simulation of the distributions for a semispan model at high research flight simulator of DFVLB subsonic speeds CDGIB PAPEB 77-086] A78-31950 [NASA-TN-D-8<)7I|] B78-20065 EBBS8AB, B. FOEBSCHIHG, B. Catalytic flame stabilization for aircraft Prediction of the unsteady airloads on afterburners harmonically oscillating spheroids based on an A78-31955 analytical solution of the governing wave equation EBICKSOH, J. C., JB. A78-29338 Experiments on supercritical flows in a FOLLE, H. I. self-correcting wind tunnel Drag formula for elongated aircraft noses A78-32345 A78-29718 EBHSf, B. F. POBD, T. DBF DP triangulation system for control and Doppler MLS - The OK solution guidance of military aircraft A78-2993H H78-21077 POBB, P. EBHST, B. C. Design of a collision avoidance system model with Lov frequency combustion instability in augmentors statistical interrogation S78-21138 H78-20107 EBTELT, B. J. FOX, C. B., JB. Analysis and synthesis of operational loads Subsonic longitudinal and lateral-directional [ISD-193] B78-20551 static aerodynamic characteristics of a general ESA010V, S. ID. research fighter configuration employing a jet The helicopter as a control object sheet vortex generator A78-29W1 [BASA-TB-7I40U9] H78-20071 ETHBIDGE, B. B. Subsonic longitudinal and lateral-directional Geometric restitution of single coverage aircraft static aerodynamic characteristics for a model mnltispectral scanner data with swept back and swept forward wings A78-2985H [NASA-TB-711093] H78-20073 ETLIK, T. Subsonic longitudinal and lateral-directional Influence of structural components of a by-pass static aerodynamic characteristics for a engine on its flight characteristics close-coupled wing-canard model in both swept A78-29582 back and swept forward configurations EVBBETT. i. D. [BASA-TB-714092] B78-21009 A test using simulated mission profile environments FBARCIS, B. S. A78-32126 A technigue for vorticity measurement in unsteady EVEBBABT, J. I. flow A parametric experimental study of the [AIAA 78-801] A78-32356 interference effects and the boundary-condition FBEEDHAB, P. coefficient of slotted wind-tunnel nails Space optical communications with the Bd:TAG laser [AIAA 78-805J A78-32359 A78-30886 EYEBITT. 1C. i. FBIEDBICB, B. Some measurements in two-dimensional turbulent wakes Simulation in the development of the training and A78-31836 ground-attack aircraft Alpha Jet A78-31913 FBOBBE, J. Unsteady two dimensional airloads acting on PABBRIDGE, J. B. oscillating thin airfoils in subsonic ventilated Some aspects of powerplant airframe integration wind tunnels affecting fuel conservation [NASA-CR-2967] B78-21059 A78-31304 FELDBAH, K. Nickel/cadmium aircraft batteries: Battery alarm unit GAItLAC, J. P. [AD-A039521] B78-20631 A review of technigues for the thermal protection nickel/cadmium aircraft batteries: Rapid of the walls of the combustion chamber and electrolyte exchange technigue reheating ducts of tarboreactors [AD-A039335] B78-20632 H78-21131 Nickel/cadoium aircraft batteries: Single sensor GAIBICHE, P. temperature monitoring Protection of cooled blades of complex internal [AD-A037722] N78-20635 structure Nickel/cadmium aircraft batteries: Multichannel H78-21111 gassing-rate meter GABBDCCI, B. J. [AD-A039735] N78-20636 Effect of high lift flap systems on the conceptual PBBE11, I. L. design of a 1985 short-haul commercial STOI tilt Fire resistivity and toncity studies of candidate rotor transport aircraft passenger seat materials [SASA-TB-78P711] B78-2109U [NASA-TH-78H68] H78-21213 GASSBIB, V. B. FIHK. B. B. Choice of optimal ellipsoid-surface projection \ method for calculating externally blown flap noise onto a sphere in solving problems of air [SASA-CB-295H] N78-20920 navigation PISHES. B. D. A78-28523 Summary of NASA landing gear research GABBETT, t. S., JB. [NASA-TH-78679] H78-20050 Limitations of the DTTAS helicopter in performing terrain flying with external loads [AD-AOa7568] M78-20121

B-5 GATIIH, D. H. PEBSOBAL AOTHOB IHDEI

G&TLIB, D. B. GBAVEL1E, P. Flight evaluation of the transonic stability and Product support for French equipment used by civil control characteristics of an airplane aviation companies incorporating a supercritical wing A78-29657 [HASA-TP-1167] N78-201UO GBEGOBY, T. J. G4DL, J. Bemotely piloted aircraft in the civil environment Heavy lift helicopter flight control system. A78-30506 Volume 3: Automatic flight control system GBEBS, B. C. development and feasibility demonstration Air quality impact of aircraft at ten U.S. Air [AD-A050059] 178-21164 Force bases GAYNOB, T. L. A78-32222 Lightweight, low compression aircraft diesel engine GBEBS, B. C., Ill [NASA-CB-135300] N78-21471 Smoke abatement for DOD test cells GBDDBS, J. P. [AD-A050223] N78-20148 Giants battle in OS small tarbine market A78-29174 GEE, S. I. H Development of systems and techniques for landing BABEBLARD, B. an aircraft using onboard television Modern wing technology for general aviation aircraft [NASA-TP-1171] N78-20114 [BMFT-FB-W-77-14] N78-20127 GEBA. J. HABBAKBB, L. Pilot-model analysis and simulation study of Cobalt-base alloys for hot corrosion protective effect of control task desired control response coatings [NASA-TP-1140] N78-20143 N78-21142 GEESBOB, I. J. HACKETT, J. E. Trends of future turbine life prediction: Time Moving ground simulation by tangential blowing phase automated analysis and test verification [AIAA 78-811] A78-32368 N78-21143 HAFTKA, B. I. GXABDIBA, C. B. Preliminary design of composite wings for New techniques for low cost strapdown inertial buckling, strength and displacement constraints systems [AIAA 78-U66] A78-29777 N78-21073 EAGAB, H., JB. GXLBEBT, B. G. Differential altimetry for satellite orbit System optimization by periodic control determination [AD-AOU9522] N78-21162 A78-31915 GILES, P. H. HAIBES, B. L. Advanced flight decks for the 80s Nickel/cadmium aircraft batteries: Multichannel A78-28835 gassing-rate meter GILLHAH, B. E. [AD-A039735] N78-20636 Automatic airspace BALL, G. ». A78-2883U Flight simulation - A vital and expanding GILIABD, G. E. technology in aircraft development Besults from flight and simulator studies of a [AIAA PAPEB 78-337] A78-29295 Mach 3 cruise longitudinal autopilot BALL, B. B. [NASA-TP-1180] N78-21160 Condensation and its growth down the test-section GLAZOHOV, 1. A. of the Langley 0.3-m transonic cryogenic tunnel Boundary-layer interaction with a noneqailibrium [SIAA 78-811] A78-32365 two-phase stream on a surface being burned out Onset of condensation effects with a HACJ 0012-6t in an axisymmetnc Laval nozzle airfoil tested in the Langley 0.3-meter A78-28610 cryogenic tunnel GOLBEEG, B. [NASA-TM-78666] N78-2007« Unsteady two dimensional airloads acting on BALSEY, H. D. oscillating thin airfoils in subsonic ventilated A three-dimensional potential-flow program with a wind tunnels geometry package for input data generation [NASA-CB-2967] S78-21059 [NASA-CB-1«5311] N78-210U7 GOLDSMITH, H. I. HAMILTON, J. B. Supersonic transports Acoustic emission detection of fatigue crack A78-31152 growth in a production-size aircraft wing test GOLOBIHSKII, A. I. article under simulated flight loads Three-dimensional flow of hypersonic gas past a A78-31733 thin airfoil BAB, L. S. A78-30002 The influence of transpiration cooling on turbine GOLOBKIB, V. B. blade boundary layer Three-dimensional flow of hypersonic gas past a N78-21130 thin airfoil HARKE, D. A78-30002 The HFB 320 airborne simulator of DFVLR as test GOBDOB, J. T., JB. instrument for determining flight characteristics A perturbation method for predicting amplitudes of [DGLB PAPER 77-082] A78-319U4 nonlinear wheel shimmy HAHSEH, J. S. N78-21464 Crashworthiness of aircraft fuselage structures GOBOVOI, B. I. [AIAA 78-477] A78-29785 The An-26 aircraft: Construction and use BABTE7, B. A. A78-30273 Aircraft fuel econony - The propulsion system GOTKIB. L. contribution An experimental facility for wind engineering A78-31309 research HASPEBT, K. fAIAA 78-813] A78-32367 Investigation to support phase 1 of the OSAF GBABDE, D. L. midair prevention systems program (HAPS) Study of advanced composite structural design [AD-A049743] N78-21066 concepts for an arrow wing supersonic cruise BAVILABD. J. K. configuration Unsteady loads due to propulsive lift [NfSA-CB-2825] N78-20116 configurations. Part A: Investigation of GBABHOLfl, E. scaling laws a APL radiometer wind tunnel test program with [HASA-CB-156120] N78-20067 simulated aircraft radome Unsteady loads due to propulsive lift rBSP-1230] 178-21402 configurations. Part C: Development of experimental techniques for investigation of unsteady pressures behind a cold model jet [NASA-CF-156122] N78-20069

B-6 PBBSOBAL AOTBOB IBDEI IL»H, D.

Unsteady loads doe to propulsive lift HODGE, B. 3. con figurations. part D: The development of an Profile of the airport-development crisis experimental facility for the investigation of A78-302B9 scaling effects on propulsive lift configurations BODGES, D. B. fNASA-CB-156123] U78-20070 f theoretical technique for analyzing aeroelastic BAYAS8I, C. stability of bearingless rotors Psychological Assessment of Aircraft noise Index [AIAA 78-503] A78-29805 S78-32058 HOFFBAH, 3. B. HAY4SBI, B. H. Evaluation of windshield materials subjected to Hickel/cadmium aircraft batteries: Battery alarm simulated supersonic flight unit [AD-AOU9981] N78-21101 [AD-A039521] N78-20631 BOFPHAB1, E. Fickel/cadmiua aircraft batteries: Bapid Hodern wing technology for general aviation aircraft electrolyte exchange technigue [BHFT-FB-W-77-1U] H78-20127 [AD-A039335] H78-20632 HOFFBA1H, H.-E. Hidkel/cadmium aircraft batteries: Single sensor Some test results concerning visibility of temperature monitoring obstacle and hazard beacons [AD-A037722] N78-20635 A78-29907 HIT«OOD, S. S., as. BOFPBiBB, i. F. A rotor-mounted digital instrumentation system for The Boeing Aerodynamic Labs data system helicopter blade flight research measurements [AIAA 78-789] A78-32316 [NASA-TP-11H6] N78-20128 BOFB, J. HECHLBB, B. Hethods of reducing aircraft noise Proposal and construction of a hybrid flight-sight A78-30355 simulator with large picture projection BOLDEBBT, G. B. [DGLB PAPEB 77-0871 A78-319U5 Pressure cycling fatigue tests of P-111 crew BELLES, P. P. module glass transparencies Flying over the exclusive economic zone [AD-AO<49625] H78-20119 A78-299U5 BOLLARD, B. J. BEHIECKE, D. K. Project optimisation of military gas turbines with Hot cascade test results of cooled turbine blades respect to turbine life and their application to actual engine conditions N78-21120 N78-21125 BOLLIDAY, B. 6. BEP9BB. T. P. Concorde noise-induced building vibrations, John Correlation of laser velocimeter measurements over f. Kennedy International Airport a wing with results of two prediction techniques [NASA-TH-78676] N78-20919 [mSA-TP-1168] N78-21U10 BOLHES, B. K. BEBIBAH, B. Concorde noise-induced building vibrations, John Properties of hydraulic servomotor controlled by F. Kennedy International Airport flapper valve or by edge valve [NASA-TH-78676] N78-20919 A78-29587 BOLUS, A. G. Choice of engine design for small transport aircraft 'Chain pooling* model selection as developed for A78-30357 the statistical analysis of a rotor burst BBHLIHG, 8. H. protection experiment Unsteady loads due to propulsive lift A78-29327 configurations. Part D: The development of an HOPPS, B. B. experimental facility for the investigation of Fuel efficiency - Where we are heading in the scaling effects on propulsive lift configurations design of future jet transports [NASA-CB-156123] H78-20070 A78-31307 HERRING, B. L. HBUBY, B. 3. Thermal design for areas of interference heating Flight test results of the Strapflown hexad on actively cooled hypersonic aircraft Inertial Beference Dnit (SIRO). Volume 3: [NASA-CB-2828] N78-20117 Appendices A-G HEWLETT, B. B. [NASA-TH-7322U] N78-20098 A sub-scale turbojet test cell for design BDFFHAR, J. K. evaluations and analytical model validation Subsonic longitudinal and lateral-directional [AD-AOI49862] N78-21166 static aerodynamic characteristics of a general HEYSOS, B. B. research fighter configuration employing a jet TESTPLT: Interactive computer procedure for sheet vortex generator wind-tunnel-data management, retrieval, [NASA-TB-7nOU9] H78-20071 comparison, and plotting Subsonic longitudinal and lateral-directional [HASA-TH-78663] N78-2014II static aerodynamic characteristics for a model HEYSOOD, J. B. with swept back and swept forward wings Nitric oxide formation in gas turbine engines: A [NASA-TH-7U093] H78-20073 theoretical and experimental study Subsonic longitudinal and lateral-directional [SASA-CB-2977] 178-21116 static aerodynamic characteristics for a HICKEY, t. 3. close-coupled wing-canard model in both swept A sub-scale turbojet test cell for design back and swept forward configurations evaluations and analytical model validation [HASA-TH-74092] (178-21019 rAD-AOa9862] N78-21166 HDGGETT, C. HICKS, B. E. Time-dependent fire behavior of aircraft cabin Nitric oxide formation in gas turbine engines: A materials theoretical and experimental study [AD-A050923] N78-2123D [SASA-CB-2977;) N78-21116 BOIRIIK, B. BILD, J. Modern wing technology for general aviation aircraft How to make an airport unattractive to birds [BHFT-FB-H-77-11] S78-20127 A78-29209 BD1PHBIS, B. B. BIHDSOV, »- S. Unsteady loads due to propulsive lift The wind and turbulence measuring system of the configurations. Part B: Pressure and velocity H»E Airborne V/STOL Simulator measurements in a three dimensional wall jet A78-30850 [NASA-CB-156121] N78-20068 BIBSf, H. Ground radar - Vital tool or luxury A78-31869 HOAD, D. B. ILAR, D. Correlation of laser velocineter measnreaents over Performance of the ARAVi aircraft with wing-tip a wing with results cf two prediction techniques winglets [HASA-TP-1168] S78-21110 A78-30256

B-7 INBS. B. S. PEBSOBAL AOTHOB IBDEI

IRES, 6. S. UI, t. The use of transient testing techniques in the Optimal control theory (OWEB) applied to a Boeing ?C-11 flutter clearance program helicopter in the hover and approach phase [AIAf 78-505] A78-29806 [BASA-CH-152135] 878-21161 IOAHHOO, R. Kill, K. A., IV Crash worthiness of aircraft fuselage structures Unsteady, surface pressure and near-wave hotvire [AIAA 78-177] A78-29785 measurements of a circulation control airfoil IBVOJS, J. [AD-A050025] B78-21061 Inertial smoothing and eitrapolation of ILS beams: KAHH, S. Application to the Airbus A 300 B Further experimental evaluation of the 1178-210711 electrostatic roll sensor at Bach 2.3 and 3.5 ISOGAI, K. [AIAA 78-802] A78-32357 Numerical study of transonic flow over oscillating KiPOOB. S. G. airfoils using the fall potential equation Runway roughness characterization by DOS approach [BASA-TP-1120] S78-21055 A78-30679 IOSHIF, V. P. KiBBABKAB, J. S. Computation of the pressure on the surface of a Bemotely piloted aircraft in the civil environment fuselage with a wing in an ideal fluid A78-30506 A78-29712 K4THIBESAB, K. IV&HOV. V. IA. Stress analysis of typical flaws in aerospace Boundary-layer interaction vith a noneguilibrium structural components using 3-D hybrid two-phase stream on a surface being burned out displacement finite element method in an axisyametnc Laval nozzle [AIAA 78-5133 178-29812 A78-28610 KAVEBIR, A. I. IV&HOV, V. K. Optimization of linear stabilization systems of Analytical design of an automaton for the flight vehicles on the basis of orthogonal filters longitudinal control of an aircraft A78-32270 A78-32262 KEESEE, 3. E. A technique for vorticity measurement in unsteady flow [AIAA 78-801] A78-32356 JACOBS, P. F. KELLEY, 8. 1. Effect of winglets on a first-generation jet Simulator evaluation of a flight-path-angle transport wing. 3: Pressure and spanwise load control system for a transport airplane with distributions for a semispan model at Bach 0.30 direct lift control [BASA-TB-D-8178] N78-20063 [HASA-TP-1116] B78-20139 Effect of winglets on a first-generation jet Besults of a simulator test comparing two display transport wing* 1: Longitudinal aerodynamic concepts for piloted flight-path-angle control characteristics of a semispan model at subsonic [NASA-TB-78692] B78-2110M speeds KE1LT, B. L. [HASA-TH-D-8473] B78-20061 Investigation of a high speed data handling system Effect of wijiglets on a first-generation jet for use with multispectral aircraft scanners transport King. 2: Pressure and spanvise load [BASA-TB-78689] 1178-20181 distributions for a semispan model at high KIBBEE, G. H. subsonic speeds Expansion of flight simulator capability for study [SASA-TB-D-847U] S78-20065 and solution of aircraft directional control Effect of winglets on a first-generation jet problems on runways transport wing. 5: Stability characteristics [NASA-CB-2970] B78-20118 of a full-span wing with a generalized fuselage KISH, J. J. at high subsonic speeds Helicopter freewheel unit design guide [NiSi-TP-1163] N78-20081 [JD-A017559] N78-2012

B-8 FBBSOIAL 4DTBOB IHDBX LOTZ, H.

KOUALSKI, S. LAZZEBETTI, B. Investigation to support phase 1 of the DSAF Calculation of temperature distribution in disks midair prevention systems program (1AES) and cooling flow in a transient state [AD-AOH97H3] N78-21066 N78-21157 KOV1L, L. B. LEBO7, T. On sound transnission into a heavily-damped cylinder Pleasuring techniques in high temperature turbines A78-31019 B78-21151 KOVALEV, I. 8. LEE, 1. Observability criteria for nonlinear dynamic Comparison of measured and calculated helicopter systems subjected to anltiparameter measurements rotor impulsive noise A78-29089 [NASA-TB-78073] B78-20917 KOZLOVSKII, V. I. Acoustical effects of blade tip shape changes on a Weight design and the efficiency of passenger full scale helicopter rotor in a wind tunnel aircraft. Volume 2 - Calculation of the center [NASA-CR-152082] S78-20918 of gravity and moments of inertia of aircraft. LEE, D. Height analysis Airflow and thrust calibration of an F100 engine, A78-3017S S/N P680059, at selected flight conditions KBiH, I. [NASA-TP-1069] S78-21112 Bearing study program LEE, B. E. [RD-A019767] H78-21068 Further experimental evaluation of the KBEPLIH, B.-P. electrostatic roll sensor at Hach 2.3 and 3.5 Hind tunnel model and measuring techniques for the [AIAA 78-802] A78-32357 investigation of three-dimensional turbulent LEE, H. B. boundary layers Correlation study of the DH-18 helicopter blast TAIAA 78-781] A78-323HO test results from the DICE-THBOH event KBOEGEB, B. A. [AD-A050163] B78-20122 Aeroelastic analysis and ground vibration survey LEGBIVES, E. of the NASA, Grumman American Yankee modified Hew computation method of turbine blades film for spin testing cooling efficiency fNASA-CTI-156119] N78-20109 H78-2115Q KBOTKT, J. LBIKACB, K. I. Properties of fuels used in the Czechoslovak A-»F Bine Angel flight usage data, 1976 aircraft industry [AD-A05016U] N78-21100 A78-29588 LEOUG, B. K. KBOSE, B. The energy costs of some noise abatement procedures Investigation on temperature distribution near A78-31313 film cooled airfoils LEVINSEH, I. N78-21127 Bearing study program KBOSE, B. L. [AD-AOU9767] N78-21068 Influence of spin rate on side force of an LEVINSKY, E. S. axisymmetric body Semispan wind tunnel test of a computer-controlled A78-30690 self-optimizing flexible technology wing KDEBI, «. [AI4A 78-786] A78-323IH Investigations of the local heat transfer LEVY, H. coefficient of a convection cooled rotor blade OS Navy examining a wide range of V/STOL concepts N78-21126 A78-29175 KOHLB4H, J. B. LEBIS, B. B. Experimental investigation of effect of jet decay Concorde noise-induced building vibrations, John rate on jet-induced pressures on a flat plate F. Kennedy International Airport [NASA-CE-2979] 1178-21096 [NASA-TS-78676] N78-20919 LIFSBITS, ID. B. Transonic flows past a lift profile 478-28961 LAGABDE, X. LIHDSEY, G. B. Inertial smoothing and extrapolation of ILS beams: Report on aircraft fatigue studies Application to the Airbus A 300 B [AD-AOM9876] N78-21102 N78-2107H LIPIH, 4. V. LAGOSIOK, 6. S. Choice of optimal ellipsoid-surface projection The An-26 aircraft: Construction and use onto a sphere in solving problems of air A78-30273 navigation LAHBIOTTB, J. J. 478-28523 A vectorization of the Jameson-Caughey NYO LID, D. D. transonic swept-wing computer program FLO-22-V1 A lifting surface theory based on an unsteady for the STAB-100 computer linearized transonic flow model [NASA-TB-78665] H78-21050 [AIAA 78-501] A78-29820 LANG, J. D. LLOBET, F. ? technigue for vorticity measurement in unsteady Inertial smoothing and extrapolation of ILS beams: flow Application to the Airbus A 300 B [AIAA 78-801] A78-32356 N78-2107II LUNGE, H.-H. LO, C. F. The HFB 320 airborne simulator of DFV1B as test Tunnel interference assessment by boundary instrument for determining flight characteristics measurements [DGLR PAPEB 77-082] A78-319U1I 478-30689 LAPY6H, V. I. lOCKiOOD, V. E. Normal force of a flat triangular wing in a Effect of leading-edge contour and vertical-tail supersonic flow configuration on the low-speed stability A78-29720 characteristics of a supersonic transport model LABSOH, B. S. having a highly-swept arrow wing Bean velocity, turbulence intensity and turbulence [BASA-TB-78683] 1178-21051 convection velocity measurements for a LOBB. 1. D. convergent nozzle in a free jet wind tunnel A constant aerodynamic parameter testing technique [HASA-CS-29II9] N78-21058 with automatic wind tunnel control LA8RCZECK, 0. [AIAA 78-7811] A78-323U2 The influence of jets of cooling air exhausted LOBD, C. J. from the trailing edges of a supercritical Looking offshore at the airport future turbine cascade on the aerodynamic data 478-302115 N78-211H8 LOTZ, B. Hodern wing technology for general aviation aircraft [BHFT-FB-H-77-1H] N78-20127

B-9 IODIS, J. F. PEBSOHAL ADTBOB IBDEI

LOOTS. J. F. BASEK, 2. Systematic studies of heat transfer and film Influence of structural components of a by-pass cooling effectiveness engine on its flight characteristics N78-211Q6 A78-29582 LOVAT, G. BASLOV, L. A. Aerodynamic fluid-fiber interactions Computation of the pressure on the surface of a [NT-77-CN-1] N78-20060 fuselage with a wing in an ideal fluid 1DCHINI, J. B. A78-29712 Definition of tire properties required for landing HASODA, C. system analysis flicrofractographic fracture analysis of some [NASA-CK-156171] N78-21326 aircraft parts LDDWIG, I. P. A78-28789 Gas path sealing in turbine engines HASZATICS, J. CHASA-TB-73890] N78-21109 APL radiometer wind tunnel test program with LOEHE, I. H. simulated aircraft radome Dynamic/ response of lift fans subject to varying [BSB-U230] H78-21102 backpressure RATASSOV, G. [AIAA PAPEB 78-756] A78-32176 Space optical communications with the Nd:YAG laser LOIDEHS, B. I. A78-30886 Theoretical flow characteristics of inlets for BATHBHY, H. I. tilting-nacelle VTOL aircraft Flight evaluation of the transonic stability and F NASA-TP-1205] 1)78-21111 control characteristics of an airplane incorporating a supercritical wing [BASA-TP-1167] N78-201UO M BATTHEtS, B. K. HACKIHTOSB, G. B. Supersonic aerothermal testing - A new requirement Thrust computing system applications to increase [AIAA 78-773] A78-32333 engine life and provide fuel conservation BATZ, B. J. A78-31311 Ejector-powered engine simulators for small-scale HAIEB, A. wind tunnel models of high performance aircraft Hind tunnel model and measuring techniques for the [AIAA 78-826] A78-32388 investigation of three-dimensional turbulent BATES, R. B. boundary layers Concorde noise-induced building vibrations, John [AIAA 78-781] A78-323UO F. Kennedy International Airport BALCOLB, G. N. [NASA-TB-78676] N78-20919 New rotation-balance apparatus for measuring BCADAS, P. A. airplane spin aerodynamics in the wind tunnel Joint ASD/AFHAL Combined Environment Reliability [AIAA 78-835] 478-32386 Test /CERT/ Evaluation Program HALLOCK, J. F. A78-32118 A fail-safe analysis of a spanwise wing-panel splice HCCLODD, J. I., Ill [AIAA 78-487] A78-29790 A note on multicyclic control by swashplate HAHATT, S. A. oscillation Design, fabrication, and testing of a full-scale [NASA-TB-78«75] N78-21159 breadboard in nitrogen generator for fuel tank BCCOLGAH, C. J. inerting application Bean velocity, turbulence intensity and turbulence fAD-A049159] N78-21097 convection velocity measurements for a BABIBS, t. C. convergent nozzle in a free jet wind tunnel Use of HS LX1600A as a short-range altimeter [NASA-CH-29U91 N78-21058 A78-28880 BCDOBEL, J. D. BAHFE, J. A. Effects of film injection on performance of a Development of systems and techniques for landing cooled turbine an aircraft using onboard television N78-211U7 TNASA-TP-1171] 178-2011U BCKIHL1Y, R. B. H15KE, J. «. Navigation, guidance and control for high '. critical evaluation of the predictions of the performance military aircraft NASA-Lockheed multielement airfoil computer N78-21090 program BCKIBHEY, L. H. [NASA-CR-1115322] N78-20076 Status and operational characteristics of the - An improved version of the NASA-Lockheed National Transonic Facility multielement airfoil analysis couputer program [AISA 78-770] A78-32331 [HASA-CR-1145323] N78-20077 BCBANUS, E. L. BABJANEK, F. Heavy lift helicopter flight control system. Measuring noise in aircraft cabins Volume 2: Primary flight control system A78-30353 development and feasibility demonstration BABQOIHA SAHCBEZ, L. [AD-AOt9580] N78-21163 t method of calculating ILS approach surfaces BCBEHARIR, J. J., JB. A78-29207 A life cycle cost study of contractor versus HABTIH, B. D. organic support of aircraft progra&s Analysis and comparison of several methods for [ AD-AOa9it38] N78-21015 computing aerodynamic compressibility and SCBOEB, D. interference effects up to critical Bach numbers New trends and problem areas in automatic flight [AD-A050267] B78-20083 control RABTIN, P. S. A78-30252 Analysis and comparison of several methods for BEAD, S. I. computing aerodynamic compressibility and An economic analysis of a government sponsored, interference effects up to critical Bach numbers commercial convertible aircraft [AD-A050267] S78-20083 [AD-A017633] N78-20096 RABTOBANO, L. BEDGYESI-BITSCBANG, L. B. High temperature H2-Air variable geometry HF radiation characteristics of the BH-53D combustor and turbine: Test facility and helicopter and the Bark 105 ABCB system measurements [AD-AOa9795] N78-21358 N78-21137 REDVEDETA, R. A. HABYSIAK, J. Fuel pressure increase limiter The effect of a parachute on the motion of an [AD-A019393] N78-21117 axisyrametric object dropped from an aircraft BEIEB, B. 0. A78-31811 Hind tunnel model and measuring techniques for the investigation of three-dimensional turbulent boundary layers [AIAA 78-781] A78-32340

B-10 PEBSOHAL AOTBOB IHDBX HASSIBPOUB, F.

BEBEDITH, B» D. HOFFITI, I. Pi Investigation of a high speed data handling system Effect of cooling-hole geometry on aerodynamic for ose with multispectral aircraft scanners performance of a file-cooled turbine vane tested rBASA-tH-78689] N78-20U81 with cold air in a two-dimensional cascade HEBBITT. B. B. [HASA-TP-1136] R78-20080 fir traffic control and energy conservation in air BOBTOTA, L. C. operations Effect of winglets on a first-generation jet A78-3131M transport wing. 3: Pressure and spanwise load BEIEBS, J. 1. distributions for a semispan model at nach 0.30 Correlation of laser velocioeter measurements over [HASA-TB-D-81478] N78-20063 a wing with results cf two prediction techniques Effect of winglets on a first-generation jet [NASA-TP-1168] N78-21010 transport wing. 1: Longitudinal aerodynamic HIAO, 8. characteristics of a semispan model at subsonic Beanngless tail rotor loads and stability speeds [AD-AO«95791 H78-21098 [BASA-TB-D-8»73] N78-2006« BICHABLS, I. P. Effect of winglets on a first-generation jet (lore public consultation on airport plans transport wing. 2: Pressure and spanwise load A78-29208 distributions for a semispan model at high BICBALEBICZ, K. subsonic speeds The effect of a parachute on the motion of an [BASA-TB-D-8M71] S78-20065 axisymnetric object dropped from an aircraft HOBABSKI, J. A78-31811 Systematic analysis of safety in aviation. II niCHABD. t. J. A78-29671 Neasuring techniques in high temperature turbines SOBEL10, S. A. N78-21151 Terminal-area flight experience with the NASA niCHEl, B. Terminal Configured Vehicle The induction driven tunnel T2 at ONEBA-CERT - A78-31972 Flow qualities, testing techniques and examples HOB6H, B. 3. of results An economic analysis of a government sponsored, [AIAA 78-7671 A78-32328 commercial convertible aircraft HIGHOSI, 1. [AD-A007633] B78-20096 The induction driven tunnel T2 at OBERA-CEET - BOBISSET, J. Flow qualities, testing techniques and examples Hirage 2000 of results A78-31755 [AIAA 78-767] A78-32328 BORBIS, C. E. K., JB. HIKHAIL, E. H. Theoretical analysis of aerodynamic Geometric restitution of single coverage aircraft characteristics of two helicopter rotor airfoils multispectral scanner data [KASA-TB-78680] 878-20075 A78-29851 BOBBIS, B. E. BIKBAIL. B. H. Aircraft fuel economy - The propulsion system Optimum design of wind tunnel contractions contribution [AIAA 78-819] A78-32373 A78-31309 HIFCDS, T. BOBBIS, B. B. Nitric oxide formation in gas turbine engines: A Experimental evaluation of a transpiration cooled theoretical and experimental study nozzle guide vane [NASA-CH-29771 N78-21116 H78-21131 HILLEB, C. G. EOBTOH, J. B. P critical examination of expansion tunnel Onsteady loads due to propulsive lift performance configurations. Part A: Investigation of [AIAA 78-768] A78-32329 scaling laws HILLEB, G. [NASA-CB-156120] N78-20067 The use of fluidized beds for heating air for wind Unsteady loads due to propulsive lift tunnels configurations. Part B: Pressure and velocity [&IAS 78-818] A78-32372 measurements in a three dimensional vail jet BILLEB, 8. T. [NASA-CR-156121] N78-20068 Concorde noise-induced building vibrations, John BDELLEB, J. f. Kennedy International Airport Control of aircraft turbine engine acceleration [NASA-TH-78676] H78-20919 A78-29583 HILLIGBS. B. H. Use of a stepping motor for measuring fuel The effect of free-stream turbulence upon heat quantity in a digital system for control of transfer to turbine blading rotational speed N78-21155 A78-29586 BIBAILOS, t. B. HDFSEH, B. J. Calculation of supersonic flows past wings with Digital computer program maneuver pilot allowance for trailing tangential S78-319H6 discontinuities within the framework of a model Simulation tests of anti-flak profiles employing a system of Enler equations A78-31951 A78-28958 HDBPBI, B., JB. BISBHET, B. F. Low frequency combustion instability in auqmentors Optimal control of the longitudinal motion of a N78-21138 helicopter on the basis of an operational BDBTBT, i. V. algorithm An intermittent high Reynolds number wind tunnel A78-32272 [AIAA 78-766] A78-32327 HITBOFANOV, A. A. BOSANOV, S. T. Laser and optical methods of monitoring in An analytic study of free molecule flow fields at aircraft construction the front and back edges of a plate 178-30123 A78-28972 HIXSOH, J. s. Investigation of interior noise in a twin-engine light aircraft N A78-296H1 DABDA, V. HOAVEBI. B. K. Interference analysis between TRSB microwave Badio interference in helicopter-borne pulse landing system and adjacent C-band radars Doppler radars [AD-A019882] B78-20101 A78-31038 BASSIBPODB, F. Runway roughness characterization by DOS approach 478-30679

B-11 HA00IE, D. F. PEBSOBAL 10TBOB IBDEI

BAQGIE, D. F. PJLKO, B. L. Air quality impact of aircraft at ten O.S. Air A constant aerodynamic parameter testing technique Force bases with automatic wind tunnel control A78-32222 [AIAA 78-784] A78-32342 HAZABETB. J. B. Semispan wind tunnel test of a computer-controlled STOL system fuel savings - Ground and air self-optimizing flexible technology wing A78-31312 [AIAA 78-786] A78-32344 HELBS, B. P. PAHOHZIO, S. Remotely piloted aircraft in the civil environment The use of fluidized beds for heating air for wind A78-30506 tunnels RELSOH, J. B. [AIAA 78-818] A78-32372 Life-cycle analysis of aircraft turbine engines PAPADALES, B. S., JB. [AD-A050349] N78-20135 Effect of turbulent jet mixing on the static lift HETZBB, D. B. performance of a power augmented ram wing A sub-scale turbojet test cell for design [AD-A049620] B78-21060 evaluations and analytical model validation PABK, C.-B. [AD-A049862] H78-21166 Tandem-queue algorithm for airport user flows HEDBECKEB, A. A78-30677 Simulation tests of anti-flak profiles PABKEB, B. J. A78-31951 Rolling-element fatigue life of AISI B-50 and HEOLIBB, B. I. 18-4-1 balls Estimating tines to early failures asing finite [SASA-TP-1202] H78-21473 data to estimate the Beibnll scale parameter PEITZBAH, F. I. [AD-A050263] N78-20524 Determination of high attitude wall corrections in BBOSTOPi, F. a low speed wind tunnel Bain characteristics of the ADT 4000-4100 digital [AIAA 78-810] A78-3236H computer for a hybrid computing system PELPOB, D. S. A78-29589 Gyroscopic instruments of orientation and HEBTOB, B. stabilization systems Some lessons learned from aircraft accidents - The A78-29859 engineering aspects PESTIDKHOV, V. I. A78-29936 Aircraft takeoff from dirt airstrips HICKS, 0. B. A78-32273 Status and operational characteristics of the PERSOS, L. H., JB. National Transonic Facility Terminal-area flight experience with the RASA fAIAA 78-7701 A78-32331 Terminal Configured Vehicle HICK OH, J. D. A78-31972 Stand-alone development system using a KIH-1 PETEBSOB. C. B. microcomputer module A computer-controlled video instrumentation [NASA-CR-156067] B78-20100 technique for wind tunnel testing of full-scale NICOLAS, 3. 3. lifting parachutes Bew computation method of turbine blades film [AIAA 78-785] A78-32343 cooling efficiency PETBIHO, E. 1. N78-21154 Low frequency combustion instability in augmentors HXSHIJIBA, S. B78-21138 Hicrofractographic fracture analysis of some PEOKBB, G. aircraft parts Precise enronte navigation based on ground-derived A78-28789 techniques HOSICB, A. I. B78-21078 lifting force of a plane R-polarized PFAFF, F. electromagnetic wave Hot cascade test results of cooled turbine blades A78-32296 and their application to actual engine conditions B78-21125 PHILLIPS, I. B. Ground distance covered during airborne horizontal OBEBTI, A. deceleration of an airplane Improved energy efficiency for small CTOL [BASA-TP-1157] B78-20115 transport aircraft PICKEl, F. E. A78-31305 A multi-sensor implementation for navigation, OLSEB, N. L. position location, position update, The use of transient testing techniques in the reconnaissance, and weapon delivery: Boeing YC-1U. flutter clearance program AH/ABH-101 (V) [AIAA 78-505] A78-29806 H78-21082 OBABOHEY, B. PIBB, J. B. On the calculation of the incompressible flow past Experimental investigation of composite wing failure an aerofoil with a jet flap [AIAA 78-509] A78-29809 A78-31838 PIBCKBEI, S. Z. O8LICK, S. C. Rectangular capture area to circular combustor 'irport/community environmental planning scram^et engine A78-30678 [SASA-TB-78657] 878-21107 OSOKIH, ID. A. PITTS, J. I. Gyroscopic instruments of orientation and A vectorization of the Jameson-Caughey SIB stabilization systems transonic swept-wing computer program FLO-22-V1 A78-29859 for the STAB-100 computer O0STEEHODT, D. S. [BASA-TB-78665] B78-21050 Experimental investigation of effect of jet decay PLATZOBDER, L. rate on jet-induced pressures on a flat plate Digital computer program maneuver pilot [NASA-CB-2979] N78-21096 A78-31946 PLESS, B. B. Acoustic emission detection of fatigue crack growth in a production-size aircraft wing test P&LAZOTTO, A. H. article under simulated flight loads Cutout reinforcement of stiffened cylindrical shells A78-31733 [AIAA 78-512] A78-29811 PLOBETEB, p. PALFBEEBAB, B. 3. Development of a binary frequency synthesis as Aircraft fuel economy - The propulsion system control element for frequency correction in contribution time-synchronous collision systems without A78-31309 onboard atomic frequency standard avoidance B78-20106

B-12 PEBSOHAL AUTBOB IHDBI ETZHOV, O. S.

Design of a collision avoidance system model vith Botorcraft linear sioulation model. Volume 2: statistical interrogation Computer implementation N78-20107 CRASA-CR-152079-VOL-2] B78-20137 POGUST, F. B. Rotorcraft linear simulation model. Volume 3: User's manual Microwave landing systeis [NASA-CB-152079-VOL-3] 078-20138 478-29221 BEICB, B. Shither HLS Integrated Doppler/TACAB navigation through A78-30096 conformity with the least squares method - POLASEK. J. Analysis from registered flight data Airfoil profile in a nonnnifon flov A78-29906 [NASA-TB-75272] H78-2101I8 BEIO, L. D. POPGOSHEV, D. Research on various aspects of atmospheric flight Effectiveness of the real time ferrograph and [AD-A033681] H78-20088 other oil monitors as related to oil filtration HEVELL, 0. D. [AD-A049330] H78-2013U Fuel conservation merits of advanced turboprop POOILLOT, H. transport aircraft Mixed ventilated foils [HASA-CR-152096] B78-21095 478-31127 BEIROLDS, P. A. POOPABD, B. Flight simulation - A vital and expanding Fault tolerant flight controls technology in aircraft development A78-28900 [AIAA PAPER 78-337] A78-29295 PBBSLET, L. L. BICE, B. The shock tube as a device for testing transonic A study of low-cost reliable actuators for light airfoils at high Reynolds numbers aircraft. Part A: Chapters 1-8 [AIAA 78-769] A78-32330 [RASA-CR-156112] 1178-20110 PBICE, J. L. A study of low-cost reliable actuators for light Trends of future turbine life prediction: Time aircraft. Part B: Appendices phase automated analysis and test verification [HASA-CR-1561H3] N78-20111 H78-211U3 BICBABDS, B. B. FROST, H. I., JR. The measurement of film cooling effectiveness on Two-dimensional cold-air cascade study of a turbine components in short duration wind tunnels film-cooled turbine stator blade. M: B78-21152 Comparison of experimental and analytical BICHABDSOB, D. aerodynamic results for blade with 12 rows of Fire power 0.076-centimeter-(0.030-inch-) diameter holes A78-3T425 having streamwise ejection angles BICBABDSOB, D. J. [NASA-TP-1151] N78-20130 AB-^S high-survivable transmission system Two-dimensional cold-air cascade study of a [AD-SOM7558] B78-20123 film-cooled turbine stator blade. 5- BICHABDSOH, D. B. Comparison of experimental and analytical Area navigation systems and procedures aerodynamic results for blade with 12 rows of 1178-21091 0.038-centimeter-(0.015 inch) diameter coolant BODGEBS, C. holes having streamwise ejection angles The neit generation E(J system - ASPJ [HASA-TP-1205] N78-20133 A78-31700 POBVIS. J. BODBIGDEZ, J. B. Analysis and comparison of several methods for Airflow and thrust calibration of an F100 engine, computing aerodynamic compressibility and S/N P680059, at selected flight conditions interference effects up to critical lach numbers [BJSA-TP-1069] B78-21112 [AD-A050267] H78-20083 ROSFJOBD, T. J. Catalytic flame stabilization for aircraft afterburners Q A78-31955 QOEBABD, C. BOSS, B. The induction driven tunnel T2 at OSERA-CERT - Space optical communications with the Nd:TAG laser Plow qualities, testing techniques and examples A78-30886 of results ROUSSEAU, D. G. [AIAA 78-767] A78-32328 Analysis of empirically determined aerodynamic and ram coefficients for a power-augmented-ram wing-in-ground effect R [AD-AOU9636] B78-20087 BAE, S. B., JR. BODIOK, A. Low-speed test limit of V/STO1 model located Aircraft and helicopter cockpit noise vertically off-center A78-29673 A78 296Q2 BUPAB, C. B. BAIHBIBD, 1. 3. Aviation fuels - A supplier's perspective Optimum design of wind tunnel contractions A78-31308 fAIAA 78-819] A78 32373 BUSRAK, J. F. BAKBTEEHKO, E. B. Low frequency combustion instability in augmentors Gyroscopic instruments of orientation and B78-21138 stabilization systems BUSSELL, F. L. A78-29859 Low frequency combustion instability in augmentors BABACBANDBA, S. B. H78-21138 Hulti-variate optimization problems of flight BOZEK, J. vehicle synthesis Choice of engine design for small transport aircraft [PB-276123/7] H78-21103 A78-30357 BABSATBB, K. BICBKOT, A. D. Integrated Doppler/TACJH navigation through Boundary-layer interaction with a nonequilibrium conformity with the least squares method - two-phase stream on a surface being burned out Analysis from registered flight data in an axisymmetric Laval nozzle 478-29906 A78-28610 BAO, G. V. B. BTZBOV, A. A. Use of leaning vanes in a two stage fan Fuel pressure increase limiter [SASA-CR-15213U] N78-21115 [AD-A019393] H78-21117 BEASEB, J. S. BTZBOV, O. S. Hotorcraft linear simulation model. Volume 1: Transonic flows past a lift profile Engineering docunentation A78-28961 [NASA-CR-152079-VOI-1] H78-20136

B-13 S&CBS, G. PEBSOHAL AOTHOB IHDEI

SHAH, 3. C. Benefits of strapdown over gimbal INS systems for aircraft application SACHS, G. J78-30253 Optimum tail plane design for artificially SHEISIS, V. B. stabilized aircraft Height design and the efficiency of passenger A78-29331 aircraft. Volume 2 - Calculation of the center SAFBOBOV, V. I. of gravity and moments of inertia of aircraft. Theory of bending-torsional self-oscillations of Weight analysis an aircraft wing system A78-30175 A78-32261 SBESTOPiLOV, V. P. SAIKI, D. H. Lifting force of a plane H-polanzed Rotorcraft linear simulation model. Volume 2: electromagnetic wave Computer implementation A78-32296 [NASA-CB-152079-VOL-2] N78-20137 SHEVE1EV, A. 5. SANDAUEB, J. Quality assurance in the fabrication of products Theory of dolphin-style sailplane flight and the in aviation technology principles of dynamic flight. II A78-32267 A78-29672 SBIBODAIBA, B. SAHDEBS, T. B. Hicrofractographic fracture analysis of some Heavy lift helicopter flight control system. aircraft parts Volume 2: Primary flight control system A78-28789 development and feasibility demonstration SHIRDO, S. [AD-A019580] H78-21163 low-speed test limit of V/ST01 model located SABIA1, B. vertically off-center Erosion prevention and film cooling on vanes A78-29612 N78-21128 SHIPLET, B. G. SAHFOBD, B. I. Fiber Optics Cost Analysis Program (FOCAP) Use of Ns 1X1600A as a short-range altimeter [AD-A019859] N78-21105 A78-28880 SHKVAB, A. IA. SAIEHA, I. S. Investigation of the flow in a plane diffuser by An experimental investigation of oscillating flows means of a laser Doppler anemometer over an airfoil A78-28969 1178-20058 SHOVLIH, B. D. SCHOELLEB, H. Effect of high lift flap systems on the conceptual Integrated Doppler/TACAH navigation through design of a 1985 short-haul commercial STO1 tilt conformity with the least squares method - rotor transport Analysis from registered flight data tSASA-TH-78171] N78-21091 A78-29906 SIEGEL, 8. H. SCHBOEDEB, J. C. Experimental and finite element investigation of Dnsteady loads due to propulsive lift the buckling characteristics of a beaded skin configurations. Part C: Development of panel for a hypersonic aircraft experimental technigues for investigation of [NASA-CR-111863] S78-2053I1 unsteady pressures behind a cold model jet SIBBBZ, B. F. ' rNASA-CB-156122] 1178-20069 Alloy needs and design - The airfrane SCHBOEBS, 1. G. A78-30856 A simple method for estimating minimum SISCLAIB, B. autorotative descent rate of single rotor The wind and turbulence measuring system of the helicopters NAE Airborne V/STOI Simulator [NASA-TB-78U52] 178-20113 A78-30850 SCHBOTT, A. SIBAZETDIHOV, T. K. Special problems in the determination of the The problem of choosing design parameters for radiation characteristics of antennas on unpiloted flight-vehicles aircraft and satellites with the aid of A78-32258 geometric diffraction theory Analytical design of an automaton for the A78-31582 longitudinal control of an aircraft SEDGSICK, G. A78-32262 Evaluation of a ceramic combustion chamber for a SLEEPEB, B. K. small gas turbine engine Summary of NASA landing gear research 1178-21115 [NJSA-TB-78679] S78-20050 SEJHOST, D. SLOBODKIHA, F. A. lethods and equipment for testing for acoustic Stability of subsonic gasdynamic flows fatigue A78-28959 A78-30351I SHED1EI, B. D., JB. SEIZES, H. An evaluation of the bird/aircraft strike hazard, node of operation and characteristics of Darrieus Halmstrom AFB, Montana rotors [AD-A019637] H78-20095 478-28560 SHITH, B. G. SEPP, F. Aviation fuel usage - Economy and conservation The Dual-Flight-Simulator on the evaluation of air A78-30698 combat effectiveness SniTH, F. T. [DGIB PAPEB 77-080] A78-31918 On the calculation of the incompressible flow past SFOBZA, P. H. an aerofoil with a ]et flap ?n experimental facility for wind engineering A78-31838 research SBITH, G. D. [AIAA 78-813] A78-32367 Ejector-powered engine simulators for small-scale SHJHIH, B. T. wind tunnel models of high performance aircraft Development of a pavement maintenance system. [AIAA 78-826] A78-32388 Volume 1: Airfield pavement condition rating SHITH, J. W. [JD-A018881] N78-20117 Besults from flight and simulator studies of a Development of a pavement maintenance management Hach 3 crnise longitudinal autopilot system. Volume 2: Airfield pavement distress [SASA-TP-1180] S78-21160 identification manual SBITB, t. B. [AD-A019029] H78-21170 low-speed aerodynamic characteristics from SHABPE, 1. e. wind-tunnel tests of a large-scale advanced A UD approach control using VOB/DBE/ILS guidance arrow-wing supersonic-cruise transport concept N78-21083 [KASA-CB-115280] 1178-21053

B-11 PEBSOHAL ADIBOB IHDEI TOLLIS, B. B.

SHITH, B. STOLLEBT, J. I. I review of methodologies and concepts to measure An intermittent high Reynolds number wind tunnel and evaluate aircraft survivability/vulnerability [AIAA 78-766] A78-32327 [AD-A050152] S78-21099 STOBE, J. E. SBITH. B. E. Thermal design for areas of interference heating A vectonzation of the Jameson-Caughey HID on actively cooled hypersonic aircraft transonic swept-wing computer program FLO-22-V1 [BASA-CR-2828] 878-20117 for the ST8H-100 computer STOBEBOCEEB, B. B. [8ASA-TH-78665] H78-21050 Flight tests of digital data transmission SBITBEY, B. J. H. A78-31050 Effect of turbulent jet nixing on the static lift STO&BT-HITCBE1I, B. H. performance of a power augmented ram wing Heat transfer characteristics of the closed [AD-A019620] N78-21060 theraosyphon system SHOLICZ, T. H78-21132 Systematic analysis of safety in aviation. II STDBBS, S. B. A78-29671I Summary of NASA landing gear research SHTSL07, V. I. [KASA-TH-78679] H78-20050 Automatic sustainment of resonance conditions in SOLC, J. the multipoint excitation of flight-vehicle Aircraft noise and its sources vibrations A78-30351 A78-32268 SOLLIVAB, B. SOLTES, 1. S. Investigation to support phase 1 of the OSAF A review of methodologies and concepts to measure midair prevention systems program (MPPS) and evaluate aircraft survivability/vulnerability [AD-A0197U3] N78-21066 [AD-A050152] H78-21099 SUBDABABAJAB, B. SPESCEB, F. A. Sensitivity reduction in aircraft control systems Factors affecting the retirement of commercial A78-310314 transport jet aircraft SVOBODA, B. [SASA-CR-152115] N78-21092 Determining the reliability requirements of SPIETH, H. aircraft engine control systems during design Fire resistivity and toxicity studies of candidate stage aircraft passenger seat materials A78-29590 [8ASA-TH-78168] N78-21211 SBAHI, H. S. SBEEBATH, G. S. Bodel support system interference on zero-lift Model support system interference on zero-lift drag at transonic speeds drag at transonic speeds [AIAA 78-809] A78-32363 [AIAA 78-809] A78-32363 SRABSOB, 3. A. STABE, B. 6. Factors affecting the retirement of commercial Effect of cooling-hole geometry on aerodynamic transport jet aircraft performance of a film-cooled turbine vane tested [NASA-CB-152115] S78-21092 with cold air in a two-dimensional cascade [NASA-TP-1136] 878-20080 STABDDLIB, W. Hodern wing technology for general aviation aircraft IA1BOT, P. D. [BHFT-FB-W-77-11] N78-20127 A simple method for estimating minimum STAINBiCK, P. C. autorotative descent rate of single rotor A new technique for reducing test section noise in helicopters supersonic wind tunnels [HASA-TM-78152] N78-20113 [AIAA 78-817] 478-32371 TEICBBAN, H. STAPIES, K. J. Crashworthiness of aircraft fuselage structures Current problems of flight simulators for research [AIAA 78-177] A78-29785 A78-29211 TEHHYSOH, B. C. STABSBS, J. B., JB. Crashworthiness of aircraft fuselage structures Preliminary design of composite wings for [AIAA 78-177] A78-29785 buckling, strength and displacement constraints TBEBEBGE, B. [AIAA 78-466] A78-29777 The impact of a proposed active BCAS on 4TCRBS STASI, B. performance in the Washington, D. C., 1981 An experimental facility for wind engineering environment research [AD-A018589/6] N78-20099 [AIAA 78-813] A78-32367 THIBESEB, 3. STAOFFEB, ». A. Sweden's latest- and last Future trends in aircraft structural design and A78-31868 materials TIBOFEEV, A. P. [AIAA 78-1165] A78-29822 Optimization of the structure of a multibulkhead STBIH. V. large-aspect-ratio wing Special problems in the determination of the A78-32275 radiation characteristics of antennas on TODD, B. aircraft and satellites with the aid of Practical solutions to the cooling of combustors geometric diffraction theory operating at high temperatures A78-31582 N78-21135 STEIHBEBG, B. A. TOPLIS, A. F. Alloy needs and design - The airframe STOI system fuel savings - Ground and air 478-30856 A78-31312 STEPABEHKO, A. F. TBABOLD, E. Effect of boundary layer suction through slits on Fire resistivity and toxicity studies of candidate the efficiency of tnrbomachine outlet diffusors aircraft passenger seat materials A78-30572 [NASA-TH-78168] 878-21211 STEPBBHS, D. G. TBiB, C. T. Concorde noise-induced building vibrations, John Dynamic stability of a two blade rotor F. Kennedy International Airport A78-32037 [NASA-TH-78676] N78-20919 TBIBBBB, L. I. STBVBBSOB, J. B. Supersonic aerothermal testing - A new requirement An engine nozzle vibration phenomenon encountered [AIAA 78-773] A78-32333 in B-1 flight tests TOLLIS, B. B. A78-32129 Fuel conservation merits of advanced turboprop STOCKHAB, B. 0. transport aircraft Theoretical flow characteristics of inlets for [BASA-CB-152096] H78-21095 tilting-nacelle VT01 aircraft [1ASA-TP-1205] 1)78-21111

B-1S TORRES, H. J. PEESOHAL AOTHOB IHDEX

TOBREB, H. J. IELLEB, B. B. Study of advanced composite structural design Comparison of aerodynamic data measured in air and concepts for an arrow wing supersonic croise Freon-12 wind-tunnel test mediums configuration [NASA-TB-78671K H78-21052 [NASA-CB-2825] S78-20116 BELSH, C. 3. TOTTLE, D. B. The AEDC Bange K facility for erosion testing Landing systems - The Navy viewpoint [AIAA 78-775] A78-32334 A78-30097 BEHTBE, V. TILBB, J. S. The Daal-Flight-Simulator as an aid for a Urea navigation systems and procedures government mission specialist K78-21091 CDGIR PAPER 77-079] S78-31949 TY.ZHEB, K. BESOKY, H. 1. Effect of noise on life of aircraft structore and Simulated flight effects on noise characteristics design of parts resistant to acoustic loads of a fan inlet with high throat Hach number 478-30352 [NASA-TP-1199] N78-20132 BETZEL, 3. K. A review of methodologies and concepts to measure u and evaluate aircraft survivability/vulnerability OHDEBBOOD, P. R. [AD-A050152] N78-21099 Low frequency combustion instability in augmentors BHITE, E. A. N78-21138 Project optimisation of military gas turbines with OHDEBBOOD, J. respect to turbine life Investigation to support phase 1 of the USiF R78-21120 midair prevention systems program (HAPS) BHITEBBAD, A. B., JR. [AD-A0097«3] H78-21066 Technical and economic evaluation of advanced air OUTERREIHEB, K.-B. cargo systems Ose of and experience with simulation in the [NASA-TH-78672] N78-20108 development of the VFB 6114 and the VAK 191 RBITEIAI, J. B. [DGLB PAPER 77-083] A78-31912 Engineering calculation methods for turbulent OSEITOR, B. L. flow, volume 1 Sting effects as determined by the measurement of [IC-AEBO-77-102-70L-1] N78-20091 pitch-damping derivatives and base pressures at Engineering calculation methods for turbulent Hach number 3 flow, volume 2 [AIAA 78-830] A78-32381 CIC-AEBO-77-102-VOL-2] B78-20092 Engineering calculation methods for turbulent flow, volume 3 [IC-AERO-77-102-70L-3] 1178-20093 VAGUER, E. f. BIGG, L. D. Laser and optical methods of monitoring in Experimental evaluation of a transpiration cooled aircraft construction nozzle guide vane A78-30123 H78-21131 VAICAITIS, B. BILLIiHS. H. L. Investigation of interior noise in a twin-engine A rotor-mounted digital instrumentation system for light aircraft helicopter blade flight research measurements A78-296U1 [NASA-TP-11U6] N78-20128 VALORI, B. BILLIS, E. A. Effectiveness of the real time ferrograph and General aviation energy-conservation research other oil monitors as related to oil filtration programs at NASA-Lewis Research Center [AD-A019334] N78-20131 A78-29330 VIDAL, B. J. WILLBABTR, B. B. Experiments on supercritical flows in a APL radiometer wind tunnel test program with self-correcting wind tunnel simulated aircraft radome A78-323U5 [BSR-U230] H78-21U02 VI1DGBOBE, 1. S. RILLSKI, A. S. Helicopters: Calculation of integral aerodynamic Reliable dual-redundant sensor failure detection performance and air-technical data and identification for the NASA F-8 DFBW aircraft A78-3012U [NASA-CB-291W] N78-20111 VIL1CB07CBERKO, S. D. BILSOH, B. E. Hydrodynamic effect on a contour produced by an The effect of hub fairings on wind turbine rotor ideal incompressible flow of constant vorticity performance A78-28956 A78-30039 VILIE, J. P. BIHCZtJBA, Z. The measurement of film cooling effectiveness on The effect of a parachute on the motion of an turbine components in short duration wind tunnels axisymmetric object dropped from an aircraft H78-21152 A78-31811 VON SCHLACHTA, K. BIHGET, L. On the possibility of classifying radar targets The influence of transpiration cooling on turbine with a coherently measured echo signal blade boundary layer A78-32308 S78-21130 VOBTHEIEB, P. W. WIRTEB, J. Hultiband antenna system for tactical aircraft Practical solutions to the cooling of combnstors [AD-AOU9699] N78-21363 operating at high temperatures N78-21135 BIRTEB, B. B. W Development of systems and techniques for landing BABCDP, B. i. an aircraft using onboard television Experimental investigation of effect of jet decay [NASA-TP-1171] H78-2011U rate on jet-induced pressures on a flat plate BOIF, J. [NASA-CB-2979] H78-21096 Space optical communications with the Nd:7AG laser RABD, D. B. A78-30886 Concorde noise-induced building vibrations, John IOODIABD, 0. H. F. Kennedy International Airport Bearing study program [FASA-TH-78676] H78-20919 [AD-A019767] N78-21068 BASSOS, G. E. ID, S. H. Flight tests of digital data transmission Runway roughness characterization by DDS approach A78-31050 A78-30679

B-16 PEBSOHAL AOTBOB IHDBI ZIFKIB, B. A.

T4TES, B. J. Factors influencing schedule reliability in international operations 478-29213 IEAGEB, ». T., JR. Theoretical analysis of aerodynamic characteristics of two helicopter rotor airfoils [NASA-TH-78680] N78-20075 YOOHG. S. H., JB. Correlation of laser velocimeter measurements over a wing with results of two prediction techniques [FASA-TP-11681 N78-21110

ZAKKAY, T. The use of fluidized beds for heating air for wind tunnels [AIAA 78-818] P78-32372 ZABETSKY. E. V. Rolling-element fatigue life of A1SI H-50 and 18-1-1 tails TlIASA-TP-1202] N78-21t73 ZABIPOV, N. 6. The problem of choosing design parameters for unpiloted flight-vehicles A78-322S8 Optimization of the design parameters of finned pilotless flight vehicles A78-32269 ZABTJBIAN, G. Correlation study of the OH-18 helicopter blast test results from the DICE-THKOS event [AD-A0501I63] N78-20122 ZAOLICHHTI, E. G. Boundary-layer interaction with a aoneguilibrium two-phase strean on a surface being burned out in an azisymmetric Laval nozzle A78-28610 ZELOH, C. C. Fiber Optics Cost Analysis Program (FOCAP) [AD-AOU9859] H78-21105 ZHAEOV, E. A. Automatic sustainment of resonance conditions in the multipoint excitation of flight-vehicle vibrations A78-32268 ZIEGLEB, H. Subsonic longitudinal and lateral-directional static aerodynamic characteristics of a general research fighter configuration employing a jet sheet vortex generator [NASA-TM-7110191 N78-20071 ZIPKIH, B. 1. Evolution of the aircraft gas turbine engine A78-30257

B-17 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 98) JULY 1978

Typical Contract Number Index Listing RAVAIB TASK AD3W-350D/001B 7113-01-13-02 N78-21053 A78-32357 713-01-31-01 H78-20078 NASH-2183 H78-11Q61 HAVSEA TASK SF32-302-H1B 791-UO-11 N78-21091 A78-32357 791-10-11 1178-21092 NA7SEA TASK SF32-399-592 A78-32357 HGL-147-003-039 H78-21096 BGR-22-009-378 Listings in this index are arranged alphanumerically by contract number N78-21116 Under each contract number the accession numbers denoting documents NGR-36-009-017 that have been produced as a result of research done under that contract H78-20100 are arranged in ascending order with the IAA accession numbers appearing NGB-«7-005-208 A78-296U3 first The accession number denotes the number by which the citation is NGB-U7-005-219-03 identified in either the lAAot N78-20067 N78-20068 N78-20069 N78-20070 AF MIPR-FQ8952-76-66005 F-INK-07-21898 NGE-U8-002-035 1178-21170 N78-21062 A78-296112 AF OBDEB P00972 F-INK-11-12-02871 NBC A-9185 A78-29785 A78-31733 N78-21062 NSF ENG-76-03135 AF PBOJ. 6H9E F-IMK-11-12-833U3 A78-32366 N78-20101 N78-21062 NSG-1050 A78-31019 »F PBOJ. 2103 F-INK-82223-76-001-21-001 NSG-1080 N78-21326 178-20118 N78-21062 SSG-1229 N78-20109 AF PBOJ. 7531 F08635-77-C-0002 KSG-1266 A78-29777 A78-31733 N78-20083 NSG-1121 N78-20110 AF-AFOSR-71-2667 F09603-77-A-3101) N78-20111 "78-29812 N78-21066 HSG-21UO N78-21059 AF-AFOSB-2091-71 F19628-76-C-0017 SSG-21«9 N78-21092 N78-20088 078-20101 1SG-2152 A78-32330 AF-AFOSB-3158-77 F33615-73-C-0678 HSG-1006 N78-20531 N78-21162 N78-21099 N00011-72-C-0102 AFOSE-2912-76 F33615-73-C-5066 A78-32315 178-20086 A78-29809 N0001U-76-C-0253 APL/JHO-600276 F33615-75-C-3105 H78-211U6 H78-21102 N78-21101 NOOOU-76-C-071I2 BHFT-LFK-7530 F33615-75-C-52119 A78-323UU N78-20127 A78-31733 N00011-77-C-0052 CTDA-0IS0,18200-6-6519 F33615-76-C-1260 A78-323D5 A78-29785 S78-21105 161331-76-BI1839 D? PBOJ. 1F2-62209-AH-76 F33625-76-C-2018 N78-21358 N78-21098 N78-211U.6 N62269-73-C-0906 DA PEOJ. 1F2-63208-DB-52 F33657-15053 A78-31733 N78-21068 N78-20123 F10600-76-C-0011 N62269-77-C-0138 DA PBOJ. 111-61102-AH-ltS A78-323U5 N78-21363 N78-21110 F«9e20-77-C-0023 199-53-04 N78-2011t DA-ABO(D)-31-121-G111« N78-20135 505-02-21-01 N78-21055 A78-29612 FH9620-77-C-0035 505-OU N79-20080 DA-ERO-75-G-071I N78-20086 N78-20130 t.78-21152 MIPB FQ-8952-76-66005 N78-20133 DAAD05-76-C-0772 N78-201I17 N78-211173 N78-20122 NASW-2791 S78-210U8 505-05 N78-21112 DAAJ01-71-C-08110 NAS1-12287 N78-20112 N78-211111 N78-21163 178-20116 505-06-31 N78-201UO 1178-21161 NAS1-13267 N78-20102 505-06-63-02 N78-20115 DAAJ02-71-C-0028 NAS1-13500 S78-21053 505-08-21 N78-212ia N78-20121 NAS1-1362U N78-21093 505-08-33-12 K78-20050 DAfJ02-75-C-0017 NAS1-1391U N78-20U1 505-09-13-11 N78-20919 N78-21098 NAS1-13981 S78-20118 505-09-33-03 H78-201U2 DA«J02-76-C-0006 NAS1-1I1110 N78-20117 505-10-21 N78-20917 178-20123 NAS1-1U28a 178-2009U H78-21159 DAAJ02-76-C-0007 NAS1-111102 N78-210U7 505-10-23 B78-20113 N78-20120 NAS1-1U522 N78-20076 505-10-23-03 N78-21052 DAAJ02-76-C-0027 178-20077 505-10-23-05 H78-21IHO N78-20121 NAS2-6690 A78-32368 505-10-23-07 N78-20075 DGRST-7U-7-0695 NAS2-7187 N78-21161 N78-20128 N78-20060 NAS2-8612 N78-21095 505-10-31 N78-21115 DOT-FA70BAI-175 NAS2-8680 N78-21115 505-11-13-02 S78-20081 N78-20099 NAS2-8699 178-21223 505-11-16-08 N78-20063 N78-20101 NfS2-87H5 A78-32368 N78-20061 DOT-FA75HA-3658 NAS2-910U A78-31306 N78-20065 N78-21097 NAS2-9155 J78-32368 505-11-22-01 N78-20079 DOT-FA76HAI-610 NAS2-937U H78-20136 505-11-23-13 N78-20071 '178-21231 N78-20137 B78-20072 DOT-OS-50232 A78-30677 N78-20138 510-56-01 H78-21223 E(19-18) -2358 HAS2-9399 N78-20917 512-51-02-03 N78-20113 H78-32367 178-20918 513-52-01-09 N78-21101 EF-76-C-01-2256 NAS3-16732 N78-21147 513-52-13-52 S78-20139 A78-32372 SAS3-17863 N78-70920 513-53-05 N78-20098 r-INK-07-11966/02871 NAS3-17866 178-21058 516-51-01 N78-21160 178-21062 NAS3-20051 N78-21H71 738-01 N78-20132 1AS7-100 A78-31915 7U3-01-13-01 N78-201HH

C-1 1 Report No 2 Government Accession No 3 Recipient's Catalog No NASA SP-7037 (98) 4 Title and Subtitle 5 Report Date AERONAUTICAL ENGINEERING July 1978 A Continuing Bibliography (Supplement 98) 6 Performing Organization Code

7 Author(s) 8 Performing Organization Report No

10 Work Unit No 9 Performing Organization Name and Address

11 Contract or Grant No National Aeronautics and Space Administration Washington, D. C. 205^6 13 Type of Report and Period Covered 12 Sponsoring Agency Name and Address

14 Sponsoring Agency Code

15 Supplementary Notes

16 Abstract

This bibliography lists 399 reports, articles, and other documents introduced into the NASA scientific and technical information system in June 1978.

17 Key Words (Suggested by Author(s)) 18 Distribution Statement Aerodynamics Aeronautical Engineering Aeronaut ics Unclassified - Unlimited B ibliography

19 Security Classif (of this report) 20 Security Classif (of this page) 21 No of Pages 22 Price' Unclass if Jed Unclass if led 120 $4.75 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1978 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organizations listed below Each library it prepared to furnish the public such services as reference assistance, interlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention CALIFORNIA MASSACHUSETTS University of California. Berkeley Massachusetts Institute of Technology. Cambridge COLORADO MISSOURI University of Colorado. Boulder Linda Hall Library. Kansas City DISTRICT OF COLUMBIA NEW YORK Library of Congress Columbia University. New York GEORGIA PENNSYLVANIA Georgia Institute of Technology. Atlanta Carnegie Library of Pittsburgh ILLINOIS WASHINGTON The John Crerar Library. Chicago University of Washington, Seattle

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY

NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP-7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP-7(B9 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques

Details on the'availability of these publications may be obtained from SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. 20546