https://ntrs.nasa.gov/search.jsp?R=19760003906 2020-03-22T19:15:02+00:00Z NASA SP-7037 (61)
AERONAUTICAL ENGINEERING
A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 61
SEPTEMBER 1975
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ACCESSION NUMBER RANGES
Accession numbers cited in this Supplement fall within the following ranges:
STAR (N-10000 Series) N75-23470—N75-25862
IAA (A-10000Series) A75-32381 A75-35876
This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information Systems Company NASA SP-7037 (61)
AERONAUTICAL ENGINEERING
A Special Bibliography
Supplement 61
A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in August 1975 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAAI
Scientific and Technical Information Office SEPTEMBER !975 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D C. This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161,for $400 For copies mailed to addresses outside the United States, add $2 50 per copy for handling and postage INTRODUCTION
Under the terms of an interagency agreement with the Federal Aviation Administra- tion this publication has been prepared by the National Aeronautics and Space Administra- tion 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 sup- plements have been issued This supplement to Aeronautical Engineering—A Special Bibliograph\ (NASA SP-7037) lists 418 reports, journal articles, and other documents originally announced in August 1975 in Scientific and Technical Aerospace Reports ISTAR) or in International Aero\pa>.e 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 aero- nautical 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 or STAR, including the original accession numbers from the respective announcement journals This procedure, which saves time and money, accounts for the slight variation in citation appearances Three indexes—subject, personal author, and contract number—are included An annual cumulative index will be published AVAILABILITY OF CITED PUBLICATIONS
IAA ENTRIES (A75 10OOO Series)
All publications abstracted in this Section are available from the Technical Information Service American Institute of Aeronautics and Astronautics Inc (AIAA). as follows Paper copies are available at $5 00 per document up to a maximum of 20 pages The charge for each additional page is 25 cents Microfiche"1 are available at the rate of SI 50 per microfiche for documents identified by the j symbol following the accession number A number of publications, because of their special characteristics , are available only for reference in the AIAA Technical Information Service Library Minimum airmail postage to foreign countries is $100 Please refer to the accession number, eg (A75-10763). when requesting publications
STAR ENTRIES (N75-10000 Series)
One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation The most commonly indicated sources and their acronyms or abbreviations are listed below If the publication is available from a source other than those listed the publisher and his address will be displayed on the availability line or in combination with the corporate source line
Avail NTIS Sold by the National Technical Information Service to U S customers at the price shown in the citation following the letters HC (hard paper or facsimile copy) Customers outside the U S should add $2 50 per copy for handling and postage charges to the price shown (Prices shown in earlier STAR volumes 1962-1974 have been superseded but may be calculated from the number of pages shown in the citation The price schedule by page count was given in the last STAR issue of 1974 or may be obtained from NTIS) Microfiche'"are available at a standard price of $2 25 (plus $1 50 for non-U S customers) regardless of age for those accessions followed by a ' § symbol Accession numbers followed by a + sign are not available as microfiche because of size or reproducibility Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Unit
NOTE ON ORDERING DOCUMENTS When ordering NASA publications (those followed by the * symbol), use the N accession number NASA patent applications (only the specifications are offered) should be ordered by the US-Patent-Appl-SN number Non-NASA publications (no asterisk) should be ordered by the AD PB or other report number shown on the last line of the citation not by the N accession number It is also advisable to cite the title and other bibliographic identification
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Avail Univ Microfilms Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) at $1000 each and microfilm at $400 each regardless of the length of the manuscript Handling and shipping charges are additional All requests should cite the author and the Order Number as they appear in the citation
Avail USGS Originals of many reports from the U S Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this Introduction The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction
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Avail Issuing Activity, or Corporate Author, or no indication of availability Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document
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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 bibliog- raphy user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies especially NASA A listing of public collections of NASA documents is included on the inside back cover
SUBSCRIPTION AVAILABILITY
This publication is available on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements excluding the annual cumulative index is $18 00 All questions relating to subscriptions should be referred to the NTIS 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 O Box 62 Oak Ridge. Tennessee 37830
U S Geological Survey ESA - Space Documentation Service 1033 General Services Administration Bldg ESRIN Washington, D C 20242 Via Galileo Galilei 00044 Frascati (Rome), Italy
Her Majesty's Stationery Office U S Geological Survey P O Box 569 S E 1 601 E Cedar Avenue London, England Flagstaff Arizona 86002
NASA Scientific and Technical Information U S Geological Survey Facility 345 Middlefield Road PO Box 8757 Menlo Park, California 94025 BWI Airport Maryland 21240 U S Geological Survey National Aeronautics and Space Bldg 25. Denver Federal Center Administration Denver, Colorado 80225 Scientific and Technical Information Office (KSI) Zentralstelle fur Luftfahrtdoku- Washington. D C 20546 mentation und -Information 8 Munchen 86 National Technical Information Service Postfach 880 Springfield. Virginia 22161 Federal Republic of Germany TABLE OF CONTENTS
Page
IAA Entries 323 STAR Entries 353
Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1
TYPICAL CITATION AND ABSTRACT FROM STAR
NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE
ACCESSION NUMBER—-». N75-10OO5*# Lockheed-Georgia Co Marietta -CORPORATE «-GROUND EFFECT FOR V/STOL AIRCRAFT CONFIGURA- SOURCE TIONS AND ITS SIMULATION IN THE WIND TUNNEL PART 3 THE TANQENTIALLY BLOWN GROUND AS AN TITLE • -PUBLICATION ALTERNATIVE TO A MOVING GROUND APPLICATION DATE TO THE NASA-AMES 40 BY 80-FOOT WIND TUNNEL •-J E Hackett E B Praytor and E O Caldwell (1973) ~59 p AVAILABILITY AUTHOR refs SOURCE (Contract NAS2-6690) (NASA-CR-114497) Avail NTIS HC $4 25 CSCL01B-*- CONTRACT- fr A set of conceptual drawings showing the application of COMTI OR GRANT slot-blowing boundary layer control to the 40- by 80-foot wind COOf tunnel is presented In small scale pilot experiments unswept slots were used, fed by a below-floor plenum The model was REPORT- sting mounted and its wing was unswept However design for NUMBER the Ames tunnel was heavily constrained both by under floor balance mechanisms and by a large turntable An over floor supply system was therfore designed A description of appropriate procedures for using the floor tangential blowing system is given Though some of the operating graphs are specific to the design for the Ames tunnel both non-dimensional plots and the approach generally are widely applicable Author TYPICAL CITATION AND ABSTRACT FROM IAA
NASA SPONSORED AVAILABLE ON DOCUMENT ' MICROFICHE
ACCESSION- -A75-10336 * K Sealing technology for aircraft gas turbine TITLE NUMBER engines L P Ludwig and R L Johnson (NASA, Lewis Research Center, Cleveland, Ohio) American Institute of Aeronautics and AUTHORS - Astronautics and Society of Automotive Engineers, Propulsion AUTHORS' Conference, 10th, San Diego, Calif, Oct fi-23. 1974, AIAA Paper AFFILIATION 74-1188 12 p 23 refs Experimental evaluation under simulated engine conditions TITLE OF revealed that conventional mamshaft seals have disadvantages of high - PERIODICAL gas leakage rates and wear An advanced seal concept, the self-acting face seal, has a much lower gas leakage rate and greater pressure and PUBLICATION speed capability In endurance tests (150 hr) to 43,200 rpm the DATE self acting seal wear was not measurable, indicating that noncontact sealing operation was maintained even at this high rotative speed A review of published data revealed that the leakage through gas path seals has a significant effect on thrust specific fuel consumption, stall margin, and engine maintenance Reducing leakages by reducing seal clearances results in rubbing contact, and then the seal thermal response and wear determines the final seal clearances (Author)
VIM AERONAUTICAL ENGINEERING
A Special Bibliography (Suppl 61) SEPTEMBER 1975
A75-32430 Random vortex shedding noise of airfoils S Kotake (Tokyo, University, Tokyo, Japan) Journal of Sound and Vibration, vol 40, May 8, 1975, p 87 99 6 refs The acoustic radiation due to turbulent vortex shedding from a thin airfoil is analyzed by applying thin airfoil theory In terms of the statistical quantities of the wake vorticity that is, the spanwise IAA ENTRIES and chordwise intensities of turbulent vorticities or turbulent circulations per unit length and their space and time correlations the associated acoustic intensity is expressed The latter spectral density distribution can be related to that of the wake vortices through their mertial modification (Author)
A75-32396 Automatic Test System for Jet Engine Acces- sories R Hartwell (RCA, Government Communications and Auto- mated Systems Div, Burlington, Mass) RCA Engineer, vol 20, Apr May 1975, p 30-35 A75-32439 Search for the final period of decay of the The present work describes the design concepts of the Auto axisymmetnc turbulent wake P Freymuth (Colorado, University, matic Test System for Jet Engine Accessories (ATSJEA), a fully Boulder, Colo ) Journal of Fluid Mechanics, vol 68, Apr 29, 1975, automated test facility for a wide range of jet aircraft fuel controls, p 813-829 19 refs pumps, and similar accessories The test stands, in which hydraulic Profiles of mean and fluctuating turbulent velocities and and pneumatic flows and pressures, mechanical rotations, and temperatures, of the time derivative of velocity and of intermittency physical linkages are the principal quantities sensed, are connected have been measured in the wake of an unheated as well as a heated via an elementary operations controller (EOC) to the CPU and sphere in the low Reynolds number range 600-2500 at distances computer peripheral equipment Test programs written in 80-1800 sphere diameters downstream The wind-tunnel experiments FORTRAN IV control, measure, record, sequence, and evaluate exhibit a strong dependence on Reynolds number but they do not individual tests P T H indicate the attainment of or an approach to the final period of turbulent decay which has been explored theoretically by Phillips and by O'Brien The lowest turbulence Reynolds number obtained A75-32397 Automated test facility for aircraft hydraulic was R sub lambda = 1 4 (Author) pumps and motors R Blanchard and L R Hulls (RCA, Government Communications and Automated Systems Div , Burlington, Mass ) RCA Engineer, vol 20, Apr May 1975, p 36 39 A multi-stand test facility is described which automatically tests aircraft hydraulic pumps and motors in their three basic configura- A75 32452 ? On the way to tactical aircraft robotics W B Ballenberger (Sperry Rand Corp, Sperry Flight Systems Div, tions A central hydraulic supply is employed, consisting of an assembly of pumps which share the load in delivering fluid under Phoenix, Ariz ) Astronautics and Aeronautics, vol 13, June 1975, p 28-35 pressure to a common supply manifold, reducing the number of motors, pumps, and heat exchangers The system features pump and A radar control system for the F 102A aircraft is described The starter stands plus combined pump/motor and motor/starter test PQM 102 target system, as it is designated, features a dual redundant stands A computer identified as an elementary operations controller (two sets of radar and controls) mobile ground station, a fixed interfaces the central processor unit to a group of ten test stands ground station, and two fixed ground radar sources The primary Particular consideration has been given to energy conservation in the radar of the mobile ground station has a 50 n mi range and a 2 kW design of the system P T H output, it controls the plane during takeoff and recovery and during close-in missions The aircraft contains a 7 5 Ib rod charge for destruct purposes and a scoring system consisting of four antenna assemblies containing two independent receiving elements, one A7S-32410 Velocity vector The logical solution J E horizontally and the other vertically polarized Applications en Hutchmson Shell Aviation News, no 427, 1975, p 6-10 visioned for the target system include interdiction, surveillance, A description is given of two head up aircraft displays produced reconnaissance, ECM, decoy, defense suppression, and air superior- by Thomson-CSF, the CV-91 visual guidance system and the TC 121 ity SJM all-weather approach and landing monitor The basic information presented to the pilot includes the velocity vector, the potential path, the aircraft symbol, the reference angle of attack, and the flight path Flight evaluations show that in visual approaches, the CV 91 A75-32455 /> B-1 - The road to first flight A B Martin enables any desired glide path angle to be flown precisely without (USAF, Systems Command, Wright Patterson AFB, Ohio) Astro ground-based guidance such as ILS or VASI The TC-121 provides nautics and Aeronautics, vol 13, June 1975, p 56-62 the capability of monitoring an automatic approach and landing, The present article provides insight into the complexity of with the pilot able to take over manually at any point ATS present aircraft weapons systems and demonstrates how extensive
323 A75-32463
'test before fly' must help neutralize the risk associated with this A75-32472 # Transmissivity of light - One of the quantities complexity and insure a successful 'fly before buy' Specifically, the usable in the diagnostics of oil in a motor (Propustnost svetla - Jedna complexity and prefhght testing of the B-1 are reviewed Component z velicin vyuzitelnych pro diagnostiku oleje v motoru) J Krotky materials and structural features of this aircraft were emphasized in Zpravodai VZLU, no 5, 1974, p 17-21 7 refs In Czech the testing process S J M A method is described for measuring the transmissivity of fresh B3V oil and of oil of different degrees of use The relationship A75-32463 Mechanics of composite materials R M Jones between transmissivity and degradation of oil used in a turboprop (Southern Methodist University, Dallas, Tex) Washington, DC, engine is determined It is found that transmissivity is a function of Scnpta Book Co , 1975 367 p 176 refs $21 50 oil loading Measurement of transmissivity can therefore be used as a The classification and the characteristics of composite materials means of determining the state of the oil directly in the engine are considered along with a basic terminology of laminated fiber- PT H reinforced composite materials, the manufacture of laminated fiber-reinforced composite materials, and current and potential A75-32473 ff Identification of systems by means of adaptive advantages of fiber reinforced composite materials Attention is given model (Identifikace systemu pomoci adaptwnihomodelu) J Salaba to the macromechamcal behavior of a lamina, the micromechanical Zpravodai VZLU, no 6, 1974, p 5-14 20 refs In Czech behavior of a lamina, the macromechamcal behavior of a laminate, Methods of identifying systems are reviewed and evaluated, and and the bending, buckling, and vibration of laminated plates Other a method based on the use of adaptive models is then analyzed This topics discussed are related to fatigue, holes in laminates, and aspects method features three variants for coupling the models series, of fracture mechanics G R series-parallel, and parallel Analysis and derivation of identification by means of the adaptive model are given for the case when the set of state variables measured in the system is known Possibilities for A75-32468 ff A method to determine a distribution function application of the method of identification with an adaptive model of main structure failures in an aircraft M Samir Abdelsalam Zprava to a jet engine and its modifications are examined P T H VZLU, Z-23, 1974, p 1-9 6 refs An approach is suggested for determining the structural distri- bution function of main defects in fatigue-tested structures of an A75-32518 // The problem of diffraction of a strong mag- aircraft Only one representative structure is tested, and it is assumed netogasdynamic shock wave by a wedge (Zadacha o difraktsn sil'noi that in the recorded sequence of defects, all defects will manifest the magnitogazodmamicheskoi udarnoi volny okolo khna) L D Azatian same distribution function type, so that the method is actually based (Erevanskn Gosudarstvennyi Universitet, Yerevan, Armenian SSR) on the formalism of a partially parallel system Any quantile of the Aksdemua Nauk Armianskoi SSR, Izvestiia, Mekhanika, vol 27, no distribution function of the mam defects can then be graphically or 5, 1974, p 4762 17 refs In Russian numerically determined The method is tested by solving the The nonuntform flow region is investigated in the problem of distribution function for the first main defect of the Ae 45 aircraft the reflection of a strong magnetogasdynamic shock wave from a frame under fatigue strength testing and comparing the theoretical wedge with an obtuse angle (close to 180 deg) m the presence of a solution with measurement data on the actually determined distri- magnetic field parallel to the incident wave The Smirnov Sobolev bution function P T H method is used to reduce this problem to a boundary problem for the solution of an analytical function characterizing the pressure involved The solution is obtained by the Lighthill method The gas A75-32470 ft Diagnostics of jet aero-engines by means of parameters behind a shock wave incident on the obtuse wedge and spectral analysis of lubricating oil (Diagnostika leteckych reaktivnich behind a plane wave reflected from the wedge are determined, along motoru pomoci spektralni analyzy oleje) P Vacck Zpravodai with the pressure distribution over the wedge wall S D VZLU, no 4, 1974, p 15, 16 5 refs In Czech A method of interpreting the results of spectral analysis of lubricating oil, which is used as one of the principal methods of A75-32527 # Rescue measures in the case of accidents of diagnosis of the condition of aero engines, is described This method the AN-12 aircraft (Spasatel'nye meropmatriia pn avarn samoleta is based on the rate of change of concentration of the products of AN-12) G A Kas'ianov and G M Shereshkov Voenno Meditsmskii wear in lubricating oil, which is proportional to the rate of wear of Zhurnal, Mar 1975, p 5760 In Russian the lubricated parts This method makes it possible to determine the An emergency rescue procedure for accidents involving the critical points in respect to wear and so detect and eventually prevent AN-12 aircraft is described The proposed procedure makes use of failures of aero engines in operation (Author) stretchers, straps, parachute harness, and a special ambulance car The characteristics of each of the available emergency hatches are taken into consideration The evacuation of casualties is discussed m A75-32471 # Statistical analysis of the functioning quality terms of penetration into the aircraft and evacuation of casualties of regulators with random parameter scatter (Prispevek ke statisttcke directly from their posts or out of the aircraft cabins S D analyze jakosti prace regulatoru s nahodnym rozptylem parametru) M T A EI-Mayah Zpravodai VZLU, no 5, 1974, p 5-16 12 refs In Czech The author points out three methods The analytical method is A75-32652 # Response of aircraft structural compartments suitable for a small number of parameters and the simplest forms of to blast pressures and fragments from high explosive proiectiles M J distribution For solving this task the author goes over to a linearized Jacobson, J R Yamane, and J Brass (Northrop Corp , Hawthorne, form of the critenal function and to the simplest distributions The Calif ) A/AA, ASME, and SAE, Structures, Structural Dynamics, second method is combined numerical-analytical, in which the and Materials Conference, 16th, Denver, Colo , May 27-29, 1975, random changes of parameters are simulated numerically, but the A/AA Paper 75-751 8 p 21 refs Research supported by the magnitudes of the criteria are calculated from the known analytical Northrop Corp , Contract No F33615 72 C 1045 formula The obtained population of random realizations of the A description is given of the BR-1 (Blast Response) finite critenal function are processed by usual statistical methods The element computer code that was developed to predict the local purely numerical method can be used even ior complicated and damage and transient response of metallic aircraft structural com- nonlinear systems, but it requires comparatively much machine time partments subjected to blast pressures and fragments from the As an example the system of a single shaft gas generator and a detonation of high explosive (HE) projectiles within the compart- hydraulic mechanical regulator is solved (Author) ment The structural analysis is limited to isotropic materials and
324 A75 32667
unstiffened or skm-rib-strmger type construction Large deflections, A75-32662 If Drag effects on wing flutter A Petre (Bucu large strains, nonlinear stress-strain relations, and ultimate strain resti, Institutul Politehnic Gheorghe Gheorghiu De|, Bucharest, material failures are accounted for in the structural response theory Rumania) and H Ashley (Stanford University, Stanford, Calif) thai was assembled in the development of the BR 1 code Sample AIAA, ASME, and SAE, Structures, Structural Dynamics, and problems of structural response to blast loading that were executed Materials Conference, 16th, Denver Colo, May 27-29, 1975, AIAA with the BR-1 code are discussed, and the prominent role of the Paper 75-775 11 p 7 refs NSF Grant No GK-35004, Grant No membrane stresses in the response is noted (Author) AF AFOSR-74-2712 An investigation is conducted of the influence of drag on dynamic aeroelastic stability, taking into account the large-aspect- A75-32654 * # Applications of a quadratic extended interior penalty function for structural optimization R T Haftka (Technion ratio straight wing as a model The investigation makes use of the method of fixed directions The wing is an unswept cantilever of • Israel Institute of Technology, Haifa, Israel) and J H Starnes, Jr (NASA, Langley Research Center, Structures and Dynamics Div, constant cross section Strip theory for incompressible unsteady flow Hampton, Va) AIAA, ASME, and SAE, Structures, Structural is adopted as a source of loads in the lift direction Drag is assumed Dynamics, and Materials Conference, 16th, Denver, Colo. May to have invariant direction and magnitude all across the span G R 27-29, 1975, AIAA Paper 75-764 11 p 11 refs Gram No NGR-52 012-008 A quadratic extended interior penalty function formulation especially well suited for second order unconstrained optimization A75-32663 /;' The random decrement technique applied to procedures is presented Analytical derivatives of constraints and an the YF-16 flight flutter tests W J Brignac, H B Ness, and L M approximate analysis technique are used Minimum-mass design Smith (General Dynamics Corp, Fort Worth, Tex ) AIAA, ASME, results are presented which indicate that the combination of these and SAE, Structures, Structural Dynamics, and Materials Conference, procedures can help make mathematical programming a useful 16th. Denver, Colo , May 27-29, 1975, AIAA Paper 75 776 9 p 7 optimization tool for large order structural design problems with a refs large number of design variables and multiple constraints Examples The application of the random decrement method to flight include statically loaded high- and low aspect ratio wings simul- flutter testing of the YF 16 lightweight fighter prototype is taneously subiected to stress, displacement, minimum gage and, in described The method was adopted to simplify and shorten the some cases, maximum strain constraints (Author) flutter clearance procedure In this approach, subcritical damping of the structural modes is extracted from the turbulence-induced random vibrations of the structure Hence, the method bypasses the requirement for an excitation system needed in the conventional A75-32656 * # Stochastic model for fatigue crack size and approaches Damping is obtained from the Randomdec Signature of cost effective design decisions S Hanagud (Georgia Institute of each mode The Randomdec Signature is analogous to the transient Technology, Atlanta, Ga ) and B Uppalun AIAA, ASME, and SAE, response to an initial displacement To obtain a Randomdec Structures, Structural Dynamics, and Materials Conference, 16th, Signature, one collects and averages a number of segments of the Denver, Colo, May 27-29, 1975, AIAA Paper 75-766 10 p 16 refs random response of the mode (Author) Grant No NCR 11 002-169, Contract No NAS8 30617 This paper describes a methodology for making cost effective fatigue design decisions The methodology is based on a probabilistic model for the stochastic process of fatigue crack growth with time A75 32664 // Minimum weight design of the F 15 em- The development of a particular model for the stochastic process is pennage for flutter J D Shelton and P B Tucker (McDonnell also discussed in the paper The model is based on the assumption of Aircraft Co , St Louis, Mo ) AIAA, ASME, and SAE, Structures, continuous time and discrete space of crack lengths Statistical Structural Dynamics, and Materials Conference, 16th, Denver, Colo , decision theory and the developed probabilistic model are used to May 2729, 1975, AIAA Paper 75 777 10 p 6 refs develop the procedure for making fatigue design decisions on the The twin boom F 15 empennage was found to be a complex basis of minimum expected cost or risk function and reliability dynamical system and considerable effort was devoted to the bounds Selections of initial flaw size distribution, NOT, repair evaluation of alternate methods for achieving a flutter free configura threshold crack lengths, and inspection intervals are discussed tion To obtain a minimum weight low drag design, the stiffness (Author) properties of the boron composite lifting surfaces were tailored, boron composite skins were used on the rudders, vertical tail tip pod A75-32657 * # Statistical estimation of service cracks and balance weights were added, and the inboard leading edge of the maintenance cost for aircraft structures J N Yang (Virginia stabilators was snagged The program for the design and flutter Polytechnic Institute of State University, Blacksburg, Va ) AIAA, substantiation of the F 15 empennage is summarized and significant ASME, and SAE, Structures, Structural Dynamics, and Materials results of analytical flutter studies and wind tunnel flutter model test Conference, 16th, Denver, Colo, May 2729, 1975, AIAA Paper data that affected the empennage design are presented (Author) 75 767 11 p 20 refs Grant No NsG 1099 A method is developed for the statistical estimation of the number of cracks to be repaired in service as well as the repair and A75-32667 * K Influence of structural damping, preconing the maintenance costs The present approach accounts for the offsets and large deflection on the flap-lag-torsional stability of a statistical distribution of the initial crack size, the statistical nature cantilevered rotor blade P Friedmann (California, University, Los of the NDI technique used for detecting the crack, and the renewal Angeles, Calif ) AIAA, ASME. and SAE, Structures, Structural process for the crack propagation of repaired cracks The mean and Dynamics, and Materials Conference, 16th, Denver, Colo, May the standard deviation of the cumulative number of cracks to be 2729, 1975. AIAA Paper 75-780 14 p 12 refs Army-supported repaired are computed as a function of service time The statistics of research, Grant No NGR-05-007-414 the costs of repair and maintenance, expressed in terms of the A set of equations describing the coupled flap-lag-torsional percentage of the cost of replacement, are estimated as a function of dynamics of a cantilevered rotor blade in hover is presented This set service time The results of the present study provide relevant of equations is used to evaluate the influence of structural damping, information for the decision of fleet management, the estimation of preconing and offsets on the linearized aeroelastic stability of some life cycle cost, and procurement specifications The present study is representative blade configurations A number of examples illus- essential to the design and cost optimization of aircraft structures trating the coupled nonlinear flap-lag-torsional response are con- (Author) sidered (Author)
325 A75 32668
A75-32668 g New Air Force requirements for structural Force applied at a point can be distributed over a large area By using safety, durability and life management M D Coffin (USAF, appropriate cross and angle ply orientations one can use B Al's Aeronautical Systems Div , Wright Patterson AFB, Ohio) and C F inherently excellent strength and stiffness to the full Special Tiffany A/AA, ASME, and SAE, Structures, Structural Dynamics, attention was directed to calculating the B Al web dimensions and and Materials Conference, 16th, Denver, Colo, May 27 29, 1975, their fixture to the cover sheets The finished element incorporates AIAA Paper 75-781 8p 8 refs two basic substructures The corrugated webs are obtained by braze The past five years have seen significant changes in the Air Force bonding tapes, the laminated cover sheets are made by using a mask philosophy and approach in achieving structural safety and durability m order to obtain the required varying cross sections during the in military aircraft These changes have been motivated by problems braze bonding process (Author) of high cost, late system development programs, with a high level of in-service structural maintenance and modification costs (poor A75-326BO II Ion vapor deposited aluminum improves struc- durability) and, in some cases, less than desired fracture resistance ture durability E R Fannm and K E Steube (McDonnell Aircraft (poor damage, tolerance/safety) The problem area has been attacked Co , St Louis, Mo ) AIAA, ASME, and SAE, Structures, Structural along a number of avenues, one major thrust has been a thorough Dynamics, and Materials Conference, 16th, Denver, Colo, May examination and revision of the structural design and test specifica 27-29, 1975, AIAA Paper 75-807 6 p 5 refs tions, the MIL A-8860 series In this paper certain aspects of the Two fairly recent changes in airframe structure have had an overall problem are discussed An overview of the pre-1969/70 Air impact on the corrosion protective coatings used First, the fatigue Force approach is presented along with its shortcomings, and, finally, improvements resulting from the use of interference fit fasteners can significant aspects of current policy are listed giving comparisons be greatly reduced if anodic coatings are applied to the aluminum with the old requirements (Author) structure The second change involves the increased utilization of titanium structure which places a restriction on the use of cadmium A75-32670 * # Hypersonic wing test structure design, anal- plating because of potential solid metal embnttlement Data is ysis, and fabrication P P Plank (Martin Marietta Aerospace, Denver, presented to show that ion vapor deposited aluminum coatings can Colo ) AIAA, ASME, and SAE, Structures, Structural Dynamics, and Materials Conference, 16th, Denver, Colo , May 27-29, 1975, be substituted for both of the above coatings without these AIAA Paper 75785 12 p Contract No NAS4 1845 undesirable effects Additional performance comparisons of the An investigation was conducted to provide the analyses, data, aluminum coating will also be described (Author) and hardwaie required to experimentally validate the beaded panel concept and demonstrate its usefulness as a basis for design of a hypersonic research airplane (HRA) Combinations of beaded panel A75-32684 ,? Crippling/column buckling analysis and test of structure, heat shields, channel caps, and corrugated webs for ribs graphite/epoxy stiffened panels E E Spier (General Dynamics and spars were analyzed for the wing of a specified HRA to operate Corp, Convair Div, San Diego, Calif) AIAA, ASME, and SAE, at Mach 8 with a life span of 150 flights Detailed analyses, Structures, Structural Dynamics, and Materials Conference, 16th, conducted in accordance with established design criteria, included Denver, Colo , May 27-29, 1975, AIAA Paper 75-753 17 p 6 refs aerodynamic heating and load predictions, transient structural This paper is concerned with test and analysis of graphite/epoxy thermal calculations, extensive NASTRAN computer modeling, and stiffened panels Both wide-column and local crippling tests were structural optimization After geometry was established for the total involved, where conventional aircraft strength of materials tech- wing, part of the wing (85 sq ft) was designed, fabricated, and niques, in conjunction with lamination theory, were employed in the assembled into a test structure to experimentally verify the structural analysis Stiffener cross sections include both rectangular and I adequacy of the beaded panel design concept (Author) section shapes Although catastrophic delammations usually occur at failure, theoretical predictions of crippling and wide column A75-32673 * # Impact fracture of composite sandwich struc- strengths agree remarkably well with the test results The test panels tures M D Rhodes (NASA, Langley Research Center, Hampton, have potted end supports, providing nearly clamped-end conditions Va I AIAA, ASME, and SAE, Structures, Structural Dynamics, and in the testing machine Slenderness ratios were carefully selected to Materials Conference, 16th, Denver, Colo, May 27-29, 1975, AIAA provide either a crippling specimen or a moderate length column as Paper 75-748 10 p 12 refs required The stiffened panels were Type A-S/3501 graphite/epoxy An experimental investigation of impact initiated failures in with cocured stiffeners The skins were pseudoisotropic laminates, high strength graphite/epoxy and Kevlar-49/epoxy sandwich struc- while several laminations were selected for elements of the stiffeners tures has been conducted The tests consisted of firing small diameter The results of this paper have demonstrated good potential for aluminum projectiles with a velocity range of 1667 meters/second graphite/epoxy structures in primary components of aircraft and (52 220 ft/sec) at preloaded sandwich specimens These tests were spacecraft (Author) intended to be representative of service conditions on materials and structures which might be used as secondary aircraft components The preload and impact energy necessary to initiate catastrophic A75-32688 * # Analytical displacements and vibrations of failure were determined The residual strength of impact damaged cantilevered unsymmetric fiber composite laminates M D Mimch specimens was also measured The results of these tests indicate that and C C Chamis (NASA, Lewis Research Center, Cleveland, Ohio) catastrophic failures in sandwich structures can be initiated at AIAA, ASME, and SAE, Structures, Structural Dynamics, and relatively low preloads by impact projectiles at energy levels well Materials Conference, 16th, Denver, Colo , May 27-29, 1975, AIAA below that required to initiate visible damage (Author) Paper 75-757 13 p 6 refs A fiber composite flat cantilever plate that has symmetric and A75-32675 ff Development and testing under static condi- nonsymmetric laminate configurations is theoretically investigated to tions of a B-AI load transfer element R Gunther and W Hartmann determine its static and dynamic structural response The finite (Messerschmitt-Bolkow-Blohm GmbH, Ottobrunn, West Germany) element analysis method used includes a unique triangular finite AIAA, ASME, and SAE, Structures, Structural Dynamics, and element developed at Lewis for the analysis of fiber composite Materials Conference, 16th, Denver, Colo , May 27-29, 1975, AIAA airfoils The various responses investigated include tip displacements, Paper 75-788 15 P Research sponsored by the Bundesmimstenum natural frequencies, and fundamental mode shapes The results show der Verteidigung of West Germany that laminate configurations may be selected for a cantilever such High strength aircraft structures can be manufactured from that when the tip at the leading edge is loaded normal to the plane of boron fiber reinforced aluminum (B AD B-AI structural components, the plate, the tip at the trailing edge can (1) deflect in the opposite including a load transfer element, have been manufactured and direction, (2) deflect about the same, or (3) deflect more than the tip tested The load transfer element consists of fan shaped B-AI at the leading edge This variation in response can be utilized to corrugated webs joined to B-AI cover sheets of varying thickness provide built in structural damping to resist flutter (Author)
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A75-32689 # Subsonic transient lifting surface aero- A75-32693 * # Integrated potential formulation of unsteady dynamics T B Burkhart (McDonnell Douglas Corp , St Louis. Mo ) supersonic aerodynamics for interacting wings K Appa (Bell AIAA, ASME. and SAE, Structures, Structural Dynamics, and Aerospace Co, Buffalo, N Y ) and W P Jones (Texas A & M Materials Conference, 16th, Denver, Colo , May 27-29. 1975, AIAA University, College Station, Tex ) AIAA, ASME, and SAE, Struc- Paper 75-758 10 p 15refs tures, Structural Dynamics, and Materials Conference, 16th, Denver, A method is presented for numerical evaluation of subsonic Colo . May 27-29, 1975, AIAA Paper 75-762 14 p 40 refs Contract transient lifting surface aerodynamics Existing subsonic oscillatory No NAS1 12709 aerodynamic procedures are modified to evaluate generalized aero A numerical integrated velocity potential method for the dynamic factors as two matrices aerodynamic stiffness and damping determination of unsteady aerodynamic forces on arbitrary inter Transfer functions are numerically evaluated which describe the acting wings and tails in supersonic flow has been developed complex variation with reduced frequency of each matrix element Constant Mach number has been assumed throughout the flow field The results are used to formulate the aeroelastic equations of motion Normalwash and sidewash integrals have been derived The upwash in the Laplace operator and real time domains The Laplace operator integral remains to be derived Singular integrals in the expressions formulation is applied to transient flutter solutions and the results for the velocity components have been evaluated in closed form compared to conventional solutions The time formulation is applied Lifting surfaces are represented by triangular elements defined by to several time history dynamic response configurations (Author) arbitrarily spaced characteristic lines and the true surface edges The wake field is represented by rectangular strip elements Velocity potential distributions and generalized aerodynamic coefficients have been compared (Author)
A75-32690 # The flutter analysis of T tails W P Jennings A75-32694 g Interaction between control augmentation and M A Berry (Boeing Co , Seattle. Wash ) AIAA, ASME, and system and airframe dynamics on the YF-17 T D Arthurs and J T SAE, Structures, Structural Dynamics, and Materials Conference, Gallagher (Northrop Corp, Hawthorne, Calif) AIAA, ASME, and 16th, Denver, Colo, May 2729, 1975, AIAA Paper 75 759 5 p 7 refs SAE, Structures, Structural Dynamics, and Materials Conference, 16th, Denver, Colo . May 27-29, 1975, AIAA Paper 75-824 10 p 5 The importance of stabilizer dihedral and static lift forces on refs T-tail flutter speeds is discussed Based upon strip theory considera Three types of instability, involving interaction between control tions the additional unsteady aerodynamic forces derived from these static forces are introduced into the generalized air forces of the augmentation system (CAS) and airframe dynamics, were identified system The importance and introduction of structural deformations during development of the YF 17 air combat fighter Two were caused by such static forces are also considered These effects are potential flight instabilities the first in which the CAS coupled with confirmed by the results of flutter tests on a low speed flutter model rigid airframe dynamics, the second involving coupling with elastic (Author) structural dynamics The third type was the ground instability generally referred to as ground resonance This paper describes the analytical and test methods used to define feedback compensation required to suppress adverse coupling and permit CAS operation at design gain levels All three types of instability were found to be A75-32691 ff The supersonic doublet lattice method - A predictable using a unified analytical approach and no unanticipated comparison of two approaches B J Brock and J A Griffin, Jr interaction was encountered during the flight program Recommen (LTV Aerospace Corp, Dallas, Tex) AIAA, ASME, and SAE. dations are made for the use of improved analogs of airframe Structures, Structural Dynamics, and Materials Conference, 16th, response in ground limit cycle tests (Author) Denver, Colo , May 27-29, 1975, AIAA Paper 75-760 8 p The method described is based on a relatively simple form of the kernel function for supersonic flow Techniques are presented for A75 32695 » YF16 active control-system/structural dynam- evaluating the required integrals of the kernel function with its ics interaction instability R P Peloubet, Jr (General Dynamics singularities for the coplanar condition Certain difficulties in the Corp, Fort Worth, Tex) AIAA, ASME, and SAE, Structures, application of the supersonic doublet lattice method have been Structural Dynamics, and Materials Conference, 16th, Denver, Colo , overcome by developing an approach based on rectangular panels May 2729, 1975.AIAA Paper 75-823 16p 11 refs mapped into squares An approach utilizing a doublet Mach box is During the early flight tests of the YF16 an instability was compared with the doublet lattice method G R encountered involving antisymmetric oscillations of the airplane at a frequency of 6 5 Hz Subsequent analyses coupling flexible airplane dynamics and the active flight control system were conducted for flight conditions at which the instability had been observed Antisymmetric natural modes of vibration measured during the A7S-32692 # Oscillatory supersonic lifting surface theory ground vibration tests were used as degrees of freedom as well as the using a finite element doublet representation J P Giesing and T P antisymmetric rigid body degrees of freedom The Nyquist criteria Kalman (Douglas Aircraft Co , Long Beach, Calif) AIAA, ASME, was employed to determine stability of the system in the frequency and SAE, Structures, Structural Dynamics, and Materials Conference, domain The analyses indicated that the instability was caused by a 16th, Denver. Colo , May 27-29, 1975, AIAA Paper 75-761 18p 18 coupling of the flight control system and the vibration modes of the refs Research supported by the Douglas Aircraft Co airplane The degree of correlation between analysis and flight test is A new method for predicting oscillatory supersonic lifting shown (Author) surface airloads has been developed which is based on a finite element doublet representation The finite elements are both swept A75 32697 * # Active flutter suppression using trailing edge and tapered and thus are able to fit most planforms accurately and tab control surfaces E Nissim (Techmon - Israel Institute of Diaphragm regions are eliminated because of the doublet representa Technology, Haifa, Israel) AIAA. ASME, and SAE. Structures, tion and the procedure is applicable to very general nonplanar Structural Dynamics, and Materials Conference. 16th. Denver. Colo , configurations As a first step in the development of this procedure May 2729, 1975, AIAA Paper 75-822 8 p Grant No NsG 7072 the present paper gives the theory and results for the planar case An optimization procedure, based on the Aerodynamic Energy Subsonic and supersonic leading or trailing edges are considered In concept, is applied to the problem of flutter suppression using addition, control surface and wing tail interaction cases are also trailing edge (T E ) and tab control surfaces A control law is considered (Author] assumed which allows the T E -Tab system to be driven by both
327 A75-32701
linear and rotational sensors, and the optimum control law param and attempts to solve it are discussed One of the mam difficulties eters are determined Results are presented which indicate the derives from the incompatibility of strength and corrosion resistance capability of the T E Tab control system to suppress flutter A properties But a new aluminum alloy, AA7050, combines resistance comparison is also made between the T E Tab and the leading edge to exfoliation and stress corrosion with high strength, superior (L E ) T E control systems which shows their relative effectiveness toughness and excellent fatigue behavior Another area of concern is together with some aspects connected to the realization of the coating composition, the history of coating materials development is control law (Author) reviewed, with polyurethane playing an important role after WWII SJM
A75-32701 * ;/' Evaluation of bead-stiffened metal panels j L Shideler, H L Bohon (NASA, Langley Research Center, Structures and Dynamics Div , Hampton, Va ), and B E Greene A75-32839 Materials for gas turbines R J E Glenny (Boeing Aerospace Co, Seattle, Wash) AIAA, ASME, and SAB, (Royal Aircraft Establishment, Farnborough, Hants, England), J E Structures, Structural Dynamics, and Materials Conference, 16th, Northwood (National Gas Turbine Establishment, Farnborough, Denver, Colo , May 27-29, 1975, AIAA Paper 75-815 9 p 15 refs Hants, England), and A Burwood-Smith (Ministry of Defence, Potential weight efficiency for bead-stiffened panels has been London, England) International Metallurgical Reviews, vol 20, Mar demonstrated through fabrication and testing Theoretically opti- 1975, p 1 28 257 refs mum design concepts were identified, and small specimens were The major components of gas turbines and their materials tested under combined compression, shear, and bending to determine requirements are outlined The properties, advantages, and limita- local buckling failure loads and to verify theory Large optimized tions of materials which have been and are being used in gas turbines panels were then designed and tested under combined loads are then described in the following groups aluminium alloys, Correlation of test data for large circular tubular panels with theory magnesium alloys, titanium and its alloys, steels, and finally nickel- was conservative and consistent, and mdFcated reliable and accept- and cobalt base alloys The applications of the last group of alloys able design theory Tests of fluted tubular panels indicated general and the importance of their metallurgical stability in turbine blades, instability failures at loads far below the design values due to discs, nozzle guide vanes, and sheet metal components are discussed nonlinear distortions Further study of the fluted tubular configura- Corrosion and its prevention are then considered, followed by tion will be required if its potential weight efficiency is to be sections on experimental materials including alloys of chromium and attained (Author) the refractory metals, ceramics, and fibre composites Future trends and prospects are discussed briefly in a concluding section (Author)
A75-32705 (f System identification of a complex structure A Berman (Kaman Aerospace Corp, Bloomfield, Conn) AIAA, ASME, and SAE, Structures, Structural Dynamics, and Materials Conference, 16th, Denver, Colo, May 27-29, 1975, AIAA Paper A75-32840 Chemical milling J W Dim (Sandia Labora- 75-809 7 p 6 refs Grant No DAAJ02-74 C-0039 tories, Livermore, Calif ) International Metallurgical Reviews, vol The method of incomplete models has been extended and used 20, Mar 1975, p 29 55 191 refs to obtain dynamic equations of motion of a helicopter transmission Chemical milling has been used to advantage in removing excess gearbox from shake test data The application resulted in a valid material and reducing the overall weight of metal parts It is a analytical model covering a frequency range to 3000 Hertz and valuable complementary technique to conventional milling and encompassing approximately twenty major normal modes The machining methods and is particularly useful for removing metal model is usable for component synthesis analyses and for the study from thin sections or from parts that are already shaped The first of effects of boundary conditions and structural changes The paper section of this report discusses chemical milling generally, describing demonstrates a simple and inexpensive procedure compared to a the process, its applications, advantages and limitations, chemical conventional finite element analysis and its use is recommended milling solutions, maskants, and various other aspects of the chemical where such analyses are uneconomical or impractical and where milling process The second section considers the effectiveness of hardware exists (Author) chemical milling for some specific materials aluminium, beryllium, magnesium, titanium, steel, and some stainless steel alloys Various A75-32706 /, Vibration analysis of multi symmetric struc chemical milling solution formulations are presented and effects on tures D A Evensen (TRW Systems Group, Redondo Beach, Calif ) such factors as mechanical and fatigue properties are considered AIAA, ASME, and SAE, Structures, Structural Dynamics, and (Author) Materials Conference, 16th, Denver, Colo , May 27-29, 1975, AIAA Paper 75 808 15 p 16 refs This paper demonstrates that for multi symmetric structures, symmetry concepts can be used to reduce the size of the eigenvalue A75-32907 ft Aerodynamic heating in gaps in the presence problem which must be modelled and solved using a discrete of protuberances and shock wave impingement F T Hung and C A formulation It also demonstrates that an understanding of group Scottolme (Rockwell International Corp , Downey, Calif) American theory can be used to order and classify the vibration modes of Institute of Aeronautics and Astronautics, Thermophysics Con multi symmetric structures The primary new innovation of this ference, 10th, Denver, Colo , May 27-29, 1975, Paper 75 670 8 p report is the demonstration that it is not necessary to formulate a 15 refs structural dynamic model for more than a small pie shaped segment An experimental investigation of gap aerodynamic heating with of the structure This innovation required the development of external pressure gradient was conducted at Mach 5 2 Pressure appropriate boundary conditions on the edges of the pie shaped gradients were created on a sharp leading edge flat plate by either segment, and these have been derived for an equilateral triangle and a cylindrical protuberances or impinging shock waves generated by hexagon Although these ideas are demonstrated herein for flat two dimensional wedges Effect of pressure gradient level on gap polygonal membranes, they can be generalized to space frames, dish heating was determined by varying wedge angle, cylinder diameter antennas, and large three dimensional structures (Author) and cylinder orientation Gaps with different orientations and widths were tested and both laminar and turbulent external flows were studied Results indicate that heating in gaps with external pressure A75-32830 # Corrosion control in naval aircraft A M gradients can be orders of magnitude higher than the zero pressure Malloy Naval Aviation News, vol 57, May 1975, p 3239 gradient case Correlations were derived based on test results Various aspects of the current naval aircraft corrosion problem (Author)
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A75-32954 ff Study of a strongly asymmetric turbulent Shuttle training aircraft, and an airline training total in flight wake behind a profile with upper surface separation (Etude du sillage simulator S D turbulent fortement asymetrique derriere un profit avec decollement d'extrados) P E Lemonnier and L F Tsen (Poitiers, Universite, A75-33331 # Determination of surface roughness of materi Poitiers, France) Jugoslovensko Drustvo za Mehaniku, Yugoslav als (Opredelenie sherokhovatosti poverkhnosti matenalov) V F Congress of Rational and Applied Mechanics. 12th, Ohrid, Yugo- Kameko, E P laskevich, lu T Rezmchenko, V M Kovtunenko, V slavia, June 3-8, 1974, Paper 10 p 5 refs In French Direction des K Mostipan, V A Sakhnov, V S Babkm, and I S Garelik Rechercheset Moyens d'Essais Contract No 71/349/2 Aerodmamika Razrezhennykh Gazov, no 7, 1974, p 51-59 6 refs Wind-tunnel experiments were performed to study the incom- In Russian pressible turbulent wake produced by a plane profile at a nonzero The parameters of surface roughness of sheet-metal samples of angle of incidence with upper surface separation A Prandtl- magnesium aluminum alloys (AMg6-M, D16-A-T, MA2 IM) used as Kolmogoroff type turbulence model was derived which, when used the outer surface of an aircraft are determined by profilogrammetric in the Reynolds equations and the equations for the turbulent and stereophotogrammetric techniques The roughness parameters kinetic energy, permits satisfactory theoretical wake prediction The thus obtained are represented analytically as the terms of a Fourier turbulence models determined experimentally for a wake produced series The dominant harmonics of the roughness profile are by a profile with zero incidence were confirmed by measurements determined from the amplitude phase characteristics obtained for made on the wakes produced by a profile with nonzero incidence each material under study The results indicate that the surface of and upper surface separation ATS the analyzed materials can be considered as being of low roughness S 0
A75-32995 # Formation of flexibility matrices of a struc- A75-33339 # Free-molecular interference of cylinders with ture based on known yields at arbitrary points (Formiranje matrica oblique ray reflection (Svobodnomolekuharnaia mterferentsiia tsi gipkosti strukture na bazi poznatih ugiba u proizvoljmm tackama lindrov pri lucrievom otrazhenn s naklonom) V L Sergeev iste) S Lukic (Vazduhoplovnotehnicki Institut, Zarkovo, Yugo Aerodmamika Razrezhennykh Gazov, no 7, 1974, p 137-147 In slavia) Jugoslovensko Drustvo za Mehaniku, Yugoslav Congress of Russian Rational and Applied Mechanics, 12th, Ohrid, Yugoslavia, June 3-8, A solution is obtained to the problem of interaction between 1974, Paper 10 p 6 refs In Serbo-Croatian infinite parallel cylinders situated in a free-molecular hypersonic (M A method is developed for forming the flexibility matrix of a = infinity) gas flow in the case of oblique ray reflection of atoms structure based on the known yeilds at arbitrary points As an from the surface The ray model of atom reflection from a surface example, an experimental procedure for determining the flexibility takes into account the relationship between average reflection matrix of an aircraft wing is explained ATS velocity and angle of incidence The local fluxes of mass, momen turn, and energy are calculated along with the air drag coefficients for different angles of attack and for various distances between the cylinders The air drag coefficients for rays reflected normal to the A75-33103 ff Observing cold-night temperatures of agri- surface are compared to those for rays reflected at an oblique angle cultural landscapes with an airplane-mounted radiation thermometer SD P R Nixon (Agricultural Research Service, Weslaco, Tex ) and T A Hales (Texas A & M University, Weslaco, Tex ) Journal of Applied Meteorology, vol 14, June 1975, p 498 505 15 refs A75-33346 # Experimental investigation of friction on a plate in the flow of a rarefied gas (Ekspenmenta''noe issledovanie trenna na plastme v potoke razrezhennogo gaza) N M Bazarnova, A75-33150 # Fabrication of one-piece-forged thin walled A A Krylov, and B B Stankov Aerodmamika Razrezhennykh parts having variable cross section (Izgotovlenie tsel'nojhtampovan- Gazov, no 7, 1974, p 211-219 6 refs In Russian nykh tonkostennykh detalei peremennogo sechemia) 0 V Popov Moscow, Izdatel'stvo Mashmostroeme, 1974 120 p 20 refs In Russian A75-33417 Sound radiation from a bounded thin mhomo- The present work explains the theoretical and technological geneous plate reinforced with N ribs and driven by boundary-layer principles of producing one-piece-forged thin-walled parts of variable pressure fluctuations R A Mikhitarov (Akademna Nauk SSSR, cross section The range of application of such parts in the Akusticheskn Institut, Moscow, USSR) (Akusticheskn Zhurnal, vol construction of aircraft and other machines and mechanisms is 20, Nov-Dec 1974, p 863-873 ) Soviet Physics - Acoustics, vol 20, considered An explanation is given of the technological processes May-June 1975, p 528-533 6 refs Translation used in forming such parts by bulk forging from thin-walled blanks using thermal and stress intensification ATS A75-33427 # A theoretical analysis for three dimensional ram wings in parallel walls H Nakatam, Y Miyai (Osaka Prefecture, University, Osaka, Japan), and K Mmami (Kawasaki Heavy In A75-33187 Recent advances in in-flight simulator technol- dustnal Co, Ltd, Kobe, Japan) Japan Society for Aeronautical and ogy G W Hall (Calspan Corp, Buffalo, NY) In Annual Space Sciences, Transactions, vol 18, Mar 1975, p 1228 5 refs Simulation Symposium, 8th, Tampa, Fla , March 12 14, 1975, The method of matched asymptotic expansions is applied to the Proceedings Symposium sponsored by the Society for Computer analysis of a three-dimensional ram wing in parallel walls In this case Simulation Tampa, Fla , Annual Simulation Symposium, 1975, p the flows above and below the wing and trailing vortex wake, are 11 29 7 refs - two-dimensional in x, y plane The edge flow solutions are applied The mechanization, uses, recent technological developments, along the side edges of the wing and wake as well as along the leading and future prospects of in flight simulators are reviewed The and trailing edges By matching, the solution which is uniformly valid response feedback and model following systems used in airplane is obtained in the overall flow regions As numerical applications, in-flight simulators are described The principles of operation and the simple analytic results for semi-elliptic and semi-circular flat wings primary functions of several representative in flight simulators used are obtained Total lift and induced drag coefficients of those wings in conventional and V/STOL simulation are discussed Among the having straight trailing edges are calculated for different ratios of the in flight simulators under development are sophisticated variable- distance of parallel walls to the height of trailing edge of the wing stability helicopter with six-degree of freedom control, a Space (Author)
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A75-33435 # Side forces on unyawed slender inclined aero- can have specific fuel consumptions about 17% lower for flight, and dynamic bodies H C Kao (Northrop Corp, Hawthorne, Calif) up to 24% lower for sea-level static, operation It was assumed that Journal of Aircraft, vol 12, Mar 1975, p 142150 15refs the effective nacelle drag coefficients of regenerative turbofans Wind tunnel tests in recent years have indicated the existence of would not be higher than those of nonregenerative engines provided nonzero side forces and yawing moments on a fuselage model, greater installation complexity is acceptable The predicted thrust-to- configuration build-up, and a complete airplane model at high angles weight ratio of regenerative units is approximately 3 2 1 compared of attack but zero angle of sideslip These forces and moments are a with 6 1 for high pressure, high-bypass-ratio machines Typically, potential hazard to aircraft stability and control Based on observa assuming that both engine types are suitable alternatives for a tions in some related experiments, theoretical consideration and particular aircraft, this weight penalty would be counteracted by a finally some interpretation, a simple model is proposed to describe fuel saving after about 4 hr flying without reserves The correspond- the flow characteristics of these nonzero forces and moments A ing figure for srnall aircraft, for which high-pressure-ratio turbofans prediction method resulting from this model with correlation appear to be impractical, is about 2 hr In the absence of major parameters taken directly from the published papers is formulated developments in regenerator technology regenerative turbofans ap- The calculated results are compared with low-speed test data of a pear to be restricted to relatively low-thrust applications (Author) 10% scale F 5E fuselage model and a circular tangent ogive with afterbody and show satisfactory agreement (Author) A75-33447 Variable geometry today R M Braybrook Air International, vo\ 8, Mar 1975, p 111 124 A75-33436 If Image system solution for store aerodynamics Contemporary applications and requirements of variable geom with interference I F W Martin (Auburn University, Auburn, Ala ), etry (VG) in highspeed aviation are discussed Advantages and G H Saunders (ARO, Inc , Arnold Air Force Station, Tenn ), and C problems associated with the use of the VG wing are assessed, and J Smith (Electronic Data Systems, New York, N Y ) Journal of the development of NASA's outboard hinge is described The Aircraft, vol 12, Mar 1975, p 151 155 7 refs performance of the F 111 is evaluated, and the latest swing wing The aerodynamic interference problem for external aircraft aircraft are discussed in detail, including the American EF 111A, stores has been analyzed using the image system technique In order F 14A, and 81, the Soviet Su 20 and MiG 23, the French Mirage G, and the European Panavia MRCA Reference is made to the MiG to facilitate this analysis it has been assumed that small perturbation solutions are valid It is further assumed that the external stores are Fencer and Tupolev Backfire, two Soviet strategic fighter bombers slender, axisymmetric bodies and that the interference can be about which very little information is available F G M analyzed by first assuming a cross flow solution Both body body and wing-body interference solutions have been obtained For the A75-33448 Mitsubishi's mentor Supersonics from body-body solution, the image systems in the cross flow plane Nagoya E Sekigawa Air International, vol 8, Apr 1975, p consist of source sink pairs appropriately located by using the 170 176 Milne Thomson circle theorem The actual three-dimensional source- Development and specifications of the supersonic Mitsubishi T-2 sink pairs are displaced from the body axis according to the advanced trainer are described Of conventional semi-monocoque cross flow image system The strengths of the source sink pairs are design, the T-2 has a shoulder mounted wing with a thickness/chord then determined by the Rankine method Good agreement has been ratio of 4 8% and leading edge sweep angles ranging from 68 deg at found between the theoretical and experimental results It is felt that the root through 42 deg out to the dog tooth extension to 36 deg at this approach to the interference problem is a significant advance the tip Built on a multi spar torsion box, each wing has two leading ment in that this technique requires only successive superposition edge flaps and a large, single-slotted trailing edge flap The aircraft is whereas most other methods such as vortex lattice, source panels, powered by two turbofans each rated at 4,620 Ib dry and 7,070 Ib etc , require, in general, simultaneous solutions (Author) with full reheat Its maximum speed is 1,056 mph at 36,000 ft with an initial climb rate of 35,000 ft/mm The combat training version is armed with one 20-mm multi-barrel rotary cannon plus two wingtip A75-33437 # Image system solution for store aerodynamics mounted Sidewinder or Mitsubishi air-to air missiles and four with interference II F W Martin (Auburn University, Auburn, Ala ) underwing rocket bombs P T H and K B Walkley (LTV Aerospace Hampton Technical Center, Hampton, Va ) (Aircraft/Stores Compatibility Symposium, Sacra- A75-33449 The annals of the polymorph - A short history mento, Calif, Sept 18-20, 1973 ) Journal of Aircraft, vol 12, Mar of variable geometry II Air International, vol 8, Apr 1975, p 1975, p 156-161 185-190 To predict accurately the trajectory of a store from an aircraft The development of variable-geometry aircraft is traced from in an interference flowfield, the mutual aerodynamic interference WW II German designs based on a variable skewed wing, through problem for external aircraft stores is analyzed using the vortex development of the variable sweep concept and the 'Swallow* image system technique It is assumed that small perturbation concept of Wallis, to the Bell aircraft The Messerschmitt P 1101, solutions are valid, that the external stores are axisymmetric slender originally designed as a single seat, single-jet fighter with a mid-wing bodies, and that mutual interference can be analyzed by a pre- swept 45 deg on the leading edges, served as the basis for the first liminary cross flow solution For the wing-pylon-body solution, the successful variable sweep aircraft, the Bell X-5, in 1951 The basic necessary image system is found by applying the Milne-Thomson characteristics of the X 5 are described, and the mam results of circle theorem to a pair of counter-rotating planar vortices in the several years of testing it are discussed P T H vicinity of a circle The strengths of the vortex image system are then obtained by satisfying the body boundary conditions at designated A75-3345U The annals of the polymorph - A short history control points on the external stores It is found that the experimental results are consistent with theory S D of variable geometry III Air International, vol 8, May 1975, p 249-257 Early aerodynamic problems associated with the variable-sweep A75-33438 ff Regenerative turbofans - A comparison with wing were related to effects of changes in wing geometry on the nonregenerative units J A C Kentfield (Calgary, University, aerodynamic center Design innovations related to NASA's outboard Calgary, Alberta, Canada) Journal of Aircraft, vol 12, Mar 1975, p pivot provided the breakthrough which was destined to put the U S 174-181 9 refs temporarily well ahead in variable geometry research American, A theoretical study was made of the performance of regenera- European, and Soviet developments concerning variable-sweep air- tive turbofans It was concluded that, on a thermodynamic and craft are discussed Today, six military aircraft utilizing variable- aerodynamic basis, compared with conventional nonregenerative, sweep wings are in service Two others are flying in prototype form high-pressure-ratio, high-bypass-ratio units, regenerative turbofans G R
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suits The effects of long-arm statutes on lurtsdictional choices is A7S-33483 H Influence of mistuning on rotor-blade vibra- discussed, and precedents set in regard to jurisdiction in tortious acts tions L E EI-Bayoumy (Consultants and Designers, Inc. East Hartford, Conn I and A V Srmivasan (United Aircraft Corp , Pratt are described Alternative ways for defense counsel to maneuver and Whitney Aircraft Div , East Hartford, Conn ) AIAA Journal, vol litigation to a more favorable forum are summarized, including 13, Apr 1975, p 460-464 6 refs invoking the doctrine of forum non convemens, removing the action This analysis is aimed at determining the influence of blade from state to federal court, and dismissal for improper venue mistuning on the vibratory stress levels of turbine and compressor Important cases involving airlines or aircraft manufacturers are blades A frequency response analysis for a given rotor configuration discussed which have involved transfer of jurisdiction F G M shows that a large number of resonances may occur over a frequency band, the width of which is nearly 20% of the mean blade frequency A75-33568 Air transportation of radioactive materials D The resonant amplitudes are a function of blade frequency and K Eyberg Journal of Air Law and Commerce, vol 40, Autumn location on the rotor, and the amount of damping present in the 1974, p 681-703 124 refs system A parametric study is carried out to evaluate the response Regulation of the air transport of radioactive materials is levels due to engine order excitation, aerodynamic and mechanical discussed, and proposals are made to improve such regulation An damping, and blade frequency deviation The resulting mode shapes incident of radiation leakage from a package aboard a commercial and frequencies are in good agreement with the experimental airliner is reviewed, the effects of radiation on humans are described, findings reported earlier in the literature (Author) and the functions of existing regulatory agencies are summarized Federal aviation regulations are outlined which pertain to the air transport of radioactive substances, and the inadequacies of such A75-33485 * tt Theoretical study of lift-generated vortex regulations are discussed, including lack of sufficient data on wakes designed to avoid rollup V J Rossow (NASA, Ames Research movements of hazardous materials, inadequate inspection efforts, Center, Moffett Field, Calif ) AIAA Journal, vol 13, Apr 1975, p and sporadic and ineffective enforcement actions It is proposed that 476-484 24 refs regulatory and enforcement functions be centralized, consumer Two hypothetical vortex wakes are introduced and studied representatives be included on regulatory bodies, on-the-spot moni- theoretically to explore whether the rollup of lift-generated vortex toring of radioactive shipments be implemented at all times, and only sheets can be suppressed The circulation distribution across each radio.sotopes needed for medical purposes be transported on wake is specified such that one rotates and the other translates as a passenger-carrying planes F G M unit due to their self-induced velocities Several span loadings are constructed from these solutions and the resulting mviscid wake A75-33569 Consequential and special damages - Tempest structure is computed for several span lengths behind the generating in the tariff W R Johnston Journal of Air Law and Commerce, vol wing by use of the discrete vortex method wherein the vortex wake 40, Autumn 1974, p 704-722 95 refs is represented by an array of vortices The final distribution of Historical and legal background information is presented in vortices is then used to estimate the rolling moment on an regard to the CAB's Liability and Claim Rules and Practices encountering wing It is found that, even though the initial specified Investigation (1970) and the subsequent decision by an administra- motions are not sustained, substantial reductions in rolling moment tive law judge that air carriers would be liable for consequential and are predicted for certain ranges of the ratio of the span of the special damages incurred in the course of handling air freight The generating wing to the following wing (Author) common-law rule of carrier liability is traced from its origins under English common law (1703) through the Federal Aviation Act of 1958, and the development of liability for consequential and special A75-33488 t! Aeroelastic panel optimization with aero- damages is similarly traced from the British landmark case of Hadley dynamic damping B L Pierson (Iowa State University of Science v Baxendala (1854) through the major American cases up to 1970 and Technology, Ames, Iowa) AIAA Journal, vol 13, Apr 1975, p The arguments presented in the CAB's (1970) investigation are 515-517 12 refs Research supported by the Iowa State University presented, and it is concluded that liability for consequential and of Science and Technology special damages is almost certain to be imposed at some future time A number of numerical solutions are presented for the case in F G M which aerodynamic damping is included in the problem formulation The solutions were obtained with the aid of the gradient projection method reported by Pierson (1974) Optical thickness ratio distri- A75-33613 S-3A stall testing and auto-throttle develop- butions for the simply supported solid panel and nondimensional real ment/testing P S Norton (Lockheed California Co, Burbank, deflection distributions for the optimal simply supported solid panel Calif ) Society of Experimental Test Pilots, Technical Review, vol 12, no 3, 1975, p 5-12 are shown in graphs It is found that the shape of the optimal The thick wing section of the S-3A results in a stall that occurs thickness distribution with damping remains relatively unchanged at the wing leading edge and in an abrupt decrease of the lift from that obtained without damping G R coefficient at the stall The development of the landing configuration stall characteristics described was intended to optimize the stall- A75-33550 B-1 airborne strategic deterrent Air Inter- warning buffet, roll-off at the stall, and the magnitudes of the stall national, vol 8, Feb 1975, p 59 64, 100 speeds themselves In addition, the landing configuration lift charac- The B 1A now under development is a swing wing, supersonic teristics are given, and the development of the auto-throttle is strategic bomber with an unrefueled range of 6100 miles The discussed V P bomber's primary mission tactic is to be low altitude penetration at near-sonic speed It would also be capable of high altitude supersonic A75-33614 The S-3A carrier suitability demonstration D missions A detailed cutaway drawing is given The B-1A concept, R Wilson (LTV Corp , Vought Systems Div , Dallas, Tex ) Society program tradeoffs, and development testing are discussed ATS of Experimental Test Pilots, Technical Review, vol 12, no 3, 1975, p 13-21 A test program which demonstrated the suitability of the S-3A A75-33565 Problems of federal and state court jurisdic- for use on aircraft carriers is described The program involved 53 tion and venue in products liability litigation Defendants viewpoint. landing and 14 catapulting demonstration, including the arrested M L Mover Journal of Air Law and Commerce, vol 40, Autumn landing phase at minimum weight, off-center arrestment, rolled and 1974, p 637-652 55 refs yawed arrestments, rolled arrestment, tail-down, nose-down, and Trends in choosing alternative forums for litigation are ex- mean attitude high-sink, free-flight arrestment, and deck obstruction amined in the context of the defense in aviational products liability impact-sensitivity to error tests V P
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A75-33615 YF-16 - A rare opportunity P F Oestricher A75-33762 ft Boron/aluminum for advanced technology air- (General Dynamics Corp , Convair Aerospace Div , San Diego, Calif ) craft A R Robertson (General Dynamics Corp , Convair Div, San Society of Experimental Test Pilots, Technical Review, vol 12, no Diego, Calif ) AIAA, ASME, and SAE, Structures, Structural 3, 1975, p 22-26 Dynamics, and Materials Conference, 16th, Denver, Colo, May A pilots report is presented on the testing of the YF-16 fighter 2729, 1975, AIAA Paper 75790 7 p 6 refs Contract No aircraft and on the characteristics of the craft itself The principal F33615-74-C-5151 systems of the fighter are discussed V P A program is being performed to demonstrate that a boron/ aluminum component design can replace an all-metal design and have A7S-33617 Bell Helicopter/NASA/Army XV-15 status re- not only performance advantages but cost advantages as well Five port G L Colvin (Bell Helicopter Co , Fort Worth, Tex ) Society of components from the B-1 were studied in sufficient detail to Experimental Test Pilots, Technical Review, vol 12, no 3, 1975, p determine the configuration, weights, and projected manufacturing 33-36 costs of designs using boron/aluminum Composite configurations The XV-15 tilt rotor aircraft, designated model 301 by the Bell were provided that could be substituted directly for the baseline Helicopter Company, is being designed as a flight research vehicle to design with only very minor modifications to the surrounding study the use of tilt rotor technology in civil and military missions structure Weight savings predicted for the composite designs varied The program status of the helicopter is updated and reviewed V P between 8 and 56% With four of the parts examined, the predicted cost savings varied between 24 and 69% The fifth part was not cost effective A diffusion-bonded titanium rib from the root of the wing A75-33618 Stone Spin Shorthand, including Spin Data was selected for detailed evaluation, the results of which are Card and sample Criteria Spin Set R R Stone (Beech Aircraft presented Detailed manufacturing costs were prepared for the Corp , Wichita, Kan ) Society of Experimental Test Pilots, Technical baseline titanium configuration and the boron/aluminum configura- Review, vol 12, no 3, 1975, p 37-42 tion High-cost manufacturing areas were identified and were the Experimental flight testing of out-of control flight requires extra basis for a manufacturing development program (Author) emphasis on the standard test objectives of accuracy, consistency, and thoroughness to ensure safety during the test effort The test program must be designed to assure safety of the operational user by A75-33763 ;'/ Analytical prediction of fatigue crack growth exploring the entire out-of-control potential The three flight test at cold-worked fastener holes J B Chang (Rockwell International innovations proposed for the 1000 + Spin YT-34C Test program are Corp, Los Angeles, Calif) AIAA, ASME, and SAE, Structures, a Spin Shorthand for glance reference to cockpit control positions Structural Dynamics, and Materials Conference, 16th, Denver, Colo , for entry, spin to steady state, and recovery, a Spin Data Card May 27-29, 1975, AIAA Paper 75-805 7 p 23 refs Research adapted to the Spin Shorthand, and a sample Criteria Spin Set to sponsored by the Rockwell International Independent Research and provide a comprehensive matrix of spins and recoveries for thorough Development Program definition of spin characteristics V P A methodology for the quantitative prediction of crack growth behavior at cold-worked fastener holes under fatigue cyclic loading has been developed The proposed analytical prediction technique is based on an effective stress field concept which accounts for the A75-33619 Why so few all new General Aviation aircraft amount of the compressive residual stress existing at the edge of the J R Humphreys Society of Experimental Test Pilots, Technical cold worked hole Stress intensity factor ranges (delta K) and crack Review, vol 12, no 3, 1975, p 43-50 growth rates (da/dn) are all formulated in terms of the effective The question is raised why the General Aviation portion of the stress field An existing fatigue crack growth analysis computer aircraft industry (all aircraft other than military and airlines types) program has been modified to account for these changes This does not offer 'all new' models more often, in spite of the assurance program was subsequently used to study the B 1 fracture mechanics of marketing departments that some of the new aircraft designs design development test data Good correlations have been obtained already engineered are just what people are waiting for The low-risk (Author) policies of boards of directors and top management, and the economic, financial, and other factors which influence decision making are outlined VP A75-33832 The multi-mission Mirage F Air International, vol 8, June 1975, p 285-291 The Mirage F swept wing fighter aircraft was designed as a A75-33620 HUD - An important new aid to the L S O R successor to the delta wing Mirage III The F1C has a landing L Brace (U S Navy, Washington, D C ) Society of Experimental approach speed of 160 mph, compared to the Mirage Ill's 210 mph Test Pilots, Technical Review, vol 12, no 3, 1975, p 51 55 The F1 has an advanced navigation and attack system, including a The tasks and responsibilities of the LSO (Landing Signal microminiaturized Cyrano IV radar which has a 40% better range Officer) are outlined, along with his demanding job requirements Attention is centered on one of the requirements which is paradoxial than the latest Mirage III radar The F1C is powered by an Atar in the sense that the LSO simply could not maintain visual contact 9K50 straight turbojet, its maximum speed is Mach 2 2 at high with an approaching aircraft and at the same time examine a mass of altitude and its service ceiling is 65,600 ft The F1E is powered by an panel mounted indicators An innovative solution to this paradox - M53 single-spool turbojet, which improves several performance the Heads Up Display (HUD) is described V P parameters significantly The armament of the F 1C and F1E consists of cannons and air to air missiles A detailed cutaway drawing of the Mirage F 1C is given ATS A75-33621 Rotor Systems Research Aircraft /RSRA/ C M Reme (United Aircraft Corp , Sikorsky Aircraft Div , Stratford, Conn ) Society of Experimental Test Pilots, Technical Review, vol A75-33931 * ;/' Computation of nonequihbrium three- 12, no 3, 1975, p 56-61 dimensional inviscid flow over blunt-nosed bodies flying at The RSRA was conceived by NASA and the U S Army as a supersonic speeds J V Rakich, H E Bailey, and C Park (NASA, versatile research aircraft for flight testing a wide variety of advanced Ames Research Center, Moffett Field, Calif ) American Institute of helicopter and compound rotor systems, such as variable-geometry, Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- variable-twist, and variable-diameter rotors The aircraft design, ference, 8th, Hartford, Conn , June 16-18, 1975, Paper 75-835 14 p handling qualities, flight control systems, stability augmentation 22 refs system, and force feel system are discussed V P A computer code based on the method of characteristics is
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described and applied to the study of two- and three-dimensional A75-33950 * # A rigorous solution of the Navier-Stokes equa- chemical nonequilibnum flow over sharp and blunt nosed bodies tions for unsteady viscous flow at high Reynolds numbers around Nonequilibrium flow over a wedge is used to show the approach to oscillating airfoils T Bratanow, H Aksu, and T Spehert (Wisconsin, equilibrium flow, and to demonstrate the nature of the reaction zone University, Milwaukee, Wis) American Institute of Aeronautics and behind the bow shock wave The structure and development of a Astronautics, Fluid and Plasma Dynamics Conference, 8th, Hartford, blunt-body entropy layer in nonequilibnum flow is examined for a Conn, June 16-18, 1975, Paper 75-863 12 p 11 refs Grant No blunt cone at zero incidence Three dimensional computations for NCR 50-007-001 the space shuttle body at 30 deg angle of attack are presented A A method based on the Navier-Stokes equations was developed nondimensional scaling parameter, the Damkohler number, which is for analyzing the unsteady incompressible viscous flow around the ratio of flow time to chemical reaction time, is calculated and its oscillating airfoils at high Reynolds numbers The Navier-Stokes significance discussed (Author) equations have been integrated in their classical Helmholtz vorticity transport equation form, and the instantaneous velocity field at each time step was determined by the solution of Poisson's equation A A75-33933 a Aerodynamic characteristics of an axisym refined finite element was utilized to allow for a conformable metric body undergoing a uniform pitching motion L H Smith and solution of the stream function and its first space derivatives at the R H Nunn (U S Naval Postgraduate School, Monterey, Calif ) element interfaces A corresponding set of accurate boundary American Institute of Aeronautics and Astronautics, Fluid and conditions was applied, thus obtaining a rigorous solution for the Plasma Dynamics Conference, 8th, Hartford, Conn, June 16-18, velocity field The details of the computational procedure and 1975, Paper 75-838 10 p 15refs examples of computed results describing the unsteady flow charac- An experimental investigation was conducted to determine the teristics around the airfoil are presented (Author) effect of a uniform pitching motion on a slender axisymmetric body while undergoing large excursions in angle of attack Force and A75-33951 ti A calculation method for unsteady subsonic moment measurements were obtained for a slender tangent- flow about harmonically oscillating wing-body configurations R ogive/cylmdncal body over a range of Reynolds numbers from Roos, B Bennekers, and R J Zwaan (National Luchtvaart 50,000 to 140,000 while varying the angle of attack from zero to 90 laboratonum, Amsterdam, Netherlands) American Institute of Aero- degrees and the pitch rate between zero and 281 degrees per second nautics and Astronautics, Fluid and Plasma Dynamics Conference, Smoke flow visualization studies were used as an aid in assessing 8th, Hartford, Conn , June 16 18, 1975, Paper 75-864 11 p 13 refs wake vortex transitions The results of the investigation show that Research supported by the Royal Netherlands Air Force there is an increment of normal force directly attributable to the A description is given of a panel method for the calculation of uniform pitching motion The incremental increase in the normal the aerodynamic loading on harmonically oscillating wing-body force is sufficient to cause significant errors in calculating body configurations in subsonic flow Neglecting their thickness, the damping derivatives from static force measurements Distinct wake loading on the lifting surfaces is assumed to be generated by a vortex transitions at approximately 20, 50 and 65 degrees were observed The effect of a uniform pitching motion shifts the angle of distribution of unsteady lifting lines The loads on the body are represented by an unsteady source panel distribution A way is attack at which these wake vortex transitions occur, and can reduce the abruptness of those transitions (Author) indicated to introduce the effect of the steady flow field into the unsteady calculations The method provides local and total coef- ficients as well as detailed pressure distributions on both the lifting surfaces and the bodies The applicability of the rnechod is shown in A75-33936 # A modern look at conformal mapping, includ- a comparison of calculated and experimental pressure and load ing doubly connected regions D C Ives (Grumman Aerospace distributions on a wing-tip tank-pylon store configuration (Author) Corp, Bethpage, N Y ) American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference, 8th, Hartford, A75-33952 ,7 Local momentum theory and its application to Conn , June 16-18, 1975, Paper 75 842 9 p 17 refs the rotarv wing A Azuma and K Kawachi (Tokyo, University, With the advent of large scale digital computers, numerical Tokyo, Japan) American Institute of Aeronautics and Astronautics, solution of the transonic flow equations in two dimensions has Fluid and Plasma Dynamics Conference, 8th, Hartford, Conn , June proven feasible In such calculations it is convenient, and often 16-18, 1975, Paper 75-865 12 p 39 refs crucial, to conformally map the region of interest onto a simple A new momentum theory, named local momentum theory, has domain so that a simple finite difference system can be employed been developed and applied to study the rotor aerodynamics The This paper updates a well known airfoil conformal mapping method theory is based on the instantaneous momentum balance with the (Theodorsen and Garrick) with modern techniques, greatly enhanc blade elemental lift at a local station of the rotor rotational plane A ing the mapping speed and accuracy while simplifying the analysis rotor blade is considered to be decomposed into a series of wings Also, a powerful new class of conformal transformations is in each of which has an elliptical circulation distribution and is so troduced, and applied to a two element airfoil (Author) arranged that a tip of each wing is aligned to the blade tip By neglecting the upwash flow outside the said wings and by introducing an attenuation coefficient to represent timewise change of the local induced velocity after an impact of blade passage, the induced velocity distribution and the spanwise aerodynamic loading of the A75-33938 * # The dynamics of atmospheric dust particles in blade can easily be obtained It will be shown that applying the new aircraft auxiliary power radial inflow turbines W B Clevenger, Jr theory to both steady and unsteady aerodynamic problems lead to and W Tabakoff (Cincinnati, University, Cincinnati, Ohio) fruitful results with much less computation time than the case of American Institute of Aeronautics and Astronautics, Fluid and using the vortex theory in which complexity of calculation and Plasma Dynamics Conference, 8th, Hartford, Conn, June 16-18, difficulty of convergence are unavoidable (Author) 1975, Paper 75-844 12 p 9 refs NASA supported research The results of analytical and experimental studies of the traiectones that atmospheric dust particles follow as they move A75-33953 * ff A three-dimensional solution of flows over through a radial inflow turbine are presented The study reveals the wings with leading-edge vortex separation J A Weber, G W Brune, nature of the impacts that occur within the turbine and indicates F T Johnson, P Lu, and P E Rubbert (Boeing Co , Seattle, Wash ) which surfaces are expected to experience the most severe erosion In American Institute of Aeronautics and Astronautics, Fluid and addition, a dimensionless parameter is derived which can be used Plasma Dynamics Conference, 8th, Hartford, Conn, June 16-18, during preliminary design analysis to indicate the sizes of the 1975. Paper 75-866 9p 13 refs Contract No NAS1-12185 particles that will be most damaging to the turbine (Author) The application of a new, general, potential flow computational
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technique to the solution of the subsonic, three dimensional flow thaatt increased towards the aft angles The results showed general over wings with leading edge vortex separation is presented The agreement with recent National Gas Turbine Establishment (IMGTE) present method is capable of predicting forces, moments, and st results obtained in a large wind tunnel (Author) detailed surface pressures on thin, sharp edged wings of rather arbitrary planform The wing geometry is arbitrary in the sense that A75-33957 * # Wind tunnel measurements of forward speed leading and trailing edges may be curved or kinked and the wing may effects on jet noise from suppressor nozzles and comparison with have arbitrary camber and twist The method employs an mviscid flight test data A Atencio, Jr (U S Army, Air Mobility Research flow model in which the wing, the rolled up vortex sheets, and the and Development Laboratory, NASA, Ames Research Center, wake are represented by piecewise continuous quadratic doublet Moffett Field, Calif ) American Institute of Aeronautics and sheet distributions The Kutta condition is imposed along all wing Astronautics, Fluid and Plasma Dynamics Conference, 8th, Hartford, edges Strengths of the doublet distributions as well as shape and Conn . June 16- 18. 1975, Paper 75-870 1 0 p 1 2 refs position of the free fortex sheet spirals are computed in iterative The results of a test program conducted in the NASA Ames 40- fashion starting with an assumed initial sheet geometry The method by 80-Foot Wind Tunnel to determine the effect of forward speed on is verified by numerous computed results (Author) the noise levels emanating from a conical ejector nozzle, a 32-spoke suppressor nozzle, and a 104-elhptical-tube suppressor nozzle are reported It is shown that noise levels are reduced as forward speed is A75-33954 ff A model for the dynamics of a separation increased and that, for one suppressor configuration, forward speed bubble used to analyze control-surf ace buzz and dynamic stall J D enhances suppression Comparisons of noise measurements made in Lang (U S Air Force Academy, Colorado Springs, Colo ) American the wind tunnel with those obtained in flight tests show good Institute of Aeronautics and Astronautics, Fluid and Plasma Dynam- agreement It is concluded that wind tunnels provide an effective ics Conference, 8th, Hartford, Conn, June 16 18, 1975, Paper means of measuring the effect of forward speed on aircraft noise 75-867 12 p 20 refs USAF-sponsored research (Author) A theory is developed which models separation bubble dynam- ics It includes a quasi-steady model for the external shear layer, and unsteady mass flow within the bubble at a mean reversed-flow A75-33960 # Finite element analysis of unsteady transonic velocity Pressure perturbations are related to the unsteady mass flux flow S T K Chan and M R Brashears (Lockheed Missiles and in a quasi-steady momentum equation Lag in growth and Space Co , Inc , Huntsville, Ala ) American Institute of Aeronautics modifications to the 'dead air' pressure of an unsteady bubble are and Astronautics, Fluid and Plasma Dynamics Conference, 8th, predicted and verified experimentally The experiments, on an airfoil Hartford, Conn, June 16-18, 1975, Paper 75875 10 p 9 refs with oscillating spoiler and flap, included a control surface buzz Contract No F33615 73-C-3144 analogy, where the flap and spoiler were mechanically coupled The finite element technique, in conjunction with the method Limit-cycle behavior was observed and is predicted by a theory of weighted residuals, is described herein for the analysis of transonic which includes the model for bubble growth (Author) flow about an airfoil executing harmonic motion The analysis is based on equations obtained from small disturbance theory, but with the transonic effects properly accounted for Investigations are A75-33955 * ft Maximum lift of upper surface blowing STOL conducted along the lines of utilizing both the methods of Galerkin aircraft with swept wings D G Koenig and K Aoyagi (NASA, Ames and least squares Preliminary findings to date are summarized, with Research Center, Moffett Field, Calif I American Institute of some numerical results shown for the Galerkm formulation A Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- computer code development based on the least squares method is in ference, 8th, Hartford. Conn , June 16-18. 1975, Paper 75-868 8 p progress, with comparison between the two codes to be made in 9 refs future studies (Author) In a recent large scale wind tunnel investigation of a 4 engine upper surface blowing configuration in the Ames 40- by 80-Foot Wind Tunnel, the large nacelles extending well above the wing upper A75-33961 ff Calculation of transonic flows using an surface had a sizable adverse effect on maximum lift The presence of extended integral equation method D Nixon American Institute of the nacelles produced high upwash angles between the nacelles and Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- near the fuselage The severity and alleviation of this problem is ference, 8th, Hartford, Conn , June 16-18, 1975, Paper 75-876 9 p discussed with the use of calculated spanwise loadings The combined 16 refs effects of wing leading edge stall control, wing sweep, and nacelle An extended integral equation method for transonic flows is cross section modification were considered in maximum lift improve- developed In the extended integral equation method velocities in the ment Experimental results of these effects are presented (Author) flow field are calculated in addition to values on the aerofoil surface, in contrast with the less accurate 'standard' integral equation method in which only surface velocities are calculated The results obtained A75-33956 « Effect of simulated forward flight on subsonic for aerofoils in subcritical flow and in supercritical flow when shock jet exhaust noise A B Packman and K W Ng (United Aircraft waves are present compare satisfactorily with the results of recent Corp , East Hartford, Conn ) American Institute of Aeronautics and finite difference methods (Author) Astronautics, Fluid and Plasma Dynamics Conference, 8th, Hartford, Conn , June 16-18, 1975, Paper 75-869 14 p 15 refs A wind tunnel model program was conducted to investigate the A75-33962 * # Transonic flow about a thick circular-arc effect of aircraft forward speed on the jet noise characteristics of a airfoil J B McDevitt, L L Levy, Jr, and G S Deiwert (NASA, single subsonic let Electrically heated air was supplied to a Ames Research Center, Moffett Field, Calif) American Institute of convergent nozzle located on the tunnel centerlme The nozzle Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- diameter of 2 4 in produced a tunnel to nozzle area ratio of 220 ference, 8th, Hartford, Conn , June 16-18, 1975, Paper 75-878 10 p Microphones were located at a radius of 50 nozzle diameters in the 14 refs anechoic chamber outside the tunnel flow Nozzle operating condi- An experimental and theoretical study of transonic flow over a tions covered a range of velocities up to 1669 fps, and temperatures thick airfoil, prompted by a need for adequately documented to 900 F Wind tunnel speeds ranged from near zero to 350 fps experiments that could provide rigorous verification of viscous flow Measured noise data were corrected for tunnel shear layer refraction simulation computer codes, is reported Special attention is given to and moving medium convection effects, thus simulating the effects the shock-induced separation phenomenon in the turbulent regime on the jet noise sources of relative velocity during an aircraft flyover Measurements presented include surface pressures, streamline and Measured overall sound pressure level reductions due to relative flow separation patterns, and shadowgraphs For a limited range of velocity were correlated with relative velocity raised to an exponent free-stream Mach numbers the airfoil flow field is found to be
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unsteady Dynamic pressure measurements and high-speed shadow- A75-33966 ti Some wind tunnel measurement of the trailing graph movies were taken to investigate this phenomenon Com- vortex development behind a sweptback wing - Induced rolling parisons of experimentally determined and numerically simulated moments on intercepting wings Z EI-Ramly, W J Rambird, and D steady flows using a new viscous-turbulent code are also included G Earl (Carleton University, Ottawa, Canada) American Institute of The comparisons show the importance of including an accurate Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- turbulence model When the shock boundary layer interaction is ference, 8th, Hartford, Conn , June 16 18, 1975, Paper 75-884 9 p weak the turbulence model employed appears adequate, but when 13 refs National Research Council of Canada Grant No A-7799 the interaction is strong, and extensive regions of separation are present, the model is inadequate and needs further development (Author) A75-33967 * fl Experimental study of the effect of span loading on aircraft wakes. V R Corsiglia, V J Rossow, and D L A75-33963 it An inverse method for the design of multiele- Ciffone (NASA, Ames Research Center, Moffett Field, Calif) ment high-lift systems J C Narramore and T D Beatty (Douglas American Institute of Aeronautics and Astronautics, Fluid and Aircraft Co , Long Beach, Calif) American Institute of Aeronautics Plasma Dynamics Conference, 8th, Hartford, Conn, June 16-18, and Astronautics, Fluid and Plasma Dynamics Conference, 8th, 1975, Paper 75-885 11 p 17 refs Hartford, Conn , June 16 18, 1975, Paper 75-879 8 p 6 refs Measurements were made in the NASA Ames 40- by 80 Foot Research sponsored by the McDonnell Douglas Independent Re- Wind Tunnel of the rolling moment induced on a following model in search and Development Program the wake 13 6 spans behind a subsonic transport model for a variety A multielement inverse potential flow program has been of trailing edge flap settings of the generator It was found that the developed which will determine the section geometry required to rolling moment on the following model was reduced substantially, Produce a desired upper-surface pressure distribution on one or more compared to the conventional landing configuration, by reshaping airfoils of a two-dimensional multielement airfoil system An the span loading on the generating model to approximate a span iterative procedure is used which modifies the camberlmes of bodies loading, found in earlier studies, which resulted in reduced wake on which the pressure is specified so that the calculated upper velocities This was accomplished by retracting the outboard trailing surface pressure distributions approach the desired pressure distribu- edge flaps It was concluded, based on flow visualization conducted tions Two options are available one which holds a constant in the wind tunnel as well as in a water tow facility, that this flap thickness while changing the camberlme and one which holds the arrangement redistributes the vorticity shed by the wing along the lower surface shape constant while changing the camberlme and span to form three vortex pairs that interact to disperse the wake thickness Both options require that the chord lengths and relative (Author) positions are held constant during the iterative procedure Examples of the results of the inverse process are presented which illustrate the A75-34112* Propulsion system structural integration and accuracy of the program and its potential application to the design of engine integrity. Proceedings of the Symposium, U S Naval Post- improved high-lift systems (Author) graduate School, Monterey, Calif, September 3-6,1974 Symposium sponsored by the U S Air Force, U S Navy, U S Army, and NASA Edited by W J Walker (USAF, Office of Scientific Research, A75-33964 * ? Supercritical airfoil flowfield measurements Washington, D C ) Journal of Aircraft, vol 12, Apr 1975 244 p F X Hurley, F W Spaid, F W Roos (McDonnell Douglas Research Current problems involving the structural integrity of propulsion Laboratories, St Louis, Mo ), L S Stivers, Jr, and A Bandettim systems, and proposed approaches to solving them, are reviewed (NASA, Ames Research Center, Moffett Field, Calif ) American Areas investigated include the stall hammershock at the engine inlet, Institute of Aeronautics and Astronautics, Fluid and Plasma Dynam distortion-induced vibration in fan and compressor blading, modeling ics Conference, 8th, Hartford, Conn, June 16 18, 1975, Paper engine static structures with conical-shell finite elements, design and 75-880 10 p 16 refs development of low-cost, self-contained bearing lubrication systems Detailed measurements in the transonic flowfield about a for turbine engines, and roller bearing slip and skidding damage Whitcomb-type supercritical airfoil profile are presented including SJ M surface pressure distributions, far wake surveys, spark schlieren photographs, and a series of vector velocity profiles in the boundary layer and in the near wake A flowfield composite for the transonic A75-34113 fj Structural integrity for propulsion systems J drag rise condition is constructed from these data The boundary E Zollinger (USAF, Aeronautical Systems Div , Wright Patterson layer measurements are compared with current correlation and AFB, Ohio) (US Air Force, US Navy, US Army, and NASA, computation schemes, and the importance of viscous thickening Symposium on Propulsion System Structural Integration and Engine effects is demonstrated by the results of wave drag rise calculations Integrity, Monterey, Calif, Sept 3-6, 1974 ) Journal of Aircraft, vol for the thickened and unthickened profiles (Author) 12, Apr 1975, p 195 197 Current problem areas, analytical capability, and experimental techniques regarding the structural integrity of propulsion systems A75-33965 * " Inviscid to turbulent transition of trailing are summarized In addition, an outline for future research and vortices J D Iversen (Iowa State University of Science and development efforts is given Emphasis is on the recent increase in Technology, Ames, Iowa) American Institute of Aeronautics and commercial and military problem events and the concomitant Astronautics, Fluid and Plasma Dynamics Conference, 8th, Hartford, necessity for development and application of better structural tools, Conn. June 16-18, 1975, Paper 75883 8 p 12 refs NASA- specifications, and tests S J M supported research The plateau region in which trailing vortices initially exhibit A75-34114 ft YF-16 air induction system design loads as- slow decay of maximum tangential speed is demonstrated with the sociated with engine surge P J Evans and P P Truax (General aid of constant and variable eddy viscosity models The existence of Dynamics Corp , Fort Worth, Tex ) (US Air Force, US Navy, US the plateau is explained by the presence of the viscous core and by Army, and NASA, Symposium on Propulsion System Structural the necessity for transition of the initial, nearly inviscid profile to Integration and Engine integrity, Monterey, Calif, Sept 3-6, 1974 ) similarity far downstream Span loading is shown to affect the initial Journal of Aircraft, vol 12, Apr 1975, p 205209 7 refs • maximum tangential speed as well as the duration of the plateau Basic data and procedures used to calculate structural loads due region Triangular span loading is shown to present less hazard to to engine surge on the YF-16 prototype fighter are presented The trailing aircraft, at least in the near field, than elliptic loading because procedure is based on a correlation of transient pressure vs engine- the inviscid profile for triangular loading exhibits a finite tangential compressor pressure ratio and relies heavily on extensive flight speed at the vortex centerlme and a large inviscid core (Author) measured transient-pressure data from engine surge events on F-111
335 A75-34115
aircraft equipped with Pratt and Whitney TF30 family engines These A75-34119 # Rapid verification of engine rotor and case data were supplemented and confirmed by theoretical calculations flexibilities by a modal comparison algorithm R A Marmol and J for the YF-16 and by test cell measurements of transient-pressure T Akin (United Aircraft Florida Research and Development Center, data from engine-surge events on the Pratt and Whitney West Palm Beach, Fla ) (US Air Force, US Navy, US Army,and F100-PW 100 engine, which is used in the YF 16 (Author) NASA, Symposium on Propulsion System Structural Integration and Engine Integrity, Monterey, Calif, Sept 3-6, 1974) Journal of Aircraft, vol 12, Apr 1975, p 242-246 5 refs A75-34115 # Review of hammershock pressures in aircraft A computation technique has been developed in which localized inlets L C Young and W D Beaulieu (Rockwell International dynamic flexibilities in an assembled rotor or case can be rapidly Corp, Los Angeles, Calif) (US Air Force, US Navy, US Army, determined from experimental mode shape and frequency data A and NASA, Symposium on Propulsion System Structural Integration dynamic mathematical model of the structure is developed with and Engine Integrity, Monterey, Calif, Sept 3-6, 1974 I Journal of empirical flexibility terms assigned to mechanical joints such as Aircraft, vol 12, Apr 1975, p 210216 15refs flanges, splines, couplings, etc The vibratory response of the Hammershock pressures caused by turbine engine stalls dictate structure is measured in laboratory tests and compared with the inlet duct structural design for high speed air vehicles The initial calculated values Agreement between calculated and experimental pulse strength is defined by the inlet airflow cutoff rate, engine mode shapes and frequencies is obtained by a computerized random bypass ratio, and cycle pressure ratio The inlet pressures are search technique, which determines the flexibility terms that influenced by the inlet duct volume and area distribution and produce the best match between experimental data and calculated attenuation of the engine stall pulse by bypass or boundary layer values for all of the vibration modes compared The technique was control air bleed from the duct The scarcity of experimental data developed for rotor critical speed applications, but it may be applied has inhibited in-depth hammershock analyses to date The B 1 to any simple or complex beam type structure (Author) Inlet/Engine Compatibility Test model had very extensive dynamic pressure instrumentation Deliberate engine stalls were made with off-design inlet geometry and/or by step engine fuel pulses Data are A75-34121 H Design and development of low-cost, self- utilized to show hammershock pressure propagation through the contained bearing lubrication systems for turbine engines G W inlet duct Test data will also be used to illustrate inlet design Hamburg, T D Moyer, R Smith, and R S Van Huysen (Teledyne, concepts for alleviation of transient pressure loads in the forward Inc. Teledyne CAE Div , Toledo, Ohio) (US Air Force, U S Navy, inlet region The B-1 inlet engine model test data enforce existing U S Army, and NASA, Symposium on Propulsion System Structural analytical and semiempincal hammershock prediction techniques Integration and Engine Integrity, Monterey, Calif, Sept 3-6, 1974 I (Author) Journal of Aircraft, vol 12, Apr 1975, p 253259 This paper discusses methods to simplify bearing lubrication systems for gas turbine engines The approaches presented are based A75-34116 # Control of gas turbine stator blade vibrations on experience in the development of a small turbojet engine for a by means of enamel coatings D I G Jones (USAF, Materials missile application During this development, the ability to operate Laboratory, Wright Patterson AFB, Ohio) and C M Cannon (Day- under a very hostile environment was demonstrated, the environment ton, University, Dayton, Ohio) (US Air Force, US Navy, US included accelerating from standstill to full speed in the order of 12 Army, and NASA, Symposium on Propulsion System Structural sec after cold soaking in a -60 F environment, accelerating to full Integration and Engine Integrity, Monterey, Calif, Sept 3-6, 7974 ) speed in less than half that time after hot soaking, running at Journal of Aircraft, vol 12, Apr 1975, p 226 230 AF Task 7351, temperatures experienced at speeds in excess of Mach 1, and AF Project 735106 operating at very high thrust loads The final thrust bearing This paper describes the application of a high temperature configuration involved a self-contained pot lube system, but a enamel coating to part of the surface area of the stator vanes of a jet grease-packed thrust bearing system was also successfully developed engine, to increase the damping and thereby reduce aerodynamically for a slightly less stringent set of operating conditions The induced resonant vibration failures The investigation showed that development of the companion grease-packed roller bearing, which such 3 coating can increase the damping level by a very significant operates in the hot turbine end environment, is also discussed amount, particularly when it is initially very low as when the blades (Author) are stalled, for example The use of enamel coatings is a relatively new approach to resolving jet engine vibration problems, and many engineering problems have to be overcome before all high tempera A 75-34123 H Current seal designs and future requirements ture vibrations are controllable Some of the engineering problems for turbine engine seals and bearings V P Povmelli, Jr (United are discussed (Author) Aircraft Corp, Pratt and Whitney Aircraft Div, East Hartford, Conn) (US Air Force, US Navy, US Army, and NASA, Symposium on Propulsion System Structural Integration and Engine A75-34118 ," Propulsion system and airframe structural in- Integrity, Monterey, Calif, Sept 3-6, 1974 I Journal of Aircraft, vol tegration program M N Aarnes and J L White (Boeing Commercial 12, Apr 1975, p 266273 16 refs Airplane Co , Seattle, Wash ) (US Air Force, US Navy, US Army, Turbine engine mamshaft seals are a significant factor in overall and NASA, Symposium on Propulsion System Structural Integration engine performance Each engine application presents a different set and Engine Integrity, Monterey, Calif, Sept 3-6, 1974 ) Journal of of requirements often dictating solutions that employ one or more of Aircraft, vol 12, Apr 1975, p 234242 I3refs the basic seal types ring seal, face seal, or labyrinth seal The aircraft The requirements for propulsion system and airframe structural turbine engines of the 1980's with corotational rotors will require integration are outlined The deficiencies in current practice are seals that can operate at pressure differentials within the 345 N/sq discussed and emphasis is placed on joint airframe and engine cm (500 psi) to 413 N/sq cm (600 psi) range, gas temperatures company participation in developing a comprehensive integration within the 922 K (1200 F) to 1032 K (1400 F) range and surface plan that will result in well defined system interfaces and a high level velocities within the 152 m/sec (500 fps) to 183 m/sec (600 fps) of risk awareness Structural analysis programs applicable to propul- range Currently developed seal systems demonstrate limited capa- sion system and airframe integration analysis are discussed including bility for meeting advanced requirements without imposing severe input automation and substructuring capabilities Examples of performance and system penalties rvlainshaft bearings for these propulsion system and airframe math models and typical substruc- advanced engine applications will require operation in the 2 5 to 3 0 • tures are presented including static structure and rotating com million DN level range Of the two basic bearing types employed, ball ponents The importance of propulsion system loads is discussed thrust and cylindrical roller, the latter presents the most challenge Applications of general purpose structural analysis programs such as Additional bearing and mamshaft seal development is required to NASTRAN to propulsion system structure are given (Author) meet the requirements of tomorrow's aircraft engines (Author)
336 A75-34134
A75-34127 /? High-speed rotor dynamics - An assessment of Aircraft Div , East Hartford, Conn ) (US Air Force, US Navy, US current technology for small turboshaft engines J M Vance Army, and NASA, Symposium on Propulsion System Structural (Florida, University, Gainesville, Fla ) and A C Royal (U S Army, Integration and Engine Integrity, Monterey, Calif, Sept 36, 1974) Air Mobility Research and Development Laboratory, Fort Eustis, Journal of Aircraft, vol 12, Apr 1975, p 325332 14 refs Contract Va ) (US Air Force, US Navy, US Army, and NASA, Symposium No N00019-72-C-0187 on Propulsion System Structural Integration and Engine Integrity, A unified approach to flutter prediction has been developed, in Monterey. Calif, Sept 3-6, 1974) Journal of Aircraft, vol 12, Apr which aeromechamcal stability of the blade-disk system is expressed 1975, p 295-305 61 refs in terms of a stability parameter which measures the amount of An extensive study was made to determine current needs for unsteady work done by the air on the system, when the system is research in rotor dynamics to solve problems encountered in small vibrating in one of its natural modes In neutrally stable systems, the high speed turboshaft engines for helicopter and aircraft propulsion unsteady work done by the air on the blades will balance the work The purpose of this paper is to report the state of-the-art for this area dissipated by friction and by material damping An accurate as completely and concisely as possible The present and past prediction of the vibrational deflections and of the unsteady philosophy of rotor-bearing system design including the impact of aerodynamic forces is required at every spanwise location on each the demand for front drives, is discussed Methods for critical speed blade, so that the work done by the unsteady aerodynamic forces prediction and high-speed balancing are reviewed The trend to may be calculated Recent progress is described in the prediction of higher speeds is seen to require consideration of new approaches to unsteady aerodynamic forces and the determination of mode shapes balancing through flexural modes The major parameters available for The stability model is applied to the prediction of supersonic flutter, control by the designer are shown to be the bearing support chordwise bending flutter, and stall flutter (Author) properties, and recommendations are made for improving the accuracy of prediction of these properties (Author)
A75-34132 # Blade vibration - Some key elements in design A75-34128 ft Dynamic response of viscous damped multi- verification C E Danforth (U S Air Force, U S Navy, U S Army, shaft jet engines D H Hibner (United Aircraft Corp, Pratt and and NASA, Symposium on Propulsion System Structural Integration Whitney Aircraft Div , East Hartford, Conn ) 'US Air Force, US and Engine Integrity, Monterey, Calif, Sept 3-6, 1974 > Journal of Navy, US Army, and NASA, Symposium on Propulsion System Aircraft, vol 12, Apr 1975, p 333-342 5 refs Structural Integration and Engine Integrity, Monterey, Calif, Sept The paper outlines in some detail two key considerations (1) 36, 1974) Journal of Aircraft, vol 12, Apr 1975, p 305312 12 the assessment at a given operating point of compressor and fan refs blade vibration in relation to high-cycle fatigue, and (2) the Rotor synchronous vibration experienced on multi shaft aircraft identification of engine operating points worst for blade vibration engines results directly from rotor imbalance exciting the numerous An illustrative distillation is given of hitherto unpublished per- critical speeds inherent in lightweight, high-speed modern power spectives in blade stress, dynamics, and their experimental sensing as plants The understanding and reduction of this dynamic response is required for effective design and validation of modern bladmg A essential during engine design and development phases This paper deliberate effort is made to illustrate design and design verification presents an efficient analytical technique capable of predicting the significance of blade dynamics, and increasingly three-dimensional vibratory response of an engine with nonlinear viscous damping A stress distributions and levels as derived from precision experiments unique transfer-matrix method is applied to the idealized equivalent and massive numerical analysis investigations For example, local engine system to produce an unusually small array of influence time-average stresses three times elementary treatment levels, as coefficients The damper equations for a closed-end viscous damper generated by the interaction of blade twist, camber, and rim are derived from the basic Reynolds equation The analysis is applied overhang, are indirectly capable of causing fatigue failures, attrib- to a two-shaft aircraft engine to illustrate the basic concepts of utable to nonexistent 'mystery' vibration The effectiveness of design multi-shaft critical speeds and nonlinear viscous-damped response verification in extensive simulated flight tests can be enhanced by a (Author) systematic identification of operating conditions 'worst' for blade vibration Illustrative examples are given for blade vibration, both stable and self-excited (Author) A75 34130 # Philosophy, design, and evaluation of soft- mounted engine rotor systems N Magge (General Electric Co, Aircraft Engine Group, Lynn, Mass) (US Air Force, US Navy, U S Army, and NASA, Symposium on Propulsion System Structural A75-34134 # F100 fan stall flutter problem review and Integration and Engine Integrity, Monterey, Calif, Sept 3-6, 1974) solution J D Jeffers, II and C E Meece, Jr (United Aircraft Journal of Aircraft, vol 12, Apr 1975, p 318324 9 refs Grants Florida Research and Development Center, West Palm Beach, Fla ) No DAAJ01-72C-0381, No DAAJ02-71-C-0050 No DAAJ02-68 (US Air Force, US Navy, US Army, and NASA, Symposium on C-0002 Propulsion System Structural Integration and Engine Integrity, In the present paper, the design philosophy, criteria, and Monterey, Calif, Sept 3-6, 1974 ) Journal of Aircraft, vol 12, Apr methods of evaluation for soft-mounted turbine-engine rotor systems 1975, p 350357 6 refs used in aircraft engine design are described A major constituent of An experimental investigation was conducted to examine an this method is a computer program for system vibration and static airfoil durability problem in the first fan rotor of the F100 engine analysis (VAST) This program is capable of finding natural This study incorporated laboratory and simulated engine flight tests, frequencies, normalized modes, and responses due to any distribu an empirical correlation of aeroelastic stability parameters from tion of exciting forces considering gyroscopic and shear-deflection engine test data, and substantiation testing of the redesign The effects Aircraft mounting and excitations from the helicopter rotor results of this investigation's initial testing showed that rotor failure are also included in the computer analysis General Electric's T700 at high-flight Mach numbers and low altitudes was caused by turboshaft engine serves to illustrate the squeeze film, soft-mounting torsional stall flutter instability The results of the empirical concept of design Results from tests of the T700 engine, Advanced correlation indicated that a design free of flutter required a decrease Technology Axial Centrifugal Compressor (ATACC), T64 turboshaft, in both normalized incidence and reduced velocity Further, the TF34 turbofan, and other engines are summarized, verifying the correlation indicated that the flutter was affected by inlet pressure, a advantages of soft-mounted rotor systems (Author) heretofore undocumented phenomenon The results of the sub- stantiation testing confirmed that the redesign made the rotor A75-34131 # Advances in fan and compressor blade flutter flutter-free throughout the entire aircraft flight envelope It was analysis and predictions A A Mikolajczak, R A Arnoldi, L E concluded that an improved stall flutter analysis was required to Snyder, and H Stargardter (United Aircraft Corp , Pratt and Whitney ensure stable fan and compressor rotor designs (Author)
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A75-34137 # Turbine Engine Structural Integrity Program As a step toward a better understanding of engine burst /ENSIP/ W D Cowie (USAF, Aeronautical Systems Div , Wright containment and ascertaining practical shield requirements, a large Patterson AFB, Ohio) (US Air Force, US Navy, US Army, and deflection shell computer program has been modified to model NASA, Symposium on Propulsion System Structural Integration and fragment impact, simultaneously calculate the motion of the Engine Integrity, Monterey, Calif, Sept 3-6, 1974) Journal of fragment and shield and predict perforation Recent test data Aircraft, vol 12, Apr 1975, p 366369 indicates that substantial savings in engine burst containment shield The Turbine Engine Structural Integrity Program (ENSIP) was weight may be possible by the use of ballistic fabrics In metal shields established by the Air Force to provide the framework from which the dissipation of fragment kinetic energy is due to compressive and an engine contractor can derive a well-ordered structural develop- shear deformation in the impact region followed by extensive ment program to meet Air Force needs ENSIP's background and bending and stretching deformation due to structural excitation In highlights are presented as well as the concept details Some effects contrast, a fabric shield dissipates the energy almost wholly by of the concept on existing programs are discussed The paper is tensile deformation The mechanical energy is distributed relatively concluded with a brief list of new criteria which are under rapidly throughout the shield as a result of the fabric's high wave consideration to refine or update the present program (Author) speed and membrane response Encouraging results were found in analytical comparisons with experimental data (Author) A75-34139 " Low-cycle fatigue and creep analysis of gas turbine engine components S Majumdar (Argonne National Labora- A75-34142 # Design of fabricated static structures for long tory, Argonne, III ) (US Air Force, US Navy, US Army, and cyclic life A Coles, C K Coombs, and H G Popp (General Electric NASA, Symposium on Propulsion System Structural Integration and Co , Cincinnati, Ohio) (US Air Force, US Navy, US Army, and Engine Integrity, Monterey, Calif, Sept 3-6, 1974) Journal of NASA, Symposium on Propulsion System Structural Integration and Aircraft, vol 12, Apr 1975, p 376-382 Engine Integrity, Monterey, Calif, Sept 36, 1974) Journal of The factors that determine the damage of aircraft engines due to Aircraft, vol 12, Apr 1975, p 394-399 low cycle fatigue and creep during service are the numbers and rate High performance, lightweight jet engines, which are designed of transient acceleration and deceleration, operating ambient tem- for relatively low cost production and long life requirements, place perature, time at temperature, and amount of time at over stringent restrictions on material utilization Static structure design temperatures The present paper attempts to define a method for criteria require that tensile, creep, and cyclic life limits be met predicting this engine damage and establishing the critical engine However, the long operational lifetimes require increased accuracy parameters to be monitored in conjunction with either an on-board and reliability of material data and analysis methods In addition, the computer or a suitable recording system that can be used on a central widespread use of welded sheet fabricated structures has emphasized computer at the conclusion of a flight An analytical study is made the need for quality control of manufacturing processes and for a of a typical fan engine to show the important engine operating viable defect-tolerance approach to cyclic life prediction A design parameters leading to limiting the useful engine life due to (1) method which is based on the fracture mechanics approach is low-cycle fatigue in the fan turbine disk and (2) the combination of presented Both material and geometric imperfections are considered, low-cycle fatigue and creep in the high-pressure turbine blades and and guidelines are presented to achieve safe lifetimes for lightweight vanes The leading edge of both the high-pressure turbine blade and welded structures (Author) the inlet vane was found to be a critical element The analysis shows that stress concentration due to the presence of cooling holes in the blade should be examined for low-cycle fatigue failure (Author) A75-34143 # Turbine airfoil life prediction by mission analysis M T Loferski (United Aircraft Corp , Pratt and Whitney A75-34140 # Fracture failure modes in lightweight bearings Aircraft Div , East Hartford, Conn ) (US Air Force, US Navy, US J C Clark (General Electric Co, Cincinnati, Ohio) (US Air Force, Army, and NASA, Symposium on Propulsion System Structural U S Navy, U S Army, and NASA, Symposium on Propulsion Integration and Engine Integrity, Monterey, Calif, Sept 3-6, 1974} System Structural Integration and Engine Integrity, Monterey, Calif, Journal of Aircraft, vo\ 12, Apr 1975, p 400-402 Sept 3-6, 1974 ) Journal of Aircraft, vol 12, Apr 1975, p 383-387 Increasing design complexity and cost have required an accurate 6refs life-prediction technique which would possess rapid computation A series of sixteen bearings operated with tensile stresses in the time and still account for the life-determining variables A method is races were analyzed for cracks Ten of the sixteen bearings generated described which analyzes the life expectancy of turbine parts by cracks of critical size resulting in rapid fracture of the races From simulating airplane and engine performance, and incrementally these data, an estimate is made of the critical stress intensity factor calculating heat transfer and loading on those parts This method has for AISI 52100 and AISI M-50, the materials currently used in been successfully used to predict life in field service and to develop aircraft engine bearings Flaws are generated in the races apparently turbine hardware through accelerated endurance testing Future due to a combination of tensile hoop stress and the superimposed applications of the mission analysis are described for real-time Hertz stress pattern An attempt was made to correlate the flaw size prediction systems and maintenance planning (Author) and shape to the known stress field, or components of the stress field, but currently these have not been completely successful Using relatively simple, established fracture-mechanics techniques, a A7S-34146 # Dynamic simulator for advanced gas turbine limiting stress level can be determined for a given flaw size, but engine component tests R A Cundiff, R H Badgley (Mechanical experimental data must be relied upon to predict the flaw size, Technology, Inc , Latham, NY), and J Reddechff (United Aircraft particularly the depth of the flaw By proper design, the stresses can Corp , Pratt and Whitney Aircraft Div , West Palm Beach, Fla I (US be maintained at sufficiently low levels to preclude rapid fracture in Air Force, US Navy, US Army, and NASA, Symposium on the outer races The area of concern arises in engines of the future Propulsion System Structural Integration and Engine Integrity, with increased rotor speeds which will generate high hoop stresses in Monterey, Calif, Sept 3-6, 1974 ) Journal of Aircraft, vol 12, Apr the bearing inner races (Author) 1975, p 423-430 11 refs Contract No F33615-72-C-1801 A rotor-bearing system has been designed and manufactured to A75-34141 H Analysis of rotor fragment impact on ballistic be dynamically representative of an entire class of gas-turbine fabric engine burst containment shields J H Gerstle (Boeing engines the two-spool front-drive, power-turbine engine, which is Commercial Airplane Co, Seattle, Wash) (US Air Force, US widely used in helicopter applications The test-rig configuration, Navy, US Army, and NASA, Symposium on Propulsion System with the addition of low-pressure compressor and fan simulator Structural Integration and Engine Integrity, Monterey, Calif, Sept disks, would be dynamically representative of the turbojet and 3-6, 1974) Journal of Aircraft, vol 12, Apr 1975, p 388393 20 turbofan classes of engines, respectively The apparatus has been refs utilized for initial evaluation of air-lubricated intershaft foil bearings.
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and for demonstration of an advanced balancing procedure For and detachment lines can be calculated The solution procedure these tests, the shaft was operated on elastically-mounted ball permits the incorporation of a wide variety of turbulent models and bearings without support damping over a speed range encompassing boundary conditions including entropy layer procedures, specified two bending critical speeds Rotor balancing via the recently- surface temperatures or heat flux distributions, surface catalysis, developed multiplane-multispeed balancing procedure was used to mass addition, and the coupling to both three-dimensional mviscid suppress both the first bending critical speed and a pedestal codes and surface ablation codes In addition, reasonable computing resonance, and to leave a distinct vibration peak at the second times are obtained (Author) bending critical speed An air-lubricated intershaft foil bearing of the hydrodynamic, resihently-supported type proved to be capable of raising the second critical speed above the normal operating speed A75-34193 * f! Transonic potential flow calculations using range of the power turbine shaft (Author) conservation form A Jameson (New York University, New York, NY) In Computational Fluid Dynamics Conference, 2nd, Hartford, Conn , June 19, 20, 1975, Proceedings A75-34147 # Systematic development testing for engine New York, American Institute of Aeronautics and Astronautics, Inc , structural integrity assurance E M Spear and R F French (General 1975, p 148-161 21 refs Grants No NCR 33-016-167, No Electric Co, Cincinnati, Ohio) (US Air Force. US Navy, US NGR-33-016-201, Contract No AT(11-1) 3077 Army, and NASA. Symposium on Propulsion System Structural A method is presented for the solution of the full potential Integration and Engine Integrity, Monterey, Calif, Sept 36, 1974) equation in conservation form This assures that a weak solution Journal of Aircraft, vol 12, Apr 1975, p 431-436 satisfying proper isentropic jump conditions is obtained, giving an The primary objectives of General Electric's development test improved representation of shock waves in comparison with earlier programs are to verify the basic design and then demonstrate that the nonconservative schemes The method uses the concept of artificial engine, including the individual components, has adequate life and viscosity to produce a stable difference scheme in the supersonic integrity under all operating conditions to which it could be exposed zone, and artificial time to generate a convergent iterative scheme for in customer service The successful attainment of these objectives the solution of the difference equations Results of calculations using requires balanced test programs The programs must consider all the nonconservative and conservative schemes are compared phases of testing from the initial preliminary design models through (Author) flight testing of the engine Emphasis is placed on real life operating environment and accelerated life testing The paper discusses General Electric's approach to systematic test planning Examples of these programs from preliminary design components through engine life and reliability demonstrations are provided (Author) A75-34194 * n A fast semidirect method for computing tran- sonic aerodynamic flows E D Martin (NASA, Ames Research Center, Computational Fluid Dynamics Branch, Moffett Field, A75-34186* # Use of numerically generated body fitted co- Calif ) In Computational Fluid Dynamics Conference, 2nd, ordinate systems for solution of the Navier-Stokes equations J F Hartford, Conn , June 19, 20, 1975, Proceedings Thompson, C W Mastm (Mississippi State University, Mississippi New York, American Institute of Aeronautics and Astronautics, Inc , State, Miss ), F C Thames (LTV Aerospace Corp , Dallas, Tex ), and 1975, p 162-174 40 refs S P Shanks In Computational Fluid Dynamics Conference, 2nd, A fast, semidirect, iterative computational method, previously Hartford, Conn , June 19, 20, 1975, Proceedings introduced for finite difference solution of subsonic and slightly New York, American Institute of Aeronautics and Astrondutics, Inc , supercritical flow over airfoils, is extended both to apply to strongly 1975, p 68-80 11 refs Grant No NGR-25-001 055, Contract No supercritical conditions and to include full second order accuracy in N00014-74-C-0373-P0001 computing mviscid flows over airfoils The nonlinear small- A procedure for numerical solution of the time-dependent, disturbance equations are solved iteratively by a direct, linear, elliptic two-dimensional incompressible Navier-Stokes equations that can solver General, fully conservative, type dependent difference equa- treat the unsteady laminar flow about bodies of arbitrary shape, such tions are formulated, including parabolic- and shock-point transition as two-dimensional airfoils, multiple airfoils, and submerged hydro- operators that provide consistency with the integral conservation foils, as naturally as it can deal with the flow about simple bodies laws These equations specialize to either first-order or to fully The solution is based on a method of automatic numerical generation second-order-accurate equations Various free parameters are eval- of a general curvilinear coordinate system with coordinate lines uated for rapid convergence of the first-order scheme Resulting coincident with all boundaries of a general multiconnected region pressure distributions and computing times are compared with the containing any number of arbitrarily shaped bodies The curvilinear improved Murman Cole line relaxation method (Author) coordinates are generated as the solution of two elliptical partial differential equations with Dinchlet boundary conditions, one coordinate being specified to be constant on each of the boundaries, A75-34195 * tj Transonic airfoil analysis and design using and a distribution of the other being specified along the boundaries Cartesian coordinates L A Carlson (Texas A & M University, The solution compares excellently with the Blasius boundary layer College Station, Tex ) In Computational Fluid Dynamics Con- solution for the flow past a semunfinite flat plate S J M ference, 2nd, Hartford, Conn , June 19, 20, 1975, Proceedings New York, American Institute of Aeronautics A75-34190 * H Computational procedure for three- and Astronautics, Inc, 1975, p 175-183 18 refs Grant No dimensional boundary layers on aircraft and aerospace vehicles R NCR 44-001 157 M Kendall, W S Bonnett, C T Nardo, and M J Abbett (Acurex An inverse numerical technique for designing transonic airfoils Corp, Mountain View, Calif) In Computational Fluid Dynamics having a prescribed pressure distribution is presented The method Conference, 2nd, Hartford, Conn, June 19, 20, 1975, Proceedings uses the full potential equation, inverse boundary conditions, and New York, American Institute of Aeronautics Cartesian coordinates It includes simultaneous airfoil update and and Astronautics, Inc, 1975, p 113123 10 refs Contract No utilizes a direct-inverse approach that permits a logical method for NAS1 12424 controlling trailing edge closure The method can also be used for the An implicit numerical procedure is developed to solve the full analysis of flowfields about specified airfoils Comparison with three-dimensional laminar, boundary layer equations over realistic previous results shows that accurate results can be obtained with a aircraft and spacecraft configurations This procedure utilizes splmed Cartesian grid Examples show the application of the method to functions in the direction normal to the surface and finite differences design aft-cambered and other airfoils specifically for transonic in the cross flow direction Calculation of off-pitch plane attachment flight (Author)
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A75 34196 * # Computer simulation of transonic flow past A75-34272 * General analysis of the diffraction pattern for airfoils with boundary layer correction F Bauer and D Korn (New a plane acoustic wave at a wedge moving at supersonic speed York University, New York, NY) In Computational Fluid Dy (Obshchn analiz kartmy difraktsn ploskoi akusticheskoi volny na namics Conference, 2nd, Hartford, Conn, June 19, 20, 1975, klme, dvizhushchemsia so sverkhzvukovoi skorosti'iu) A V Pana- Proceedings New York, American Institute of senko Akademiia Nauk SSSR, Izvestna, Mekhanika Zhidkosti i Gaza, Aeronautics and Astronautics, Inc , 1975, p 184204 15refs Grant Mar-Apr 1975, p 172-175 5 refs In Russian No NGR-33 016-167, Contract No AT(11-1)3077 A computer program has been developed to solve the com- pressible flow equation for the velocity potential The exterior of the A75-34299 fi Aircraft dynamics - What pilots never ask J airfoil is mapped onto the unit circle and the flow is computed on a D Enckson (FAA, Southwest Regional Office, Fort Worth, Tex ) grid in the circle plane A relaxation method using backward AIAA Student Journal, vol 13, Spring 1975, p 10-13 differencing in the flow direction at supersonic points permits Dynamic testing of aircraft response is examined Methods are solutions for large supersonic areas The pressure distribution described for exciting, observing, and recording phygoid response resulting from the flow becomes the input to the von Karman and short-period oscillation as well as the roll, spiral, and Dutch-roll momentum equation which when integrated gives the displacement modes Acceptable damping ratios are provided, and precautions are thickness This displacement thickness is smoothed and added to the given for conducting the tests using pilot-induced control displace- airfoil to account for the turbulent boundary layer The boundary ments F G M layer correction is computed iteratively with the flow Results from this program and test data agree well (Author) A75-34535 * Simulator evaluation of manually flown curved MLS approaches D Sager (Mitre Corp , McLean, Va ) In International Conference on Systems, Man, and Cybernetics, Dallas, Tex, October 24, 1974, Proceedings New A75-34203 The effect of water path variations on ultra- York, Institute of Electrical and Electronics Engmeeis, Inc , 1974, p tonic through-transmission sensitivity C J Palmer (McDonnell 104-109 Grant No NGL22009640 Aircraft Co , St Louis, Mo ) (American Society for Nondestructive Pilot performance in flying horizontally curved instrument Testing, National Fall Conference, Detroit, Mich , Oct 21-24, 1974 ) approaches was analyzed by having nine test subjects fly curved Materials Evaluation, vol 33, June 1975, p 128-132,134 approaches in a fixed base simulator Approaches were flown The through-transmission C-scan method employing focused without an autopilot and without a flight director Evaluations were search units in squirter nozzles is used to ultrasonically inspect vertical, rudder and horizontal stabilator torque boxes for typical based on deviation measurements made at a number of points along fighter aircraft as well as composite wing skins for development the curved approach path and on subject questionnaires Results programs Figure 1 shows the location of the composite assemblies indicate that pilots can fly curved approaches, though less accurately on the aircraft The ultrasonic test is applied in addition to film than streight in approaches, that a moderate wind does not seriously radiography to detect disbonds and other anomalies in these affect curve flying performance, and that there is no major honeycomb structures that have airfoil shapes The purpose of this performance difference between 60 and 90 deg turns (Author) study is to evaluate the effect of variations of water path on the relative size or sensitivity of the C-scan images obtained using this ultrasonic test method (Author) A75-34536 International and U S design proposals for a microwave landing system S A Meer and S R Jones (Mitre Corp , McLean, Va ) In International Conference on Systems, Man, and Cybernetics, Dallas, Tex, October 24, 1974, Proceedings A75-34245 ft A method for calculating flows through plane New York, Institute of Electrical and Electronics airfoil lattices (Ob odnom sposobe rase he ta obtekanna ploskikh Engineers, Inc, 1974, p 150-160 8 refs reshetok profilei) G I Chmyr', A Sh Asaturian, and A M This paper describes the preliminary designs being proposed to Kuzemko (Zaporozhskii Mashmostroitel'nyi Institut, Zaporozhe, the International Civil Aviation Organization (ICAO) by the five Ukrainian SSR) Pnkladnaia Mekhanika, vol 11, Apr 1975, p countries having development programs on a new precision approach 83-88 7 refs In Russian and landing system The Australian, U K and U S Systems are all In the method proposed, the computation of the flow through a 'air derived' and use the C-Band for the main functions of azimuth plane cascade is reduced to solving an integral equation A method, and elevation Differences in these designs exist both in the use of termed the method of averaging functional corrections, proposed for Doppler or scanning beam concepts and in the use of time or solving the equation provides analytical expressions for the velocity frequency multiplexing of the azimuth and elevation signals The potential and for the velocity of the potential flow through the French and German designs derive the angle information on the cascade Analytical representation of the blade profile (required in ground and transmit it to the aircraft via a data link The French are the application of the method) is obtained with the aid of Chebyshev proposing either an interferometric or a Doppler-effect reception polynomials A numerical example problem is solved on a computer technique, while the German approach is to employ the L-B and VP DME The signal formats, ground systems, and avionics features of each design are described Design parameters that influence system performance in terms of accuracy, integrity and implementabihty are identified (Author) A75-34262 H Calculation of the separated flow at a thin- section wing of finite span (Raschet otryvnogo obtekanna tonkogo kryla konechnogo razmakha) S M Belotserkovskii, M I Nisht, and A75-34537 Involving the expert and aviation community 0 N Sokolova Akademiia Nauk SSSR, Izvestna, Mekhanika in the decision making structure of the U S MLS program G Jensen Zhidkosti i Gaza, Mar -Apr 1975, p 107-112 8 refs In Russian (FAA, Systems Research and Development Service, Washington, Approaches proposed by Belotserkovskii (1968, 1974) to the DC) In International Conference on Systems, Man, and Cyber solution of steady and unsteady nonlinear problems involving netics, Dallas, Tex, October 24, 1974, Proceedings attached flows are adapted to the analysis of separated flows at wings New York, Institute of Electrical and Electronics of arbitrary planform Motions of a thin lifting surface in an Engineers, Inc, 1974, p 161 165 5 refs incompressible medium, accompanied by the trailing off of vortex This paper describes the decision making structure being used to sheaths both from the trailing and leading edges are examined V P define the U S microwave landing system (MLS) design that will be
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offered to the International Civil Aviation Organization for con air fuel ratios Thereby the large quantities of NO produced at sideration as the new standard replacing the existing instrument adiabatic peak temperatures are omitted and soot formation as a landing system (ILS) Essential prerequisites of such an offering result of low velocity droplet combustion is avoided Tests with a include thoroughness in the underlying technical work and agree combustor incorporating the fuel injection system yielded high ment by the user community that the new system is responsive to its combustion efficiencies, improved combustor outlet temperature diverse requirements in a cost effective manner The basic charac- distributions and low pollutant emissions Comparing the measured teristics of a landing system are determined by the technique on emission indices for CO, NO, and unburned HC with values required which it is based and the design of the signal structure (signal for civil aircraft engines showed a promising development potential format) Wide acceptance of a system requires that the development of achieving the standards (Author) and user groups mutually agree on these fundamental design choices This calls for open, participative communication between these groups while the system decisions are being made (Author) A75 34573 -I Surge and rotating stall in axial flow com pressors I Theoretical compression system model E M Greitzer (United Aircraft Corp, Pratt and Whitney Aircraft Div, East A75-34539 Air traffic controllers' operative effectiveness Hartford, Conn ) American Society of Mechanical Engineers, Gas under NAS environments W Siddiqee, G J Couluns, and D K Turbine Conference and Products Show, Houston, Tex , Mar 26 Schmidt (Stanford Research Institute, Menlo Park, Calif I In 1975, Paper 75-GT-9 9 p 13 refs Members, SI 00, nonmembers, International Conference on Systems, Man, and Cybernetics, Dallas, S3 00 Tex, October 2-4, 1974, Proceedings New This paper reports a theoretical study of axial compressor surge York, Institute of Electrical and Electronics Engineers, Inc. 1974 p 175-179 A nonlinear model is developed to predict the transient response of a compression system subsequent to a perturbation from steady In this paper the usefulness of various features of national operating conditions It is found that for the system investigated airspace system (MAS) stage A eg, automated flight data there is an important nondimensional parameter on which this processing, automatic altitude reporting (mode C), automated radar response depends Whether this parameter is above or below a critical target tracking and automatic handoff capabilities in enhancing the value determines which mode of compressor instability, rotating stall effectiveness of controllers in the air route traffic control centers or surge, will be encountered at the stall line For values above the (ARTCC) is critically reviewed Aspects of failure effect considera- critical, the system will exhibit the large amplitude oscillatory tions that may limit a controller's effectiveness are discussed Results behavior characteristic of surge, while for values below the critical it of a few field measurements and interviews with controllers are %lso_ will move toward operation in rotating stall, at a substantially reported Recommendations are made that might be helpful in reduced flow rate and pressure ratio Numerical results are presented improving further effectiveness of controllers (Author) to show the motion of the compression system operating point during these two basic modes of instability, and a physical explanation is given for the mechanism associated with the genera- A75-34S66 * H Three dimensional characteristics of turbulent tion of surge cycle oscillations (Author) wakes behind rotors of axial flow turbomachinery R Raj and B Lakshmmarayana (Pennsylvania State University, University Park, Pa ) American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston, Tex, Mar 2-6, 1975, A75-34575 * ft Rotor burst protection program - Statistics on Paper 75-GT-1 10 p 12 refs Members, S1 00, nonmembers, S3 00 aircraft gas turbine engine rotor failures that occurred in U S Contract No NAS3-17855 commercial aviation during 1973 G J Mangano and R A DeLucia (US Naval Air Propulsion Test Center, Trenton, NJ) American Society of Mechanical Engineers, Gas Turbine Conference and A75-34567 ft Ground vortex - Limit to engme/reverser Products Show, Houston, Tex , Mar 2-6, 1975, Paper 75 GT-12 4 p operation D L Motycka (United Aircraft Corp , Pratt and Whitney Members, Si 00, nonmembers, S3 00 NASA-sponsored research Aircraft Div , East Hartford, Conn ) American Society of Mechanical This paper presents statistical information on the aircraft gas Engineers, Gas Turbine Conference and Products Show, Houston, turbine engine rotor failures that occurred in U S commercial Tex, Mar 26, 1975, Paper 75-GT-3 6 p Members, SI 00, aviation during 1973 Based on FAA data, results are presented that nonmembers, $300 establish (1) the incidence of rotor failure, (2) the type of fragments It has been commonly accepted that engine stalls during reverser generated, (3) whether or not these fragments were contained, (4) operation are caused by the temperature distortion created by the causes of failure, (5) where in the engine failure occurred, (6) remgested exhaust gases Recent studies have shown that com- what engines were affected, and (7) what flight conditions prevailed pressors respond to instantaneous inlet distortions of a time duration at failure The rate of uncontamed rotor burst was considered to be on the order of one engine revolution This paper describes the significantly high (Author) results of a test of a high bypass ratio engine during reverse thrust operation which revealed, through the use of high response tempera- ture and pressure measurement, that instantaneous distortions caused by an induced ground vortex were the cause of engine stalls (Author) A75-34576 # Study on the mechanism of stall margin improvement of casing treatment H Takata (Tokyo, University, A75-34570 ft Experimental investigation of a new concept Tokyo. Japan) and Y Tsukuda (Mitsubishi Heavy Industries, Ltd , of fuel prevaponzatton G Kappler, G Kirschey, and A Fehler Takasago, Hyogo, Japan) American Society of Mechanical En (Munchen Techmsche Hochschule, Munich, West Germany) gmeers. Gas Turbine Conference and Products Show, Houston, Tex, American Society of Mechanical Engineers, Gas Turbine Conference Mar 26, 1975, Paper 75-GT-13 16 p 6 refs Members, S1 00, and Products Show, Houston, Tex, Mar 26, 1975, Paper 75-GT-6 4 nonmembers, S3 00 p 12 refs Members, S1 00, nonmembers, S3 00 An experiment on the effect of casing treatment was made using The established emission standards for aircraft engines require a low-speed axial-flow compressor equipped with a single rotor the development of low emission combustors which incorporate new Results on the overall compressor performance and on the flow concepts of fuel prevaponzation and premixing systems At MTU- through the blade row as well as the flow within the treatment slots Muenchen a fuel injection system was designed which greatly are presented Then, based on the experiment, possible mechanisms suppresses droplet combustion and avoids burning at stoichiometric of the stall margin improvement are suggested (Author)
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A75-34580 # The refracting inlet - A new concept for measurements on a turbine with roughened blades were done From aircraft inlet noise suppression D Sloan and B W Farquhar (Boeing these measurements a conclusion on the aerodynamical and tnermo Co , Propulsion Research Group, Renton, Wash ) American Society dynamical behavior of the turbine is obtained The paper gives a of Mechanical Engineers, Gas Turbine Conference and Products summary of the measurements and shows how the performance of a Show, Houston, Tex, Mar 2-6, 1975, Paper 75-GT-21 11 P 5 refs turbine is affected by the roughness and the profile tolerances Members, $1 00, nonmembers, S3 00 (Author) Observations of wave refraction in flowfields containing large transverse velocity gradients have suggested a means by which A75-34597 ft Experiments concerning the response of super refraction effects could be used to aid suppression of the noise sonic nozzles to fluctuating inlet conditions E E Zukoski propagating forward thfough aircraft gas turbine inlets The first part (California Institute of Technology, Pasadena, Calif) American of this paper describes an experiment using a schlieren apparatus to Society of Mechanical Engineers, Gas Turbine Conference and observe waves passing through inlet-type flowfields The second part Products Show, Houston, Tex , Mar 26, 1975, Paper 75-GT-40 5 p describes a test program using model inlets to examine the feasibility Members, $1 00, nonmembers, S3 00 of the refracting inlet concept (Author) The noise field pioduced by the passage of pressure and entropy fluctuations through a supersonic nozzle has been investigated in an experimental program Magnitude and phase information for the A75-34586 ft Performance development of the Gem turbo- disturbances produced within the nozzle are presented and are shaft engine A B McKenzie, B T Bayne (Rolls Royce/1971/, Ltd , compared with numerical calculations (Author) Leavesden, Herts, England) American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston, Tex, Mar 26, 1975, Paper 75-GT28 9 p Members, $1 00, A75-34604 ,-f Missile firing tests at stationary targets in nonmembers, S3 00 Research supported by the Ministry of Defence support of blade containment design J I Goatham and R M (Procurement Executive) Stewart (Rolls-Royce /1971/, Ltd, Derby, England) American The Gem engine considered was specifically designed for a Society of Mechanical Engineers, Gas Turbine Conference and helicopter application The engine has a two shaft gas generator Products Show, Houston, Tex , Mar 26, 1975, Paper 75-GT-47 6 p There are altogether three concentric shafts, including the power Members, S1 00, nonmembers, S3 00 Research supported by the turbine shaft, the low-pressure gas generator shaft, and the high Ministry of Defence (Procurement Executive) pressure gas generator shaft Questions of component performance Compressor and turbine blades of aircraft engines are liable to development are discussed along with aspects of component match failure from a number of causes Their subsequent containment ing and details regarding the development of engine performance within the immediate confines of the engine has long posed problems G R for the designer aiming for minimum weight designs To assist the understanding of the dynamics of the containment problem, a series of small scale model tests have been conducted The particular tests A75-34588 ff Preliminary study of low emission gas turbine reported, deal with the failure mechanism at the point of impact A combustor with airblast fuel atomizer K Yamanaka and K Nagato theoretical analysis in support of the results obtained is developed (Ishikawa)ima Harima Heavy Industries Co, Ltd, Tanashi, Japan) Fairly good agreement is obtained between tests and theory and the American Society of Mechanical Engineers, Gas Turbine Conference read-across to full scale containment tests indicates that the and Products Show, Houston, Tex , Mar 2-6, 1975, Paper 75-GT31 containment problem is capable of scaling if linear velocities are kept 8 p 7 refs Members, S1 00, nonmembers, S3 00 constant A discontinuity in the behavior of materials with respect to An airblast fuel infection tube (AFIT) for gas turbine engines is their |ust contained energy capacity has been identified While several reported in which fuel is broken up into droplets by atomizing air contributory factors can be suggested, a fully satisfactory explana- from several small holes on the tube wall and is mixed well with the tion is not found (Author) air immediately at the hole outlets Design considerations for the AFIT are described, and results are reported for atomization and combustion tests as well as for the measurement of exhaust A75-34612 # Propagating stall in compressors with porous emissions It is sho.vn that the AFIT can fully atomize fuel using walls J H Horlock and C M Lakhwam (Salford, University, only the discharge of compressed air and has a higher combustion Salford, England) American Society of Mechanical Engineers, Gas efficiency than the pressure atomizer even at low engine speeds The Turbine Conference and Products Show, Houston, Tex, Mar 2-6, NOx emission level of the AFIT is found to be lower than that of the 1975, Paper 75-GT-59 9 p 7 refs Members, S1 00, nonmembers, pressure atomizer and to satisfy EPA regulations, while the CO S3 00 A modification is presented to the Emmons/Stennmg analysis emission level is found also to be lower than that of the pressure for predicting stall propagation, taking into account the unsteady atomizer but not to meet the EPA standards It is noted that the CO flow through the end wall of a cascade row of compressor blades It emission level can be reduced by an even further suitable arrange is shown that if radial flow from the blade channels is permitted, ment of the injection holes F G M then the condition for flow instability is changed The expression obtained for the flow coefficient at which stall occurs indicates an improvement in operating range, with virtually no effect on stall cell A75-34592 # Influences of manufacturing tolerances and speed Experimental evidence suggests that a mechanism such as that surface roughness of blades on the performance of turbines K described may be the reason for the delay in stall onset produced by Bammert and H Sandstede (Hannover, Universitat, Hanover, West porous wall treatment of axial compressors (Author) Germany) American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston, Tex, Mar 2-6, 1975, Paper 75-GT-35 8p 11 refs Members, SI 00, nonmembers, $300 The costs of the manufacturing of turbine blades are very A75-34613 * fj A study of casing treatment stall margin dependent on the manufacturing tolerances and the quality of the improvement phenomena D C Prince, Jr, D C Wisler, and D E surface A good performance of a turbine needs a certain smoothness Hilvers (General Electric Co . Aircraft Engine Group, Cincinnati, of the surface and small tolerances For an optimisation of the costs Ohio) American Society of Mechanical Engineers, Gas Turbine it is necessary to know the influences of roughness and tolerances on Conference and Products Show, Houston, Tex, Mar 2-6, 1975, the performance of a turbine In our institute measurements were Paper 75-GT 60 13 p 9 refs Members, S1 00, nonmembers, $3 00 carried out with thinned and thickened blades mounted in a turbine, Contract No NAS3 15707 which represents different manufacturing tolerances In addition. The results of a program of experimental and analytical research
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in casing treatments over axial compressor rotor blade tips are investigated include root reactions due to various load conditions, Presented Circumferential groove, axial skewed slot and blade angle average composite and ply stresses, ply delaminations, and the slot treatments were tested at low speeds With the circumferential fundamental modes and the corresponding reactions The results groove treatment the stalling flow was reduced 53% at negligible show that the thermal and pressure stresses are negligible compared efficiency sacrifice The axial skewed slot treatment improved the to those caused by the centrifugal forces Also, the core shell concept stalling flow by 15 3%, 1 8 points in peak efficiency were sacrificed for composite blades is an inefficient design (core plies not highly The blade angle slot treatment improved the stalling flow by 15 0%. stressed) and appears to be sensitive to interply delaminations The ? 4 points in peak efficiency were sacrificed The favorable stalling results are presented in graphical and tabular forms to illustrate the flow situations correlated well with observations of higher than- types and amount of data required for such an analysis, and to normal surface pressures on the rotor blade pressure surfaces in the provide quantitative data of the various responses which can be tip region, and with increased maximum diffusions on the suction helpful in designing such composite blades (Author) surfaces Annulus wall pressure gradients, especially in the 50 to 75% chord region, are also increased and blade surface pressure loadings are shifted toward the trailing edge for treated configurations A75-34628 ft A fracture mechanics approach to turbine (Author) airfoil design I Linask and J Dierberger (United Aircraft Corp, Pratt and Whitney Aircraft Div, East Hartford, Conn ) American A75-34614 « Excess noise from gas turbine exhausts N A Society of Mechanical Engineers, Gas Turbine Conference and Cumpsty (Cambridge University, Cambridge, England) American Products Show, Houston Tex, Mar 2-6, 1975, Paper 75-G T-79 8 p Society of Mechanical Engineers, Gas Turbine Conference and 8 refs Members, S1 00, nonmembers, S3 00 Contract No Products Show, Houston, Tex , Mar 2-6, 1975, Paper 75-GT-61 10 N00029 73-C-0021 p 6 refs Members, S1 00, nonmembers, S3 00 An analytical study was conducted using fracture mechanics There is evidence to show that the exhaust noise from gas principles to model turbine airfoil cracking it was found that crack turbines contains components which exceed the jet mixing noise at initiation can be related to calculated residual strains in the airfoil low jet velocities This paper describes a theory developed to coating and that coating properties are an important consideration in calculate the acoustic power produced by temperature fluctuations determining crack location and orientation The coating crack from the combustor entering the turbine Using the turbine Mach subsequently propagates into base material according to basic numbers and flow directions at blade mid height, and taking a typical fracture mechanics laws A comparison with engine tested blade value for the fluctuation in temperature, it has been possible to experience is made It is concluded that the presented model predict the acoustic power due to this mechanism for three different provides a rational method for design life prediction but its general engines In all three cases the agreement with measurements of application requires definition of new types of material property acoustic power at low |et velocities is very good Using a measured information (Author) spectrum of the temperature fluctuation the prediction of the acoustic power spectrum agrees quite well with that measured (Author) A75-34631 , Development of a high-heat-release combustor for the F100 gas turbine T E Holladay, G C Barlow (United Aircraft Corp , Pratt and Whitney Aircraft Div , West Palm Beach, A75-34617 ft Unsteady boundary layers over rotating Fla ), and R E Henderson (USAF, Aero Propulsion Laboratory, blades R S R Gorla (Chrysler Corp, Detroit, Mich ) American Wright Patterson AFB, Ohio) American Society of Mechanical Society of Mechanical Engineers, Gas Turbine Conference and Engineers, Gas Turbine Conference and Products Show, Houston, Products Show, Houston, Tex , Mar 2 6, 1975, Paper 75-GT-64 9 p Tex, Mar 26 1975, Paper 75GT-86 8 p Members, S1 00, 12 refs Membeis, S1 00, nonmembers, S3 00 nonmembers, S3 00 Rotating blades provide some of the most challenging problems The F100 turbofan engine is a twin spool, augmented engine of fluid mechanics The presence of secondary effects in the /89.000 133,000 Newton (20-30,000 Ib) thrust range/ that powers boundary layers over rotating blades results in the flow and heat the McDonnell Douglas/Air Force F 15 air superiority fighter The transfer characteristics that are different from the classical two- F100 was developed jointly with the Navy F401 engine These dimensional boundary layer theory In this paper, the unsteady engines have a common core (gas generator) The success of these velocity and thermal boundary layers have been solved for constant advanced high thrust/weight engines is, in part, the result of the temperature boundary condition By the use of small crossflow development of a short, annular, high heat release rate primary approximation, a perturbation analysis is developed to predict heat combustoi, which has a low temperature pattern factor, high transfer characteristics Numerical results for the universal functions combustion efficiency, and low pressure loss The FIDO's combustor proportional to primary flow and crossflow are presented For the uses conventional sheel metal louver cooling to minimize cost and thermal problem, universal functions are presented for Pr = 0 70 and weight, airblast fuel nozzles and combustor swirlers to atomize the 1 0 Expressions for the skin friction coefficient as well as the fuel, and a dump diffuser to reduce the compressor air exit Mach Nusselt number have been derived (Author) number (Author)
A75 34627 * * Structural response of fiber composite fan A75-34636 - Trailing edge flows over turbomachme blades blades C C Chamis (NASA, Lewis Research Center, Materials and and the Kutta-Joukowsky condition J P Gostelow (Cambridge Structures Div, Cleveland. Ohio) and M D Mmich (Cleveland State University, Cambridge. England) American Society of Mechanical University, Cleveland, Ohio) American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston, Engineers, Gas Turbine Conference and Products Show, Houston Tex. Mar 2-6, 1975. Paper 75 GT-94 16 p 40 refs Members, Tex, Mar 2-6, 1975, Paper 75GT 78 20 p Members, S1 00 S1 00, nonmembers, S3 00 Research supported by the Ministry of nonmembers, S3 00 Defence (Procurement Executive) A fiber composite airfoil, typical for high-tip speed compressor The work of Kutta and Joukowsky on trailing edge conditions is applications, is subjected to load conditions anticipated to be reviewed and the 'Kutta-Joukowsky condition' is stated It is shown encountered in such applications, and its structural response is that for most turbomachme blades, having a rounded trailing edge, theoretically investigated The analysis method used consists of this condition has no meaning and that any meaningful condition composite mechanics embedded in pre and post processors and must include the effect of viscosit/ The question of trailing edge coupled with NASTRAN The load conditions examined include conditions in an unsteady flow environment is laised and some low thermal due to aerodynamic heating, pressure due to aerodynamic frequency parameter experimental evidence on this question is forces, centrifugal, and combinations of these The various tesponses presented (Author)
343 A75-34638
A75-34638 # Jet induced thermal effects for VTOL aircraft Houston, Tex, Mar 2-6, 1975, Paper 75GT101 10 p Members, W A Barren (Grumman Aerospace Corp , Bethpage, N Y ) and J L $1 00, nonmembers, S3 00 Palcza (U S Navy, Naval Air Propulsion Test Center, Trenton, N J ) The conceptual design and feasibility of the closed loop bench American Society of Mechanical Engineers, Gas Turbine Conference test facility (CLB) are discussed The test facility integrates and Products Show, Houston, Tex , Mar 2 6, 1975, Paper 75 GT96 computers (an electrical representation of the real time engine) and 14 p 16refs Members, S1 00, nonmembers, S3 00 appropriate interfacing hardware in order to develop controls in Thermal effects peculiar to lift/cruise and lift plus lift/cruise parallel with gas turbine engine development, allowing evaluation of VTOL aircraft are evaluated These include jet heating of takeoff the engine/control interactions independently of the actual engine surfaces, wall jet effects on aircraft ground operations, fountain development cycle The development of a particular CLB is traced impingement heating of aircraft skins, and inlet hot gas remgestion from inception to the completion of one capable of representing any Data on these effects are presented, based on analysis, model tests engine over its complete operating envelope M G and airplane operational experience Design features and operational procedures which can minimize possible adverse effects are discussed A75-34650 II Spatial supersonic flow through annular It is concluded that thermal effects can be of major importance and cascades H H Fruehauf (Stuttgart, Universitat, Stuttgart, West must be carefully evaluated in the early aircraft design phase and Germany) American Society of Mechanical Engineers, Gas Turbine checked by model tests Significant constraints on ground operations Conference and Products Show, Houston, Tex, Mar 2-6, 1975, and VTOL flight modes will exist for all such aircraft (Author) Paper 75-GT 113 7 p 6 refs Members, S1 00, nonmembers, S3 00 The spatial supersonic flow through rotating and stationary annular cascades is analyzed by means of a nonlinear three A75-34639 '4 A design study of a fan augmented ramjet E dimensional method of characteristics Three dimensional corrections W Beans (Toledo, Univeisity, Toledo, Ohio) American Society of for flow quantities referred to a quasi three-dimensional Mechanical Engineers, Gas Turbine Conference and Products Show, approximation method are determined depending on geometric and Houston, Tex, Mar 26, 1975, Paper 75-GT-97 11 p 5 refs gas dynamical parameters Characteristic properties of spatial super Members, S1 00, nonmembers, S3 00 The characteristics of a hybrid propulsion system, which fills the sonic flow through annular cascades are analyzed, leading to guiding gap between turbojets and ramjets, aie piesented The hybrid system principles for practical design purposes (Author! is a fan augmented ramjet and consists of a rambumer fed by an externally driven low pressure ratio fan Cycle analyses, performance A75 34653 H Experimental results of full scale air-cooled estimates and, scaling relationships for subsonic and supersonic turbine tests H Nouse, A Yamamoto, T Yoshida, H Nishimura, K operation, and a preliminary design of a subsonic version are Takahara, T Tonsaki, and M Matusuki (National Aerospace Labora- presented A 50 to 100 percent improvement in cruise perfoimance tory, Tokyo, Japan) American Society of Mechanical Engineers, Gas above that of a ramjet can be expected in the subsonic regime Turbine Conference and Products Show, Houston, Tex , Mar 2-6, (Author) 1975, Paper 75 GT-116 11 p 5 refs Members, S1 00, nonmembers, S3 00 A75-34640 ff Lift fan characteristics selection for 1980-85 In order to investigate several problems associated with the V/STOL carrier onboard delivery aircraft R L Cavage (Rockwell turbine cooling, an air cooled two stage axial flow turbine for an International Corp , Los Angeles, Calif ) American Society of aircraft engine application was designed Aerodynamic characteristics Mechanical Engineers, Gas Turbine Conference and Products Show, of the two-stage turbine without coolants were obtained first from Houston, Tex, Mar 2-6, 1975, Paper 75 GT 98 11 p Members, the cold air turbine tests, and predictions of the turbine performance S1 00, nonmembers, S3 00 with supplying of coolants were made using the test results Characteristics for an optimum lift fan propulsion system for a Following these experiments, cooling tests of the first stage turbine 1980 1985 Ndvy V/STOL carrier onboard delivery transport aircraft were conducted in the range of turbine inlet gas temperatures lower are developed The potential characteristics and technology projec than 1360 K by another test apparatus The descriptions of the tions for the propulsion system, the aircraft design objectives and turbine and the two test apparatus and the experimental results of methodology used to select the optimum propulsion system charac the two test turbines are presented The performance prediction, tenstics are presented The results of tiade study comparisons of coolant effects and Reynolds number effect on the turbine perfor single- and two-stage fans, design fan pressure ratio, number and mance are also described (Author) arrangement of fans and gas geneiatois, and jet propulsion system effects on aircraft weight and diag are included An artist's concept and design brief of the aircraft resulting from the use of the A75 34654 # Development of real time high energy X-ray identified optimum propulsion system are presented (Author) imaging system for use in dynamic fluoroscopy of aero gas turbines A E Stewart (Rolls-Royce/1971/, Ltd , Bristol, England) American Society of Mechanical Engineers, Gas Turbine Conference and A75-34642 ,' Design and analysis of a ceramic stator vane S Products Show, Houston, Tex, Mar 2-6, 1975, Paper 75-GT 117 11 C Sanday, T L Lam, and T J Rahaim (Westinghouse Electric p 12 refs Members, SI 00, nonmembers, S3 00 Corp , Gas Turbine Systems Div , Lester, Pa ) American Society of Mechanical Engineers Gas Turbine Conference and Products Show, Houston Tex, Mar 26, 1975, Paper 75 GT WO 11 p 6 refs A75-34661 // Parachute systems of the DFVLR for stabili- Members, S1 00, nonmembers, S3 00 ARPA supported research zation and salvage of flight vehicles (Fallschirmsysteme der DFVLR The development of a ceramic stator vane for the first stage of a zur Stabihsierung und Bergung von Flugkorpern) K F Doherr and high temperature industrial gas turbine is presented The elastic P Hamel (Deutsche Forschungs- und Versuchsanstalt fur Luft- und transient thermal stress analysis of the latest design, using a Raumfahrt, Institut fur Flugmechamk, Braunschweig, West three dimensional isoparametric finite element code is outlined Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Sym- Results for a vane assembly made of silicon nitride and exposed to posium uber Start und Bergeverfahren von Flugkorpern, Hohen several temperature time conditions are discussed (Author) raketen und Drohnen, Bremen, West Germany, Apr 30, 1974, Paper 74-043 40 p 21 refs In German (DFVLR-IB 154 74/13) Scientific investigations regarding factors related to the opera A75-34643 ff Laboratory testing of controls for aircraft tion of parachute systems are considered, taking into account turbine engines J R Baker (United Aircraft Corp, Pratt and dimensional effects, relations between drag and stability, aspects of Whitney Aircraft Div , East Hartford, Conn ) American Society of pressure distribution, parachute stiength requirements, fiee flight Mechanical Engineers, Gas Turbine Conference and Products Show, model tests, and statistical accident studies Questions concerning the
344 A75-35159
development and the testing of parachute systems are also discussed Economics and Mathematical Systems Volume 108), 1975 301 p Attention is given to special test equipment and installations, 17ref S12 10 parachutes for low lump-off altitudes, rescue systems for the crews The numerical aspect of theoretical work on transonics and of military aircraft including helicopters, systems for the braking and supercritical wing sections are compiled A model of the trailing edge the stabilization of flight vehicles, and various rescue and salvage is introduced which eliminates the loss of 15 to 20 percent systems related to space applications G R experienced with heavily aft loaded models, and it is indicated how drag creep can be reduced at off design conditions A rotated finite difference scheme is presented which can handle supersonic as well as subsonic free stream Mach numbers and leads to an effective A75-34725 # System concept and key problems concerning three dimensional program for the computation of transonic flow Pllotless, remotely-controlled combat aircraft UKF (Systemkonzept past an oblique wing In the case of two-dimensional flow, the und Schlusselprobleme unbemannter, ferngelenkter Kampfflugzeuge method is extended to take into account the displacement thickness UKF) J Spmtzyk and P Starke (Dormer GmbH, Friednchshafen, computed by a semiempincal turbulent boundary layer correction A West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, series of supercritical wing sections is discussed together with Jahrestagung, 7th, Kiel, West Germany, Sept 17-19, 1974, Paper comparisons between experimental and theoretical data Computer 74076a 82 p 19 refs In German programs and a brief manual for their operation are listed It is Pllotless, remotely controlled flight vehicles show great promise shown that the programs furnish a physically adequate computer for combat missions involving strongly defended ground targets An simulation of the compressible flows that arise in problems of employment of such unmanned aircraft is considered in the case of transonic aerodynamics F G M typical area targets in connection with the provision of air support and missions which have the objective to isolate the combat area A A75-35098 Wind tunnel tests for the determination of the description of the considered vehicle concept is given Key problems behavior of aircraft external loads which are dropped (Wind are related to target recognition, data transmission, target search at kanalversuche zur Ermittlung des Abwurfverhaltens von Flugzeug the proiection screen, flight control, and vehicle navigation Aussenlasten) K Wichmann (Deutsche Forschungs und Attention is also given to an experimental system for the study of Versuchsanstalt fur Luft- und Raumfahrt, Zentralabteilung the various problem areas G R Niedergeschwmdigkeits-Windkanale, Porz-Wahn, West Germany) DFVLR-Nachrichten, June 1975, p 655,656 In German Fighters and combat aircraft carry many external loads It is A75-34854 A means of dynamic control of radar reflec- desired that these loads can be dropped without any hazard for the tivity of an antenna or other object by means of a gaseous plasma aircraft during all occurring flight conditions Practical tests involving shroud E A Flick and D J Kozakoff (Martin Marietta Aerospace, a demonstration of this capacity are very complex and present Orlando, Fla ) In Inventing the model of the future, Proceedings of certain dangers for the aircraft For these reasons preliminary studies the Southeast Region 3 Conference, Orlando, Fla , April 29 May 1, involving a simulation of the actual conditions with the aid of 1974 New York, Institute of Electrical and aircraft models are conducted in wind tunnels Details concerning Electronics Engineers, Inc , 1974, p 46-49 10 refs these studies are discussed, giving attention also to the employment A technique is proposed for controlling the reflectivity of an of high-speed cameras G R antenna by means of a bilateral gaseous plasma shrouding that permits the area shrouded to have dual mode properties and function at different times both as an opaque or transparent medium The low A75 35101 H An axisymmetric separated and reattached reflectivity of a metal nosed vehicle is attained by generating a flow on a longitudinal blunt circular cylinder T Ota (Akita sufficiently dense gaseous plasma conforming to the radome interior University, Akita, Japan) (American Society of Mechanical En- geometry At frequencies sufficiently below the plasma cutoff gineers, Applied Mechanics Summer Conference, Rensselaer Poly- frequency, the forward scatter is reduced to that of the metal nosed technic Institute, Troy, N Y, June 23 25, 1975, Paper 75-APM-14 ) counterpart until, on demand, the plasma is extinguished, exposing A SME, Transactions, Series £ Journal of Applied Mechanics, vol the antennas contained within the dielectric radome P T H 42 June 1975, p 311-315 24 refs Low-speed experiments are made for an axisymmetnc separated, reattached, and redeveloped flow over a longitudinal circular cylinder with blunt leading edge The flow characteristics such as the A75-34884 Passive infrared imaging systems J J Richter reattachment length and the flow pattern in the separated region are (Martin Marietta Aeiospace, Orlando, Fid ) In Inventing the model measured The redevelopment of the flow downstream of reattach- Of the future, Proceedings of the Southeast Region 3 Conference. ment is also investigated through various experimental results Orlando, Fla , April 29 May 1. 1974 New York, (Author) Institute of Electrical and Electronics Engmeeis, Inc, 1974, p 337 340 Passive IR imaging systems are those which employ the sensing A75 35159 Titanium casting - Industrial development - of infrared electromagnetic emission with sufficient scanned spatial Economic aspects (Moulage du titane Mise au point mdustnelle - lesolution to obtain a displayed representation of the thermal Aspects economtques) P Merrien and A Barbier (Societe Messier, characteristics of the scene Recent technological advances are Arudy, Pyrenees-Atlantiques, France) fChambre Syndicate des described along with the evolution from earlier system cor, Producteurs d'Aciers Fins et Speciaux and Union Syndicate des figurations Some applications meriting immediate system develop Industries Afronautiques et Spat/ales, Journee d'Ewdes, 6th, Le ment include accurate mihtaiy nighttime fue contiol aircraft landing Bourget, Seme-St-Denis, France, June 5, 1975) Mat&riaux et aid in heavy IFR conditions, nondestructive monitoring and testing, Techniques, vol 63, May 1975, p 235-246 In French medical diagnosis, and the like S D A new foundry in France has recently been completed for casting titanium alloy components of aerospace structures The facility possesses tools for high-temperature vacuum degassing of molds, electron beam melting, and casting by centnfugation Some A 75-34975 * Supercritical wing sections '' A handbook F results obtained with this new installation are described, and various Bauer, P Garabedian, D Korn, and A Jameson (New York economical aspects of the technology used in it are pointed out Two University, New York, N Y ) Research supported by the U S mam furnaces are contained in the installation, one with 40 kW and Atomic Energy Commission and NASA, Grants No one with 500 kW capacity Properties of the parts fabricated here, NGR-33016-167, No NGR-33 016-201, Contract No AT(11 due to the intrinsic characteristics of the alloy and to the internal 1)3077 Berlin and New York, Springer Verlag (Lecture Notes in structure that can alter them, are reported in detail S J M
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A75-35170 // Concurrent mixing and diffusion in three A75-35204 /,' Integral equations for the calculation of the dimensions H Viets and B Qumn (USAF, Aerospace Research flow about accelerated slender bodies for M greater, equal, or less Laboratories, Wright Patterson AFB, Ohio) American Institute of than 1 (Integralgleichungen zur Berechnung der Umstromung Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- beschleunigter schlanker Korper fur M greater, equal, or less than 1) ference, 8th, Hartford, Conn , June 16-18, 1975, Paper 75873 7 p J Ballmann (Rheimsch-Westfalische Technische Hochschule, Aachen, 7refs West Germany) IGesellschaft fur angewandte Mathematik und An experimental study of the effect of direction on the Mechamk, Wissenschaftliche Jahrestagung, Bochum, West Germany, concurrent mixing and diffusion process occurring in three Apr 1-5, 19741 Zeitschr/ft fur angewandte Mathematik und dimensional diffusers is presented The results of two earlier Mechamk, vol 55, Apr 1975, p T114, T115 In German analytical studies which predicted a preferred direction of diffusion A slender body which with a finite translational acceleration are verified A diffuser geometry wheie the walls diverge normal to passes through a gas that is originally at rest is considered The body the plane of the nonumfoim entrance velocity profile results in a produces in the gas a velocity field within a certain area which at larger pressure ratio across the diffuser, increased mixing within the sonic speed extends itself into all directions A solution of the diffuser and the potential to achieve the same performance as problem in three stages is discussed The approach used corresponds alternate designs while employing less driving fluid (Author) to the method used by Prandtl (1936) and Ballmann (1969) G R
A75-35171 ft A perturbation method for transonic flows A75-35215 /' Extension of the parabolic method for the about oscillating airfoils R M Traci, J L Farr, Jr (Science transonic flow I - Steady flow II - Unsteady flow (Erweiterung der Applications, Inc, El Segundo, Calif ), and E D Albano American parabolischen Methode fur die schallnahe Stromung I - Stationare Institute of Aeronautics and Astronautics, Fluid and Plasma Stromung II Instationare Stromung) K H Oehmen and I Teipel Dynamics Conference, 8th, Hartford, Conn, June 16-18, 1975, Paper 75-877 13 p 22 refs Contract No F33615 74 C 3094 (Hannover, Technische Hochschule, Hanover, West Germany) A theory and numerical solution method are presented for the (Gesellschaft fur angewandte Mathematik und Mechamk, Wissen- problem of two dimensional unsteady transonic flow about thin schaftliche Jahrestagung, Bochum, West Germany, Apr 1 5, 1974) airfoils undergoing harmonic oscillation The theory is based on a Zeitschnft fur angewandte Mathematik und Mechamk, vol 55, Apr treatment of the unsteady flow as a small perturbation on the 1975, p T143T146 9 refs In German nonlinear steady flow The coupled governing equations for the The nonlinear initial equation of the theory of first order for steady and unsteady perturbation potentials are of mixed elliptic/ transonic flow is given the form of an mhomogeneous parabolic hyperbolic type and are solved using the mixed differencing, line differential equation An approach is shown for obtaining an relaxation technique of Murman and Cole Detailed steady and analytical solution with convergent integrals Results computed for the pressure distribution in the case of two different profiles are unsteady results are compared to available data and more exact presented in graphs The computed values are compared with numerical calculations (Author) experimental data Approximate solutions for the unsteady case are de ived for the flow at the profile on the basis of linear in A75-35172 ff Vortex development and breakdown J Raat homogeneous parabolic differential equations G R (General Dynamics Corp , Convair Div , San Diego, Calif ) American Institute of Aeronautics and Astronautics, Fluid and Plasma A75-35252 Reliability and maintainability allocation for Dynamics Conference, 8th, Hartford, Conn, June 16-18, 1975, avionic maintenance optimization D E Brown and W R Krupa Paper 75-881 18 p 5 refs Contract No F33615 74 C 3084 (USAF, Systems Command, Wright-Patterson AFB, Ohio) In The process of vortex development ind breakdown is analyzed Automatic support systems for advanced maintainability, as a function of initial and external aerodynamic conditions A line Symposium, San Diego, Calif, October 30 November 1, 1974, vortex is assumed which consists of a thin viscous core of laminar Conference Record New York, Institute of flow imbedded in an inviscid flow of uniform circulation and has an Electrical and Electronics Engineers, Inc , 1974, p 9-14 axial velocity that may depend on the distance along the core A systematic approach for allocating reliability and maintain Self similar solutions which exhibit linear core growth are obtained ability factors to weapon system avionics is under development to for the particular case of an external velocity inversely proportional optimize avionics maintenance This approach will provide a means to core length The primary mechanism of vortex breakdown is to establish mission effective maintenance concepts The approach found to involve a fundamental incompatibility of the axial and deals with describing functions and allocating reliability and azimuthal flow modes within the confines of a thin layer and to be maintainability figures to influence avionics design in terms of the due to the existence of upper bounds on the ratios of axial definition of an LRU (Line Replaceable Unit) (Author) momentum area to core area and angular-momentum area to core area Core flow reversal is found to be another possible, but A75-35253 Autotest user needs at a base shop G L secondary, breakdown mechanism A quantitative method is Rowe and W Routa (Hughes Aircraft Co, Culver City, Calif ) In developed for predicting the breakdown point in terms of initial and Automatic support systems for advanced maintainability. Sym- external aerodynamic conditions, and numerical examples are given posium, San Diego, Calif, October 30 November 1, 1974, Con- which show the effect of external pressure gradients F G M ference Record New York, Institute of Elec- trical and Electronics Engineers, Inc, 1974, p 15-23 The needs of the military user of automatic test equipment at A75-35173 tj Wake vortex decay near the ground J N the base shop level of mamtemance are discussed Some of the Hallock (U S Department of Transportation, Transportation idealized concepts regr-dtng user capabilities, restrictive operating Systems Center, Cambridge, Mass ) American Institute of Aero- modes, and autotest capabilities are compared with actual ex nautics and Astronautics, Fluid and Plasma Dynamics Conference, penence User organization needs for test equipment maintenance, 8th, Hartford, Conn , June 16-18, 1975, Paper 75-882 8 p 15 refs documentation, and support are also examined V P The strength of aircraft wake vortices is being measured for aircraft landing on runway 31R at the John F Kennedy International Airport using monostatic acoustic radars By range A75-35258 # An automated tuneup calibration of jet engine gating and Ooppler processing the backscattered acoustic energy fuel controls W C Haight and H W Hawes (National Bureau of from a number of sensors, measurements are made of vortex height, Standards, Washington, DC) In Automatic support systems for strength or circulation, vertical velocity field, translational velocity, advanced maintainability. Symposium, San Diego, Calif , October and the circulation distribution within the vortex Possible decay 30-November 1, 1974, Conference Record New mechanisms and correlations with meteorological conditions are York, Institute of Electrical and Electronics Engineers, Inc , 1974, p presented (Author) 43 54 8 refs Navy supported research
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The National Bureau of Standards (NBS) has designed an manned strategic aircraft (AMSA) led to a set of requirements for automated process control system for the calibration of jet engine in-flight and ground testing that could not be met with conventional fuel controls The principal aim of this system is to relieve the test test equipment With the evolution of AMSA into the B 1 bomber, it bench operator of the necessity of setting up test conditions and to became necessary to develop a new onboard test system that would provide a means of fast and accurate data acquisition When operated meet the flight crew and to the ground maintenance service The under a vendor-supplied real time operating system, the NBS development of the B-1 central integrated test subsystem (CITS) software is designed to afford ease of modification to suit changing design requirements is described, along with the system design test requirements, ease of maintenance, and a degree of transfer- approach and the implementation of the onboard CITS hardware and ability between similar applications Attributes contributing to these software V P design goals include a modular program structure, use of a high-level programming language {Fortran) for applications routines, a well- A75-35279 Automatic test equipment for S-3A support J structured file system and utility package, and a mnemonic, M Colebank and D E Morrill (Lockheed California Co , Burbank, test-oriented language developed for coding test procedures Calif) In Automatic support systems for advanced maintainability. (Author) Symposium, San Diego, Calif, October 30 November 1, 1974, Conference Record New York, Institute of A75-35261 The age of the RPV data bus or the data bus Electrical and Electronics Engineers, Inc, 1974, p 301-310 6 refs comes of age L C Pico (Teledyne, Inc , Teledyne Ryan Aero The support of Navy S-3A Viking carrier-based antisubmarine nautical Div , San Diego, Calif ) In Automatic support systems for aircraft is based on a structured maintenance plan initiated fiom advanced maintainability, Symposium, San Diego Calif , October aircraft and avionics design The avionics is modularized and is 30-November 1, 1974, Conference Record New designed for ease of handling and for test by automatic test York, Institute of Electrical and Electronics Engineers, Inc , 1974, p equipment Onboard diagnostic computer program and built-m test 77-83 equipment functions provide 95 percent confidence that an item has The use of the airborne onboard processor to operate in a truly failed before removal to the shop A unified set of general uniquely controlled mode for self validation, and subsequent purpose automatic test equipment is used to perform all levels of validation of subsystems that are connected to a multiplexed digital shop testing to identify the failed component group for repair The data bus, are described This multiplexed digital data bus concept avionic design features for maintainability and the test systems which permits avionics system evaluation without the need for several make support of such electronics practical are discussed V P special test connectors interfacing at the interface unit, typical of the present computer test systems This test concept eliminates the many measurement instruments traditionally used for this purpose The A75-35283 A holographic visor helmet-mounted display system R N Winner (Hughes Aircraft Co , Culver City, Calif ) and J processor instruction and priority schemes are used to individually H Brmdle (USAF, Aerospace Medical Research Laboratory, Wright- address each RPV subsystem and conduct evaluations Tests can be selectively structured to permit varying levels of test complexity Patterson AFB, Ohio) In Conference on Display Devices and Systems, New York, N Y , October 9, 10, 1974, Conference Record (Author) New York, Institute of Electrical and Electronics Engineers, Inc, 1975, p 43-52 Contract No F33615-73-C-4110 A75-35264 Software management and the compiler L W An engineering evaluation model of a holographic visor helmet Wagner (General Dynamics Corp, Fort Worth Tex ) In Automatic mounted display (HVHMD) is described, which represents the first support systems for advanced maintainability. Symposium, San practical use of holographic optics with cathode-ray tube sources for Diego, Calif, October 30-November 1, 1974, Conference Record information display A system is described which has the ultimate New York, Institute of Electrical and Electronics capability of providing the pilot of an aircraft with a 30 deg Engineer, Inc, 1974, p 119-122 f ield-of-view virtual image of a miniature CRT display source while in Management decisions concerning software are discussed, with head-up or head-down modes of flight Photographs of the HVHMD particular reference to the F 111 ATE (Automatic Test Equipment) and of its virtual image, along with analytic and measured per program Specifically, it is shown how a decision to develop a formance data are given Conclusions concerning the operation of the compiler saved countless manhours of programming effort The first engineering model are made along with specific suggestions and studies which culminated in the proper compiler and language choice performance predictions for the future (Author) are outlined V P
A75-35272 * Flight test results of an automatic support A75-35284 Advanced gallium phosphide LED displays T F Kmbb (Plessey Co , Ltd , Towcester, IMorthants, England) In Paper 75-GT 1J4 7 p 6 refs Members, $1 00, nonmembers, $300 Conference on Display Devices and Systems, New Yoik, NY, Research supported by the Ministry of Defence (Procurement October 9, 10, 1974, Conference Record New Executive) York, Institute of Electrical and Electronics Engineers, Inc , 1975, p A detailed study of the vibration characteristics of a bladed disk 53-58 Research supported by the Ministry of Defence (Procurement testpiece is reported A description is given of a number of Executive) measurements and the corresponding calculations of the many The use of 7 segment or dot matrix light-emitting diode (LED) complex vibration modes possessed by a bladed disk when the blades arrays to display the value of some varying parameters in a digital are slightly mistuned Basic theoretical considerations are discussed form has, in addition to a number of advantages, the disadvantage of along with questions concerning the calculation and measurement of providing little information on the rate of change of the displayed mistuned modes, the effects of specific mistune patterns, and the parameter Disturbing display flicker and the possibility of character significance of the mode shapes G R confusion are other drawbacks of the technique The traditional form of analog displays minimizes these problems, although admittedly at the expense of resolution It was decided at the Royal A75-35277 The B-1 CITS system H L McCoy and L M Aircraft Establishment, therefore, to develop analog instrumentation Meyers (Rockwell International Corp, Los Angeles. Calif ) In for future aircraft applications Devices developed by a modular Automatic support systems for advanced maintainability. approach are described \j p Symposium, San Diego, Calif, October 30 Novembei 1, 1974, Conference Record New York, Institute of A75-35290 Cargo aircraft - A look toward the future L Electrical and Electronics Engineers, Inc , 1974, p 254 266 T Goodmanson and G N Bower (Boeing Commercial Airplane Co , Studies involving the operational use and role of the advanced Renton, Wash ) Exxon Air World, vol 27, no 3, 1975, p 62-66
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Development trends and design options are discussed in relation The present study considers the response of light aircraft to to future cargo aircraft Improvements discussed include the design atmospheric disturbances produced by thermal plumes emanating of airfoil shapes for higher subsonic speeds, the use of composite from power plants, particularly stationary gas turbine units The structures to increase payloads, and the application of computerized study is based on a theoretical and flight test investigation of a 50 tracking and billing systems to reduce overall costs Evolutionary MW gas turbine generating unit located at Shoreham, Long Island, aircraft changes are described, including the design of medium STOL N Y The results were scaled up to provide plume predictions for a transports and specialized aircraft for narrow tasks as well as the 250 MW generating complex The exhaust plume modeling used is modification of current aircraft to accomodate containerized based on the work of Hoult, Fay, and Forney (1968), which assumes cargoes Proposals are discussed for a container plane and cost flow properties that are constant in a direction normal to the axis of reductions through lower capital, maintenance, and crew costs and the plume, laminar wind and constant entramment parameters higher airplane utilization and load factors It is suggested that Results of the flight tests indicate that a minimum altitude limit can energy conservation be accomplished by laminar flow control and be safely set at 600 ft above stack exit S J M the use of airplanes which use liquid hydrogen for fuel F G M A75-35409 * ,', High altitude turbulence encountered by the A75-35298 ;: Influence of protective additions on the anti- supersonic YF-12A airplane L J Ehernberger (NASA, Flight wear properties of jet fuels (Vlnanie zashchitnykh prisadok na Reseaich Center, Edwards, Calif) In Conference on Aerospace and protivoiznosnye svoistva reaktivnykh topliv) V P Lazarenko, G B Aeronautical Meteorology, 6th, El Paso, Tex, November 1215, Skovorodin, I V Rozhkov, 2. A Sablina, and E S Churshukov 1974, Preprints Boston, Wlass , American Mete Khimiia i Tekhnologua Topliv i Masel, no 5, 1975, p 19 21 10 refs orological Society, 1974, p 305-312 12 refs In Russian The present work descnbes the tuibulence experienced by the The influence of some foreign and domestic protective additions YF 12A airplane on the basis of airplane acceleration data obtained on the anti wear properties of T 7 fuel is studied on a friction at altitudes above 12 2 km Data presented include the subiective machine It is shown that there is no direct relationship between the intensities leported by the air crew, the portion of flight distance in protective and anti wear action of the additions Protective additions turbulence, the variation of turbulence with season, and the containing the carboxyl group were found to be the only effective thickness and length of turbulence patches as detei mined along the ones V P flight path Compared with that expenenced by subsonic jets below 12 2 km, turbulence above 12 2 km was mild, but the crew was moie A75-35299 '- Changes in the properties of hydrogenated sensitive to gust accelei aliens during supersonic flight at altitudes fuels during prolonged storing {Izmeneme svoistv gidnrovannykh above 12 2 km than during subsonic flight at lowei altitudes About topliv pri dlitel'nom khranenn) E P Seregm, B A Englin, M P 68% of the distance traveled was in turbulence between 122 and 168 km, as compared to less than 1% above 18 3 km High altitude Alekseeva, G V Kachurma V A Gladkikh, A N Romanov, and A turbulence increased by a factor of thiee from summei to wintei L Ivanov Khimiia i Tekhnologua Topliv i Masel, no 5, 1975, p Turbulence patches weie 0 4 km thick and 10 km long on the 27 30 5 refs In Russian average S J M It is shown that storage periods of two or three years Icxl to a deterioration of the thermal stability of hydrogenated fuels This deterioration may be prevented over a penod of five years by adding A75-35411 * , The influence of wind shear on aerodynamic such anti oxidation (or dispersive) agents as tonola, copolymers of coefficients W Frost and E Hutto (Tennessee, University, esters of the methacrylic acid, or isopropyl octadecyl amme V P Tullahoma, Tenn ) In Conference on Aerospace and Aeronautical Meteoiology, 6th, El Paso, Tex , November 1215, 1974, Preprints A75-35300 a' Application of thin-layer chromatography for Boston, Mass, Amencan Meteoiological Society, determining the wearing capacity of additives contained in 1974, p 317324 10 refs Contract No NAS8 27387 petroleum-based aviation oils (Primeneme tonkoslomoi khroma The purpose of this study is to investigate the influence of wind tografn dlia opredelenua srabatyvaemosti prisadok, soderzha shear on the lift, diag, toll and yaw moments of a wing in a shchikhsia v aviatsionnykh neftianykh maslakh) K S Chernova, P horizontal wind gradient at various elevations and roll angles The A Mikheichev, and M M Vakhmianma (Gosudarstvennyi Nauchno- models of wind shear considered aie those proposed by Leurs (1973) Issledovatel'skn Institut Geologn Arktiki, USSR) Khinv/a i Tekh for atmospheric flow over hoiizontally homogeneous and uniform nologna Topliv i Masel, no 5, 1975, p 56-58 9 refs In Russian terrain A general series solution for the distribution of lift along the wing span following the method of Houghton and Brock (1970) is employed to compute the loads and moments on the airfoil Results A75-35350 # The An-2 aircraft /4th revised and enlarged of the computations indicate that wind sheai can have a significant edition/ (Samolet An-2 /4th revised and enlarged edition/) I V effect on the rolling and yawing moments of the wing of an aircraft Radchenko, V P Kramchamnov, and V P Dubrmskii Moscow, flying with one wing low in the atmospheric boundary layer These Izdatel'stvo Transport, 1974 456 p In Russian moments are directly influenced by the magnitude of the wind The basic design and flight characteristics of the An 2 aircraft gradient in the neutral atmosphete reflected by the magnitude of the and its three modifications are described at length The aircraft is of friction velocity The effect of wind sheai on lift and drag is biplane type, designed for short haul of passengers and cargo Its negligible Stability of the atmosphere tends to increase the equipment and instrumentation are described, and the principle magnitude of the rolling moment while decreasing its variation with difficulties that might be encountered in handling and maintamance elevation S J M of the aircraft are treated Use of the aircraft in agriculture is described P T H A75-35413 ,/ Surface wind speed range as a function of time A75-35403 H Response of a light aircraft to a thermal interval and mean wind speed P Tattelman (USAF, Cambiidge exhaust plume F W Lipfert, B R McCaffrey (Long Island Lighting Research Laboiatoi les, Bedfoid, Mass) In Conference on Co , Hicksville, N Y ), E A Sanlorenzo (General Applied Science Aerospace and Aeronautical Meteoiology 6th, El Paso, Tex Laboratories, Westbury, N Y ), P Baronti (Advanced Technology November 1215, 1974, Prepnnts Boston, Mass , Laboratories, Westbury, NY), and B W McCormick (Pennsylvania Amencan Meteoiological Society 1974, p 329334 State University, State College, Pa ) In Conference on Aerospace Nomogiams of the 50 , 75 , 90 , and 98 peicentile wind speed and Aeronautical Meteorology, 6th, El Paso, Tex , November 1215, ranges are obtained for mean speeds between 20 and 100 kts and 1974, Preprints Boston, Mass , American time inteivals between 20 and 600 sec The nomogiams indicate that Meteorological Society, 1974, p 273-280 the wind speed tange incieases with increasing mean speed and
348 A75-35425
increasing time interval However, the rate of increase diminishes A75-35422 * ." Wind tunnel tests and computer simulations of with increasing 5-mmute speed At the 98 percentile level, there is buoyant wing-tip vortices R C Costen, R E Davidson, and G T even a slight decrease in range (from 80 to 100 kts) V P Rogers (NASA, Langley Research Center, Hampton, Va ) In Conference on Aerospace and Aeronautical Meteorology, 6th, El A75-35414 <-' Aeronautical requirements and procedure for Paso, Tex, November 1215, 1974, Preprints low-level turbulence and wind shear reporting M E Nancoo Boston, Mass, American Meteorological Society, 1974, p 378 386 (International Civil Aviation Organization, Montreal Canada) In 12 refs Conference on Aerospace and Aeronautical Meteorology, 6th, El It is demonstrated that wing tip vortices with buoyant cores can Paso, Tex, November 1215, 1974, Preprints (A75 35351 1647) be made in a wind tunnel Wing-tip vortices generated by an aircraft Boston, Mass, American Meteorological Society, 1974, p 335-338 often become buoyant, because of heating effects due to the |et The nature and characteristics of low level wind shears which are exhaust or in connection with a descending motion in a stable hazardous to aircraft during takeoff and landing are examined The atmosphere A description of wind tunnel studies is given, taking into wind shear experienced by aircraft at heights up to 60 m may be account the experimental conditions, the transition to turbulence, caused by vertical variations in the mean flow (vertical shear), by and the drift of the buoyant vortex A computer simulation of horizontal variations in the mean flow (horizontal shear), by wing tip vortices is also discussed G R atmospneric turbulence, or by combinations of these factors Specific requirements, criteria, and procedures established by ICAO A75-35423 A predictive model of wake vortex transport for reporting vertical wind shear cannot be applied in many cases M R Brashears (Lockheed Missiles and Space Co , Inc , Huntsville, because of the lack of a reliable system for measuring vertical wind Ala ) and J N Hcllock (U S Department of Transportation, shear The use of tethered balloons and laser Doppler, acoustic Transportation Systems Center, Cambridge, Mass) In Conference Doppler, and radar Doppler systems for this purpose is proposed on Aerospace and Aeronautical Meteorology, 6th, El Paso, Tex , V P November 1215, 1974, Preprints Boston, Mass , American Meteorological Society. 1974, p 387 392 10 refs A75-35418 ,;' Aircraft turbulence encounters during com- Results are reported for a series of flight tests conducted to mercial operations m the vicinity of thunderstorms P A Barclay verify the predictive model of vortex transport developed by In Conference on Aerospace and Aeronautical Meteorology 6th, El Brashears and Hallock (1974) The tests include measuring Paso, Tex , November 1215, 1974, Preprints atmospheric conditions, forecasting vortex transport, flying various Boston, Mass, American Meteorological Society, 1974, p 357 360 7 aircraft past ground based and tower mounted equipment, and refs monitoring vortex tracks Predicted and measured vortex tracks are A detailed investigation of turbulence conditions experienced by compared for various aircraft, predicted and measured wind profiles an aircraft under thunderstorm conditions was conducted at Brisbane are also compared, and excellent agreement is found between the Airport in Australia over a two month period in 1972 Aspects of predictions and measurements Use of this model and meteorological aircraft response to turbulence are discussed along with details data to forecast vortices at Kennedy Airport is described F G M concerning the turbulence measurements It was found that for the observations considered the turbulence advisory service and the criterion for assessing severe turbulence from the radar was effective A75-35424 " fhe motion of wake vortices in the terminal G R environment J N Hallock, W D Wood, and E A Spitzer (U S Department of Transportation, Transportation Systems Center, Cambridge, Mass ) In Conference on Aerospace and Aeronautical A75-35419 /" A study of self-similarity in boundary layer Meteorology, 6th, El Paso, Tex , November 12 15, 1974, Preprints turbulence and its relevance to aircraft design and operation R R Boston, Mass , American Meteorological Society, Brook (Commonwealth of Australia Bureau of Meteorology, 1974, p 393398 Melbourne, Australia) In Conference on Aerospace and Aero The wake vortex problem appearing in connection with the nautical Meteorology, 6th, El Paso, Tex , November 12 15, 1974, employment of wide body lets, DC-8, and B 707 m the air traffic is Preprints Boston, Mass , American Meteorolog to be solved by the development of a Wake Vortex Avoidance ical Society, 1974, p 361 363 5 refs System (WVAS) which will be used m the terminal airspace to detect An improved method for the description of wind structure is or predict the presence of vortices, to evaluate the threat, and to discussed in connection with certain difficulties regarding the command a hazard avoidance action Questions of vortex data representation of single extreme wind gusts by the conventional collection and sensor evaluation are considered, taking into account approach The method considered requires the specification of a the design of vortex sensors and the measurement of meteorological design gust as a 'ramp' of given shape, duration, magnitude, and conditions A description of the JFK vortex test site is presented probability of occurrence It is attempted to give the results of Attention is also given to details regarding WVAS development G R applying the 'self similar' model to some unique tower data, to statistically test the effectiveness of the model by a Kolmogorov Sm.rnov test suggested by Dutton and Deaven (1969) G R A75-35425 # Airborne wake vortex detection J D Fridman (Raytheon Equipment Development Laboratories, Sudbury. A75-35420 * # Wind shear effects on landing touchdown Mass ) and J N Hallock (U S Department of Transportation, point J K Luers and J B Reeves (Dayton, University, Dayton, Transportation Systems Center, Cambridge, Mass I In Conference Ohio) In Conference on Aerospace and Aeronautical Meteorology, on Aerospace and Aeronautical Meteorology, 6th, El Paso, Tex , 6th, El Paso. Tex, November 1215, 1974, Preprints November 12 15, 1974, Preprints (A75 35351 1647) Boston, Mass, Boston, Mass , American Meteorological Society, American Meteorological Society, 1974, p 399-404 15 refs 1974, p 364369 11 refs Contract No NAS8-26600 Ground based instrumentation cannot provide the pilot with In the study reported, an investigation was conducted con information concerning vortex pairs generated by the preceding cernmg the shape of wind shear profiles during aircraft landings, aircraft for the time in which the aircraft is in the approach or taking into account also the values of the meteorological parameters take-off corridors of the airport For reasons of safety and for a which describe the wind shears Attention is also given to the better use of the available air space it would be advantageous if the variation of wind shear effects in the case of different aircraft types pilot had the information which could be obtained with the aid of an The study was conducted for commercial, military, and STOL inflight vortex measurement system Wake vortex signature aircraft A digital landing simulation model was used in the characteristics are discussed along with details concerning the investigations G R operation of airborne wake vortex instrumentation systems G R
349 A75-35426
A75-35426 ,tf The effects of atmospheric stability, turbu- separation of a laminar boundary layer in supersonic flow For the lence, and wind shear on aircraft wake behavior I Tombach experimental study, flat delta wings furnished with flaps at their (AeroVironrnent, Inc. Pasadena, Calif) In Conference on Aero- trailing edges were used The theoretical approach is based on space and Aeronautical Meteorology, 6th, El Paso, Tex , November boundary layei equations in interaction regime with the external 12 15, 1974, Preprints Boston, Mass, American flow A longitudinal velocity profile and an enthalpy distribution are Meteorological Society 1974, p 405-411 10 refs Research sup deduced from exact similarity solutions of the laminar boundary ported by the U S Department of Transportation and U S Air layer equations In order to obtain a profile of transverse velocity, a Force 'polynomial lopresentation associated with the longitudinal profile is used The theoretical results are compared to the experimental A75-35428 t Preliminary results from pilot aviation weather findings for pressure, heat transfer, and parietal current lines S J M self-briefing experiments F J Steckbeck (U S Navy, FAA, Systems Research and Development Service, Washington, D C ] and H D A75-35519 fj Engineering titanium alloys (Konstruktsionnye Milligan (FAA, National Aviation Facilities Experimental Center, titanovye splavy) S G Glazunov and V N Moiseev Moscow, Atlantic City, N J ) In Conference on Aerospace and Aeronautical Izdatel'stvo Metallurgna, 1974 368 p 157 refs In Russian H«—»oir,|0gy, 6th, El Paso, Tex , November 1215, 1974, Preprints The present work is concerned with the structure, physico Boston, Mass, American Meteorological Society, mechanical properties, heat treatment, technological properties, and 1974, p 418425 application fields of titanium alloys The topics discussed include Results are reported for field experiments conducted to evaluate phase transformations of titanium alloys, techniques of increasing the efficacy of the Pilot Self Briefing Terminals which have been their strength, description of the mechanical properties of medium proposed to provide weather information to general aviation pilots and high-strength titanium alloys, annealing and interaction between The project objectives and experimental plan are described, and the titanium and gases during heating in air, and weldability, mechanical data flow for the live data field experiments is illustrated The working, and chemical processing of titanium alloys Also discussed primary briefing foimat is discussed in detail, and data samples are are such fields of application as mechanical engineering and chemical f presented or the alphanumeric and graphic modes The major and aircraft industries S D problem encountered by pilots in the field experiments is shown to be the massive amount of data that had to be evaluated since the readouts provided regional weather forecasts It is recommended that A75-35521 // Matching of aircraft and engine characteristics a grid form be used for the weather data in order to reduce the (Soglasovame kharaktenstik samoleta i dvigatelia) 0 K lugov and amount of data and the terminal occupancy time F G M 0 D Selivanov Moscow, Izdatel'stvo Mashmostroeme, 1975 204 p 62 refs In Russian A75-35434 ,7 Lidar techniques for measuring slant visibility The book deals with the basic principles and methods of J R Lifsitz (U S Department of Transportation, Transportation choosing the parameters, dimensions, and operating conditions of an Systems Center, Cambridge, Mass) In Conference on Aerospace aircraft and its power plant at early design stages Simplified and Aeronautical Meteorology, 6th, El Paso, Tex , November 1215, techniques are described concerning the preliminary design of the 1974, Preprints Boston, Mass, American Mete- aerodynamic and weight characteristics of an airframe, the gas- orological Society, 1974, p 452457 6 refs dynamic, weight, and aerodynamic characteristics of an aircraft Optical radar appears to be unique in its potential to provide engine, and the performance characteristics of an aircraft with visibility information about the slant paths critical to the pilot during allowance for possible constraints Particular attention is given to low-visibility landing operations An investigation was conducted to such optimization methods of matching aircraft and engine charac- assess the feasibility of the optical radar technique Two pulsed teristics as the method of Lagrange multipliers, the method of optical radar devices were built and successfully tested The results steepest descents, the relaxation method, and the scanning method obtained confirm other recent studies which show that the technique SO can be applied to determine the atmospheric extinction coefficient, and hence the visibility, over an extended range of space G R
A75-35449 // The economic advantages of low and high A75-35706 Problem of supersonic flow past a slender temperature anti corrosion coatings on jet engine parts - A case pointed body with tail E M Surkova (Moskovsku Gosudarstvennyi history B Helan (Rolls Royce /1971/, Ltd, Engine Div , Derby, Universitet, Moscow, USSR) (Moskovsku Universitet, Vestnik, Serna England) In Economics of corrosion control, Autumn Review I - Matematika, Mekhanika, vol 29, Nov Dec 1974, p 66 73 ) Course, York, England, November 1-3, 1974, Proceedings Series 3, Moscow University Mechanics Bulletin, vol 29, no 5-6, 1974, p Number 2 London, Institution of Metallurgists, 1974, p 118-129, 43-49 7 refs Translation Discussion, p 130 Jet engine compressor and turbine parts operating in hostile environments have sometimes required replacing after short service A75-35765 The drag and oscillating transverse force on lives due to the effects of corrosion These situations, if uncontrol- vibrating cylinders due to steady fluid flow D W Sallet (Maryland, led, could lead to penalizing financial consequences and seriously University, College Park, Md ) Ingenieur-Archiv, vol 44, no 2, jeopardize airline operations Case histories of the major corrosion 1975, p 113 122 21 refs problems experienced on Rolls Royce engine parts and the economic When a cylinder is exposed to cross flow, oscillating transverse effects will be described together with the action taken to eliminate forces act on the cylinder in addition to the nearly steady drag the incidents The use of high temperature coatings and other forces If the cylinder is elastic or elastically supported, the anti-corrosion measures will be discussed (Author) oscillating transverse or lift forces will cause flow induced vibrations of the cylinder These vibrations, in turn, will cause significant A75 35450 // Study of the interaction and three-dimensional changes in the drag forces as well as in the lift force; itself which separation effects of a boundary layer in a supersonic laminar regime initially caused the flow induced vibrations This article develops a (Etude des effets d'mteraction et de decollement tridimensionnel de theory with which the drag and lift forces acting on vibrating la couche limite en regime lammaire supersomque) P Snnivasan cylinders can be predicted The theory is based upon a simplified, Poitiers, Universite, Docteur es Sciences Thesis, 1973 147 p 85 refs hypothetical, two-dimensional wake model The stipulated In French Direction des Recherches et Moyens d'Essais Contracts assumptions restrict the validity of the theory to small amplitude No 122/4, No 70/145 vibrations in the frequency range at which 'lock in' occurs, i e at The present paper experimentally and theoretically investigates which the vibration prescribes the vortex shedding frequency the phenomena of viscous interaction and of three dimensional (Author)
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A75-35796 // Loran-C compared with other navigation aids stability and drag often occur and are difficult to solve, since the in meeting future Canadian needs R M Eaton (Bedford Institute of flow often separates at the rear of the craft S J M Oceanography, Dartmouth, Nova Scotia, Canada) Canadian Aero- nautics and Space Journal, vol 21, Apr 1975, p 133-137 7 refs A75-35811 /,' Study on the establishment of flow in a wind A preliminary review of the Canadian requirements for naviga- tunnel functioning by induction (Etude de I'etablissement de tion aids (navaids) suggests that 200 m repeatability and 1,000 m I'ecoulement dans une soufflene fonctionnant par induction) A geographic accuracy will be needed The most immediate urgency Mignosi and C Quemard (ONERA, Centre d'Etudes et de appears to be on the Atlantic Continental Shelf and for exploration Recherches, Toulouse, France) Association Aeronautique et Astro- m the Arctic A thorough and comprehensive study is needed to nautique de France, Colloque d'Aerodynamique Appliquee, 11th, establish user's requirements over the next 15-20 years, and then to Universite de Bordeaux I, Talence, Gironde, France, Nov 6-8, 1974, determine the most effective navaid combination, carrying out Paper 24 p In French technical tests as necessary Loran C is one candidate to fill the An investigation into the problem of establishing a flow regime Canadian requirement, but, as with any other candidate, a number of in a subsonic transonic wind tunnel functioning by induction is technical questions need to be answered Canada has perhaps a year presented It entails, on the theoretical plane, solving equations in to decide how best to interface with the imminent expansion of the conservation of flow and energy, written for a nonstationary Loran-C by the United States Coast Guard on the Pacific and flow On the experimental level, a series of systematic experiments Atlantic coasts and over the Great Lakes (Author) carried out on a small-scale pilot plant is described An examination of the results obtained shows that it is possible to predict and control the time to flow establishment and the fluctuations in flow A75-35806 ti Comparison of flight and wind tunnel tests of parameters S J M an executive airplane (Comparison des essais en soufflene et des essais en vol pour un avion executive) J Maestrati (Avions Marcel A75 35813 ft Calculations of three-dimensional flows in a Dassault Breguet Aviation, Mengnac, Gironde, France) Association linearized supersonic regime (Calculs d'ecoulements tridimensionnels Aeronauttque et Astronautique de France, Colloque d'Aero en supersomque linearise) P Schem (Avions Marcel Dassault-Breguet dynamique Appliquee, 11th, Universite de Bordeaux I, Talence, Gironde, France, Nov 68, 1974, Paper 22 p In French Aviation, Pans, France) Association Aeronautique et Astronautique An experimental study is analyzed in order to determine the de France, Colloque d'Aerodynamique Appliquee, 11th, Universite degree of correspondence between wind tunnel and inflight testing de Bordeaux I, Talence, Gironde, France, Nov 6-8, 1974, Paper 49 results for an executive airplane It is shown that at least in the p 15 refs In French linear portions of the characteristic curves examined, there is a close A relatively rapid means of calculating supersonic flow param agreement between the two modes of testing Two types of eters based on the finite difference method and containing several comparison were undertaken a direct or point comparison, and an simplifying hypotheses is presented The specific problem treated indirect or global comparison Results are presented for the concerns engine-wing cell integration at the level of distortions in air longitudinal and latitudinal axes of the aircraft Some limitations on entry Emphasis is on the substantial differences between subsonic the accuracy of the wind tunnel simulations are also pointed out and supersonic flow properties, and on the need for modifying S JIM subsonic numerical treatments before applying them to supersonic regimes A comparison with some experimental results on military A75-35808 ft Interaction of jets of GE CF6 50 reactors with airplanes proves the accuracy of the method S J M the wing cellules of the airbus during cruise - Wind tunnel simulation (Interaction des jets des reacteurs GE CF6-50 sur la cellule de I'airbus A75-35814 # Aerodynamics of rotors - Wake equilibration en croisiere - Simulation en soufflene) M Saiz (Societe Nationale (Aerodynamique des rotors mise en equilibre du sillage) B Courjaret Industnelle Aerospatiale, Toulouse, France) Association Aero- (Societe Nationale Industnelle Aerospatiale, Chatillon-sous Bagneux, nautique et Astronautique de France, Colloque d'Aerodynamique Hauts de-Seine, France) Association Aeronautique et Astronautique Appliquee, 11th, Universite de Bordeaux I, Talence, Gironde, de France, Colloque d'Aerodynamique Appliqu&e, 11th, Universite France, Nov 6-8, 1974, Paper 40 p 10 refs In French de Bordeaux I, Talence, Gironde, France, Nov 6-8, 1974, Paper 25 The present work consists of three parts The first section p In French Research supported by the Direction des Recherches et defines the explicit balance between the components of drag and of Moyens d'Essais thrust from the cellule propulsive ensemble, while evaluating the A method is proposed which permits the resolution of mtegro nature of mutual interactions The second part reviews the ex differential relations defining, on the one hand, the form of the wake penmental technique used to determine these interactions, Simula of a rotor in axial translational motion, and on the other hand, the circulation distribution connected with the length of the rotor tions were performed with a mock-up mounted on the wall of a blades The advantages due to the turbulent lotor wake becoming transonic wind tunnel and equipped with a motorized nacelle The stable are significant, as the specific load on the rotor increases, i e , third section of the paper presents an application of the pressure when a marked contraction of the turbulent layer occurs S J M measurements made during the tests and confirms the validity of the method of investigation used, as well as determining the value of the interaction between engine jets in cruise flight S J M A75-35815 it Aerodynamics of lifting and propulsive sys A75-35810 # Some problems posed by the aerodynamics of terns in a periodically functioning regime -'Optimization of their the dirigible balloon (Quelques problemes poses par I'aerodynamique performance (Aerodynamique des systemes portants et propulsifs en du ballon dingeable) L Cabot (ONERA, Chati I Ion-sous Bagneux, regime de fonctionnement penodique Optimisation de leurs Hauts-de-Seme, France) Association Aeronautique et Astronautique performances) G Coulmy, T S Luu, and L Malavard Association de France, Colloque d'Aerodynamique Appliquee, 11th, Universite Aeronautique et Astronautique de France, Colloque d'Aero- de Bordeaux I, Talence, Gironde, France, Nov 6-8, 1974, Paper 18 dynamique Appliquee, 11th, Universite de Bordeaux I, Talence, p In French Research supported by the Centre National d'Etudes Gironde, France, Nov 6-8, 1974, Paper 74 p 16 refs In French Spatial es The present memoir generalizes certain concepts in the tur- Following a brief survey of various aerodynamic problems raised bulent theory of airfoils, with emphasis on the nonstationary aspect by the aerodynamics of the airship, several results are presented of the flows involved A unified theory of lifting and propulsive Concerning (1) a dirigible of classical configuration (the 1931 systems is derived based on the classical hypothesis of small American Akron) and (2) a proposed lens shaped omnidirectional perturbations It is shown that the condition of optimal functioning, vehicle (the French Pegasus) General areas discussed include the which corresponds to a minimum energy loss, amounts to a simple distribution of loads, resistance to forward motion, propulsion, condition of the Neumann type for the velocity potential This last stability and control, and drag-conscious rudder design Problems of finding holds for both stationary and nonstationary flight It is then
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possible to determine the distribution of circulation in the layer forming the turbulent wake of the airfoil, and thus the distribution of circulation on the scale of each active system element S J M
A75-35819 ft Two-dimensional transonic calculations with boundary layers (Calculs bidimensionnels transsomques avec couche hmrte) J Bousquet (Societe Nationale Industnelle Aerospatiale, Paris, France) Association Aeronautique et Astronautique de France, Collogue d'Aerodynamique Appliquee, 11th, Universite de Bordeaux I, Talence, Gironde, France, Nov 6-8, 1974, Paper 32 p 11 refs In French The method of calculating aerodynamic parameters in a perfect fluid derived by Garabedian-Korn is examined in order to determine its limits of validity, particularly in the presence of a shock wave A theoretical discussion ascertains the extent of the influence of displacement of the boundary layer on the accuracy of the method It is shown that the calculation technique can fit very advantageously into a modern scheme of profile determination S J M
A75-35827 Small antennas H A Wheeler (Hazeltme Corp, Greenlawn, NY) IEEE Transactions on Antennas and Propagation, vol AP 23, July 1975, p 462469 12 refs Research supported by the Bell Telephone Laboratories, U S Air Force, and U S Navy A small antenna is one whose size is a small fraction of the wavelength It is a capacitor or inductor, and it is tuned to resonance by a reactor of opposite kind Its bandwidth of impedance matching is subject to a fundamental limitation measured by its 'radiation power factor' which is proportional to its 'effective volume' These principles are reviewed in the light of a quarter century of ex- perience They are related to various practical configurations, including flush radiators for mounting on aircraft Among the examples, one extreme is a small one-turn loop of wide strip, tuned by an integral capacitor The opposite extreme is the largest antenna in the world, which is a 'small antenna' in terms of its operating wavelength In each of these extremes, the radiation power factor is much less than one percent (Author)
A75-35869 p Wind tunnel test of a flutter suppressor on a straight wing (Essai en soufflene d'un suppresseur de flottement sur une aile droite) R Destuynder (ONERA, Chatillon sous-Bagneux, Hauts-de-Seme, France) {NATO, AGARD, Reunion sur la Sup- pression du Flottement et la Reduction des Charges Structurales, Brussels, Belgium, Apr 13-18, 1975) ONERA, TP no 197531, 1975, 4 p In French An experimental wind tunnel study of aileron control of the fundamental bending torsion flutter of a wing caused by a load hung under it is presented Use of an aerodynamically uncoupled control surface simplified the transfei function of the servo-system It is concluded that the control thus obtained is not optimal, but that it does not require a precise knowledge of aerodynamic forces and wing dynamic characteristics, and that it provides an increased damping ratio over the entire velocity range S J M
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(NASA-CR-142818 TN-74-01) Avail NTIS HC S3 75 CSCL 20D A general theory for indicial-potential-compressible aerody- namics around complex configurations is presented The motion is assumed to consist of constant subsonic or supersonic speed (steady state) and small perturbations around the steady state STAR ENTRIES Using the finite-element method to discretize the space problem a set of differential-difference equations in time relating the potential to its normal derivative on the surface of the body was obtained The aerodynamics transfer function was derived by using standard method of operational calculus Author
N75-23479*# National Aeronautics and Space Administration N75-23475 Tecimar S A R L Pans (France) Ames Research Center Moffett Field Calif STUDIES AND RESEARCH ON MARINE HULLS WORKING EXPERIMENTAL STUDY OF THE EFFECT ON SPAN WITH NATURAL GROUND EFFECT Final Report LOADING ON AIRCRAFT WAKES L P Untersteller and M Ebersolt Apr 1974 79 p refs In Victor R Corsiglia Vernon J Rossow and Donald L Ciffone FRENCH ENGLISH summary May 1975 11 p refs Presented at the AIAA 8th Fluid and (Contract DGRST-69-01-723) Plasma Dyn Conf Hartford 16-18 Jun 1975 Avail Issuing Activity (NASA-TM-X-62431 A-6064) Avail NTIS HC S3 25 CSCL Methods for computing thick and thin airfoils of infinite 20D aspect ratio are presented The solutions are used to determine Measurements were made in the NASA-Ames 40- by 80-foot the characteristics of a finite aspect ratio airfoil Such an airfoil wind tunnel of the rolling moment induced on a following model was tested for several flight conditions in an aerodynamical wind in the wake 136 spans behind a subsonic transport model for tunnel Test results were applied to the design a hovercraft for a variety of trailing edge flap settings of the generator It was marine use ESRO found that the rolling moment on the following model was reduced substantially compared to the conventional landing configuration N75-23476*# National Aeronautics and Space Administration by reshaping the span loading on the generating model to Lyndon B Johnson Space Center Houston Tex approximate a span loading found in earlier studies which resulted SURFACE FINISHING Patent Application in reduced wake velocities This was accomplished by retracting Jack A Kinzler James T Heffernan Leroy G Fehrenkamp and the outboard trailing edge flaps It was concluded based on William S Lee inventors (to NASA) Filed 16 Apr 1975 flow visualization conducted in the wind tunnel as well as m a 26 p water tow facility that this flap arrangement redistributes the (NASA-Case-MSC-12631-1 US-Patent-Appl-SN-568541| Avail vorticity shed by the wing along the span to form three vortex NTIS HCS375 CSCL01C pairs that interact to disperse the wake Author An airfoil configuration and manufacturing process was designed to reduce or eliminate air turbulence created by surface irregularities in metal due to rivets wrinkles and N75-23480*# Kanner (Leo) Associates Redwood City Calif butt-joints The metal surface of an airfoil was cleaned then GROUND EFFECTS FOR JET LIFT VTOL coated with a thin layer of a fluid adhesive over which a sheet R Behnert R Roekmojoto and K-H Kleppe Washington NASA of thin plastic film was stretched Tension was applied to the May 1975 254 p refs Transl into ENGLISH from ZTL-Zukunfts- film and the resultant surface was squeezed to cause the adhesive Technik-Luft FAG 4 Jahresabschlussbencht 1971 VFW-Fokker to conform to the irregularities remove any bubbles and smooth (West Germany) 8 Apr 1971 out any wrinkles in the film The adhesive was then allowed to (Contract NASw-2481) set The resulting surface is smooth and relatively free of the (NASA-TT-F-16359) Avail NTIS HCS850 CSCL 01A normal irregularities present in the standard metal airfoil The conversion hypothesis proposed by VFW-Fokker is shown particularly for low speed aircraft NASA to be valid for the fountain of a four jet group The effects of temperature upon the expansion and the behavior of the mixture N75-23477*/jf Boston Univ Mass Dept of Aerospace regions of compressible gas flows is isolated The position of the ground stagnation point for multi-jet groups is determined Engineering A FINITE-ELEMENT METHOD FOR LIFTING SURFACES IN with the assumption of two dimensional behavior of the flow at STEADY INCOMPRESSIBLE SUBSONIC FLOW the ground region Momentum variations achieved through increases in nozzle size of momentum density yield varying ground Luigi Monno and Emil Sucm Dec 1974 38 p refs stagnation points The total pressure at the region of origin of a (Grant NGR-22-004-030) fountain is shown to be independent from the distance from (NASA-CR-142811 TR-74-05) Avail NTIS HCS375 CSCL the ground of the generating nozzles The fountain direction is 01C approximated from the momentum ratio at the ground stagnation The problem of potential steady subsonic flow for lifting surfaces is considered This problem requires the solution of an point Author integral equation relating the value of the potential discontinuity on the lifting surface and its wake to the values of the normal N75-23481 *# National Aeronautics and Space Administration derivative of the potential which are known from the boundary Ames Research Center Moffett Field Calif conditions The lifting surface is divided into small (quadrilateral VELOCITY AND ROLLING-MOMENT MEASUREMENTS IN hyperboloidal) surface elements which are described in terms THE WAKE OF A SWEPT-WING MODEL IN THE 40 BY of the Cartesian components of the four corner points The values 80 FOOT WIND TUNNEL of the potential discontinuity and the normal derivative of the Vernon J Rossow Victor R Corsiglia Richard G Schwmd (Nielson potential are assumed to be constant within each element and Eng and Res Inc Mountain View Calif) Juanita K D Fnck equal to their values at the centre-ids of the elements This (Army Air Mobility R and D Lab Moffett Field Calif) and yields a set of linear algebraic equations Numerical results are Opal J Lemmer (Army Air Mobility R and D Lab Moffett Field in good agreement with existing ones Author Calif) Apr 1975 36 p refs (NASA-TM-X-62414 A-5918) Avail NTIS HC $3 75 CSCL N75-23478*# Boston Univ. Mass Dept of Aerospace 01A Engineering Measurements were made in the wake of a swept w.mg SUBSONIC AND SUPERSONIC INDICIAL AERODYNAMICS model to study the structure of lift generated vortex wakes shed AND AERODYNAMIC TRANSFER FUNCTION FOR COM- by conventional span loadings and by several span loadings PLEX CONFIGURATIONS designed to reduce wake velocities Variations in the span loading Luigi Morino Sep 1974 33 p refs on the swept wing generator were obtained by deflecting seven (Grant NGR-22-004-030) flap segments on each side by amounts determined by vortex
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lattice theory to approximate the desired span loadings The N75-23485# Advisory Group for Aerospace Research and resulting wakes were probed with a three component hot wire Development. Paris (France) probe to measure velocity and with a wing to measure the AIRFRAME/PROPULSION INTERFERENCE rolling moment that would be induced on a following aircraft Mar 1975 419 p refs In ENGLISH, partly in FRENCH Presented The experimental techniques are described herein and the at the Fluid Dyn Panel Symp Rome 3-6 Sep 1974 measured velocity and rolling moments are presented along with (AGARD-CP-150) Avail NTIS HCS1050 CSCL 01A some comparisons with the applicable theories Author The proceedings are reported of the Fluid Dynamics Panel Symposium held in Rome Research on airframe/propulsion N75-23482*# Nielsen Engineering and Research Inc Mountain interference, and the design of combat and transport aircraft View Calif were discussed ANALYSIS OF WAKE VORTEX FLIGHT TEST DATA BEHIND A T-33 AIRCRAFT Gary D Kuhn and Robert A Jacobsen Apr 1975 80 p refs N75-23486 Office National d Etudes et de Recherches (Contract NAS2-6973) Aerospatiales Paris (France) (NASA-CR-137669 NEAR-TR-84) Avail NTIS HCS475 CSCL INTERACTION PROBLEMS BETWEEN AIR INTAKES AND 20D AIRCRAFT [PROBLEMES D'INTERACTIONS ENTRE LA Measurements of the vortex system behind a T-33 aircraft PRISE D'AIR ET L'AVION] were obtained by a Learjet equipped with a boom carrying a Jacky Leynaert In AGARD Airframe/Propulsion Interference three-wire hot-wire anemometry probe and other instrumenta- Mar 1975 11 p refs In FRENCH tion Analysis of the measurements using a computerized geometric method indicated the vortices had a core radius of The definition of the interaction terms between the air intake approximately 0 11 meter with a maximum velocity of 25 meters and the airframe and the theoretical and experimental tools per second The hot-wire anemometer was found to be a practical used to study the problem for subsonic or supersonic aircraft and sensitive instrument for determining in-flight vortex velocities are presented Some examples of the influence of a nonumform No longitudinal instabilities buoyant effects or vortex breakdowns upstream flow on the internal flow characteristics of supersonic were evident in the data which included vortex wake cross sections intakes are given and some means of adjusting the inlet to a from 0 24 to 5 22 kilometers behind the T-33 Author nonumform flow mainly for flight with incidence or yaw, are analyzed Author N75-23483*# Nielsen Engineering and Research Inc Mountain View. Calif N75-23487 Northrop Corp Hawthorne Calif CALCULATION OF STATIC LONGITUDINAL AERODYNAM- IC CHARACTERISTICS OF STOL AIRCRAFT WITH UPPER A CRITERION FOR PREDICTION OF AIRFRAME INTEGRA- TION EFFECTS ON INLET STABILITY WITH APPLICATION SURFACE BLOWN FLAPS M R Mendenhall S C Perkm Jr F K Goodwin and S B TO ADVANCED FIGHTER AIRCRAFT Spangler Apr 1975 63 p refs Gordon R Hall In AGARD Airframe/Propulsion Interference Mar 1975 15 p refs (Contract NAS2-8268) A simple criterion for the prediction of the effects of aircraft (NASA-CR-137646 NEAR-TR-83) Avail NTIS HCS425 CSCL 20D external flow field on installed inlet stability is presented Wind tunnel data obtained from model tests of an advanced fighter An existing prediction method developed for EBF aircraft aircraft are used to provide a base for discussion of installed configurations was applied to USB configurations to determine inlet instability and to demonstrate the instability criterion its potential utility in predicting USB aerodynamic characteristics An existing wing-flap vortex-lattice computer program was Specifically two sources of supersonic inlet instability are identified, the instability mechanism is discussed and an instability modified to handle multiple spanwise flap segments at different criterion is defined and application of the criterion is demonstrated flap angles A potential flow turbofan wake model developed The sources of instability include mgestion of separated fuselage for circular cross-section jets was used to model a rectangular boundary layer at high aircraft attitude and mgestion of a vortex cross-section jet wake by placing a number of circular jets side generated by a wing leading edge extension at negative attitude by side The calculation procedure was evaluated by comparison of measured and predicted aerodynamic characteristics on a variety A common stability criterion accounting for the effect of freestream Mach number, aircraft attitude, and inlet mass flow of USB configurations The method is limited to the case where the flow and geometry of the configuration are symmetric about ratio is postulated and confirmed by available data This same a vertical plane containing the wing root chord Comparison of criterion is discussed in relation to observed cases of subsonic predicted and measured lift and pitching moment coefficients inlet instability and inlet instability resulting from slipstream were made on swept wings with one and two engines per wing mgestion Application of the criterion to evaluate the effects of panel various flap deflection angles and a range of thrust configuration changes on inlet stability boundaries is demon- strated Author coefficients The results indicate satisfactory prediction of lift for flap deflections up to 55 and thrust coefficients less than 2 The applicability of the prediction procedure to USB configurations N75-23488 Aircraft Research Association Ltd Bedford is evaluated, and specific recommendations for improvements (England) are discussed Author THE MEASUREMENT Of THE TRANSONIC SPILLAGE DRAG OF A SUPERSONIC INTAKE N75-23484*# Wichita State Univ Kans SAM ThornleyandE C Carter In AGARD Airframe/Propulsion EFFECTIVENESS OF SPOILERS ON THE GA(W)-1 AIRFOIL Interference Mar 1975 13 p refs WITH A HIGH PERFORMANCE FOWLER FLAP W H Wentz. Jr Washington NASA May 1975 70 p refs The technique is described in current use at the Aircraft (Grant NGR-17-002-072) Research Association for the measurement of the transonic spillage (NASA-CR-2538) Avail NTIS HC $4 25 CSCL 01A drag of a two dimensional ramp intake The method requires Two-dimensional wind-tunnel tests were conducted to the calibration of the intake duct system for both mass flow determine effectiveness of spoilers applied to the GA(W)-1 airfoil and exit momentum The technique is equally applicable to Tests of several spoiler configurations show adequate control supersonic testing The achieved repeatability of the measurements effectiveness with flap nested It is found that providing a vent allows intake configuration differentiation to + or - 1% in path allowing lower surface air to escape to the upper surface aircraft drag for a typical supersonic fighter aircraft at high subsonic as the spoiler opens alleviates control reversal and hysteresis speed Theoretically based calculations show satisfactory tendencies Spoiler cross-sectional shape variations generally agreement with the measurements both for a range of intake have a modest influence on control characteristics A series of mass flow and for intake ramp angle changes The technique is comparative tests of vortex generators applied to the (GA-W)-I economical and suitable for routine testing General comments airfoil show that triangular planform vortex generators are superior on the merits of methods available for the measurement of spillage to square planform vortex generators of the same span Author drag using the balance mounted and whole model technique
354 N75 23494 are presented together with recommendations for further technique is analyzed of the phenomena when the external pressure and development Author the distance between primary injector exhaust plane and the nozzle exit are varied This experimental study shows the influence N75-23489 Grumman Aerospace Corp , Bethpage N Y of the external conditions upon the functioning of the nozzle AN EXPERIMENTAL INVESTIGATION OF THE COMPONENT Theoretical methods are given which allow a reasonable prediction DRAG COMPOSITION OF A TWO-DIMENSIONAL INLET of nozzle performance under such conditions Author AT TRANSONIC AND SUPERSONIC SPEEDS Clifton J Callahan In AGARD Airframe/Propulsion Interference N75-23492 LTV Aerospace Corp Dallas Tex Vought Systems Mar 1975 16 p refs Div An experimental study was performed to establish the separate SUBSONIC BASE AND BOATTAIL DRAG. AN ANALYTICAL drag force contributions of the principal components of a APPROACH rectangular two-dimensional, external compression type, J K Quermann In AGARD Airframe/Propulsion Interference supersonic air induction inlet system Concurrently inlet system Mar 1975 12 p refs performance was measured in terms of engine face total pressure Methods of subsonic potential flow were applied to the recovery and spacial flow distortion and the possibility for tradeoff calculation of base and boattail drag For configurations with a between inlet system drag and performance was explored A base the Korst method was extended to subsonic flow by scale model of the forebody, including air inlet and duct systems incorporating a standard family of free streamline shapes and a of an advanced, twin engine strike aircraft was employed for semi-empirical scheme for selecting the total pressure on the the study The wind tunnel model arrangement utilized a dividing streamline The potential flow around the shape defined dual-balance technique to measure forebody and the inlet forces by the body free streamline and jet establishes the base and separately The effects on the air induction system and vehicle boattail pressures Significant parts of the drag associated with forebody due to inlet component changes and varying propul- the base actually appear on the boattail In the absence of a sion air flow requirement were identified The major inlet variables base the effect of the jet shape is felt by the boattail With an in the investigation included cowling lip and sidewall geometries underexpanded supersonic jet a portion of the thrust which boundary layer bleed and air bypass exhaust configuration and would otherwise be lost in external expansion is recovered on compression surface deflection schedule The wind tunnel testing the boattail The fraction recovered drops rapidly with increasing was conducted in closed circuit continuous flow test facilities jet pressure ratio Results are compared with flight and wind over a full range of supersonic and transonic speeds and tunnel tests on the Vought A-7 Airplane Author representative ranges of vehicle angles of attack and sideslip Three significant aspects of the program are addressed inlet and vehicle configuration integration wind tunnel model arrange- N75-23493 Office National d Etudes et de Recherches ment for force data measurement and measured drag and Aerospatiales Pans (France) performance results These data can be broadly divided according THEORY OF MIXING FLOW OF A PERFECT FLUID AROUND to cowling side wall and bleed/bypass effects in order to display AN AFTERBODY AND A PROPULSIVE JET [COUPLAGE major trends in drag and performance for the investigated transonic ENTRE L'ECOULEMENT AUTOUR D'UN ARRIERE-CORPS and supersonic speed regimes Author ET LE JET PROPULSIF EN THEORIE DE FLUIDE PAR FAIT] Roland Maria Sube Jean-Jacques Chattot. and Georges Gillon N75-23490 National Aerospace Lab Amsterdam (Netherlands) In AGARD Airframe/Propulsion Interference Mar 1975 12 p JET INTERFERENCE OF A PODDED ENGINE INSTALLA- refs In FRENCH ENGLISH summary TION AT CRUISE CONDITIONS B Munniksma and F Jaarsma In AGARD Airframe/Propulsion The interference effects between external and internal flows Interference Mar 1975 16 p refs are examined in the framework of the mviscid flow theory These phenomena are connected mainly with flows around afterbodies The results of an experimental wind tunnel test program on Subcritical axisymmetncal interacting flows are studied The the wing-pylon-bypass engine combination of the Airbus A computation of both internal and external flows is carried out 300 B airplane are presented Only aerodynamic interference using a finite' element method The results make it possible to due to the engine jet was considered For determining the determine the shape of the jet using a pseudo-hodographic interference drag due to the engine jet as well as to have the method with an iterative procedure The interference effects of possibility to extrapolate the test results from model reference a supersonic internal flow with subsonic or transonic external conditions to full scale a test scheme was developed To prove flows are considered The supersonic internal jet is computed the validity of the assumptions of this scheme several intermediate using the method of characteristics The coupling conditions steps were made As the engine jet-airframe interference is mutual between the internal and the external flows are taken into account also effects of the external flow on the internal engine nozzle using an iterative procedure in a way similar to that proposed flow causing engine shifting has to be considered In order to by Young but extended to compressible external flows A estimate the magnitude of this influence of the external flow comparison with existing experimental results is presented field a two-dimensional model of the fan nozzle has been tested Author using an optical technique From these tests the specific features of the fan nozzle flow field ranging from subcritical via supercritical N75-23494 New York Univ N Y Aerospace Lab to choked conditions are described Author LOW SPEED INJECTION EFFECTS ON THE AERODYNAMIC PERFORMANCE AT TRANSONIC SPEED N75-23491 Avions Marcel Dassault-Breguet Aviation Saint- Renzo Piva In AGARD Airframe/Propulsion Interference Mar Cloud (France) 1975 10 p refs Prepared jointly with Rome Univ EFFECT OF EXTERNAL CONDITIONS ON THE FUNCTION- ING OF A DUAL FLOW SUPERSONIC NOZZLE [EFFET (Grant AF-AFOSR-72-21 67) DES CONDITIONS EXTERIEURES SUR LE FONCTIONNE- The problem concerning the possible reduction of the transonic MENT D'UNE TUYERE SUPERSONIQUE DOUBLE-FLUX] drag for a high speed airplane was studied to enhance the Guy DeRichemont and J Delery (Office Natl d Etudes et de aerodynamic performance at low altitudes when the drag must Rech Aerospatiales. Paris) In AGARD Airframe/Propulsion be minimized Attention was focused on decreasing the drag Interference Mar 1975 14 p refs In FRENCH ENGLISH forces on the aft portion of the vehicle An experimental summary investigation was conducted to determine the effect on afterbody The design of versatile military aircraft implies a very careful drag of the injection of a small amount of air spilled from the study of the propulsion system taking into account interferences propulsive system having low stagnation pressure in the rear with the external flow A possible solution to this difficult problem of the model The purpose of this injection was to avoid of adaptation is that of a dual flow system consisting of two overexpansion of the flow and to increase the average pressure nozzles with variable sections Flow regimes where the primary on the aft section The main problem to be investigated is where jet impiges on the secondary nozzle are considered The evolution the injection is most effective and the amount of air required to
355 N75-23495
avoid downstream reattachment Some results are presented It J Reid A R G Mundell and J F W Crane In AGARD was found that the required amount of air is relatively low, Airframe/Propulsion Interference Mar 1975 13 p iefs because of the high sensitivity of the interaction region to any small change in the flow regime Author The effect was studied of forebody and support interference on the base drag of cylindrical twm-)et afterbodies in wind tunnel N75-23495 Societe Nationale d Etude et de Construction de tests at subsonic speeds Two almost identical afterbodies were Moteurs d Aviation Melun (France) tested, one in a strong interference field and the other nearly RESEARCH ABOUT EFFECTS OF EXTERNAL FLOW AND free from interference The results illustrate the importance of AIRCRAFT INSTALLATION CONDITIONS ON THRUST the effect and also serve to test two methods of correction REVERSERS PERFORMANCES Supplementary tests show that the base drag of a cylindrical J M Hardy and J P Carre In AGARD Airframe/Propulsion twin-jet afterbody tends to be a slightly greater than that of the Interference Mar 1975 11 p In FRENCH ENGLISH summary equivalent axisymmetnc configuration Finally a method of correlation is described whereby the base drag of both twin-jet Development of thrust reversers is generally carried out in and single-jet models may be expressed in linear form Author engine test cells without external flow As thrust reversers deviate a significant amount of flow this modifies the aerodynamic field N75-23499 Tennessee Univ Space Inst Tullahoma surrounding an aircraft Inversely flight speed as well as aircraft ON SOME PROBLEMS ENCOUNTERED IN A THEORETICAL installation conditions react on the operating characteristics of STUDY OF THE EXTERNAL FLOW OVER A NOZZLE thrust reversers This interaction is contingent on the thrust CONFIGURATION IN TRANSONIC FLIGHT reversers design arrangement The interaction mechanisms is T H Moulden J M Wu and D J Spring (Army Missile Command) analyzed using test data collected with two types of thrust In AGARD Airframe/Propulsion Interference Mar 1975 12 p reversers during an investigation carried out on the CONCORDE refs afterbody The differences in behavior existing between the (Contract DAAH01-74-C-0183) reversers are shown as revealed by tests carried out with no Attention is dram to the lack of information both experimen- external flow and with external flow in the 0 N E R A wind tal and theoretical concerning the transonic flow over an engine tunnel installation An investigation on interaction mechanisms configuration operating at various thrust levels It is shown that is presented bringing out a correlation parameter which makes the flow is of great complexity In particular when the free it possible to extrapolate thrust reverser results obtained in static stream Mach number is just supersonic it is found that the conditions for various running configurations A balance of confluence between the jet and the external flow is still more deceleration forces are analyzed and the effects of flight Mach nearly subsonic in nature This observation implies that the usual number on the reversers base pressure values are shown theories for supersonic base flow are not applicable to this Author situation Calculations from such a theory are presented and discussed in the light of experimental evidence It is recommended N75-23496 British Aircraft Corp (Operating) Ltd Bristol that considerable effort be spent in developing theoretical tools (England) Commercial Aircraft Div based upon solutions to more exact equations and that more REVERSE THRUST EXPERIENCE ON THE CONCORDE fundamental experiments be performed Author A C Willmer and R L Scotland In AGARD Airframe/Propulsion Interference Mar 1975 15 p refs N75-23500 Air Force Aero Propulsion Lab Wright-Patterson AFB Ohio Reverse thrust is used as a means of deceleration on many TWIN JET EXHAUST SYSTEM TEST TECHNIQUES aircraft Partical limitations to its use are set by the following Ronald J Glidewell and Arthur E Fanning In AGARD Airframe/ airframe/propulsion interference of hot gas mgestion and aircraft Propulsion Interference Mar 1975 11 p refs handling The reverse thrust force may also differ from that measured on a test bed due to interference Model tests to The problem of integrating airframe and propulsion system determine these interference effects for the Concorde aircraft requires that the various wind tunnel models used in accomplish- were carried out The several test techniques used are described ing the task simulate as accurately as possible the internal and the model results are compared with those inferred from tests external flowfields that will be experienced on the airplane itself on the prototype and production aircraft Author This is particularly true for those models which are tested to define inlet and exhaust system interactions with the airplane N75-23497 Messerschmitt-Boelkow-Blohm GmbH Munich flowfield Exact simulation is however prohibited by the limitations (West Germany) of wind tunnel test techniques For the jet effects model such REYNOLDS NUMBER EFFECTS ON FORE- AND AFTBODY limitations include the interference effects associated with the PRESSURE DRAG model support system exhaust plume simulation and the use of Felix Aulehla and Geert Besigk In AGARD Airframe/Propulsion inlet fairings in substitution for flowing inlets Information from Interference Mar 1975 15 p refs a variety of sources is used to assess the impact of these model limitations on the accuracy of afterbody performance measured As analysis of a wind tunnel investigation at Mach number on twin jet models Author 0 8 on a series of axisymmetnc bodies showed as a main result that varying Reynolds number produces opposite changes in N75-23501 * National Aeronautics and Space Administration pressure drag on fore- and aftbody respectively It is explained Langley Research Center Langley Station Va that this result could very well be caused by wind tunnel AN EXPERIMENTAL STUDY OF JET EXHAUST SIMULA- interference As a consequence to determine aftbody drag TION correctly it will be required either to test in interference free William B Compton III In AGARD Airframe/Propulsion wind tunnels or to take into account the compensating effects Interference Mar 1975 11 p refs on the forebody Furthermore it is pointed out that modifications in aftbody geometry affect forebody drag Results from the Avail NTIS CSCL 01A commonly used aftbody test rigs with forebodies fixed to the Afterbody drag predictions for jet aircraft are usually made ground therefore need appropriate corrections Finally the experimentally with the jet exhaust flow simulated The physical sensitivity of drag components with respect to the location of gas properties of the fluid used for the model )et exhaust can split lines is discussed It is shown that subdividing the boattail affect the accuracy of simulation of the airplane s jet exhaust is not advisable from an accuracy point of view Author plume The effect of the accuracy of this simulation on afterbody drag was investigated by wind-tunnel tests with single engine N75-23498 Royal Aircraft Establishment Farnborough (England) model In addition to unheated air as the exhaust gas the Aerodynamics Dept decomposition products of three different concentrations of THE SUBSONIC BASE DRAG OF CYLINDRICAL TWIN-JET hydrogen peroxide were utilized The air jet simulation consistently AND SINGLE-JET AFTERBODIES resulted in higher boattail drag than hydrogen peroxide simulation
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The differences in drag for the various exhaust gases are attributed Walter J Rohlmg In AGARD Airframe/Propulsion Interference to different plume shapes and entramment properties of the gases Mar 1975 14 p refs The largest differences in drag due to exhaust gas properties A program to design and flight test quiet nacelles suitable were obtained for the combination of high transonic Mach numbers for installation on JT3D powered 707 airplanes was conducted and high boattail angles For these conditions the current data Design requirements for the quiet nacelle stated that the indicate that the use of air to simulate a nonafterburnmg turbojet nacelle shall be flightworthy flight weight capable of being exhaust can result in an increase in afterbody amounting to certificated to airworthiness standards and appropriate to the 20 percent of the nonafterburnmg turbojet value Author aircraft type The cruise performance flight tests and the additional performance diagnostic flight tests indicated an unnecessary performance penalty due to the nonoptimum aft translating sleeve N75-23502 Rolls-Royce Ltd Derby (England) Installation and fan nozzle configuration An unfavorable angle-of-attack- Aerodynamics Section sensitive interplay between the wing and nacelle aft sleeve flow A MODEL TECHNIQUE FOR EXHAUST SYSTEM PERFORM- fields was found at all cruise Mach numbers This penalty was ANCE TESTING the only significant item discovered during the flight test program T D Coombes In AGARD Airframe/Propulsion Interference which required correction to provide a viable retrofit nacelle Mar 1975 12 p refs configuration The diagnostic performance flight tests wind tunnel An accurate model technique is described that was devel- and exhaust system model tests are described that were conducted oped to measure the sum of gross thrust and afterbody drag to define the required change and to obtain data on the cruise for nozzle systems with single or two co-axial streams The rig performance benefits that resulted from the change Author uses air at ambient temperature and is designed to operate in the 9ft x 8ft transonic wind tunnel of the Aircraft Research N75-23506* National Aeronautics and Space Administration Association Limited at Bedford Model test results are also Lewis Research Center Cleveland Ohio presented to demonstrate the accuracy and repeatability of the REYNOLDS NUMBER EFFECTS ON BOATTAIL DRAG OF rig and show the considerable progress that has been made in EXHAUST NOZZLES FROM WIND TUNNEL AND FLIGHT advancing the state of the art on exhaust systems for low specific TESTS thrust engines Author Fred A Wilcox and Roger Chamberlm In AGARD Airframe/ Propulsion Interference Mar 1975 15 p refs
N7 5-23503 LTV Aerospace Corp Dallas Tex Vought Systems Div A family of nacelle mounted high angle boattail nozzles was ISOLATING NOZZLE AFTERBODY INTERACTION PARAME- tested to investigate Reynolds number effects on drag The nozzles TERS AND SIZE EFFECTS A NEW APPROACH were flown on a modified F-106B and mounted on scale models S C Walker In AGARD Airfra me/Propulsion Interference Mar of an F-106 in a wind tunnel A 19- to 1-range of Reynolds 1975 8 p refs number was covered as a result of the large size differences A flight test of the A-7E airplane is reported along with between models and by flying over a range of altitude In flight associated wind tunnel tests comprising approximately one half the nozzles were mounted behind J-85 turbojet engines Jet of the long range program The difficulty of controlling parameters boundary simulators and a powered turbojet engine simulator in flight was overcome by flying into the data point while allowing were used on the wind tunnel models Data were taken at Mach only slight variations in ambient pressure Wind tunnel tests numbers of 0 6 and 0 9 Boattail drag was found to be affected were made in a 1 2 x 12 meter blowdown tunnel Models by Reynolds number The effect is a complex relationship were run with both hot and cold exhaust One model was a dependent upon boundary layer thickness and nozzle boattail wingless body of revolution, the second was a geometric shape As Reynolds number was increased from the lowest values representation of the airplane The flight test demonstrated the obtained with scale models boattail drag first increased to a practicability of parameter control testing and showed applicability maximum at the lowest flight Reynolds number and then of stream thrust parameter to inflight engine performance decreased Author evaluation Wind tunnel data show trends and general levels comparable to flight and have verified some areas in which development of corrections is necessary Author N75-23507 Boeing Aerospace Co Seattle Wash ACCOUNTING OF AERODYNAMIC FORCES ON AIR- N7S-23504 ARO. Inc Arnold Air Force Station Tenn FRAME/PROPULSION SYSTEMS EXHAUST PLUME TEMPERATURE EFFECTS ON NOZZLE Michael E Brazier and William H Ball In AGARD Airframe/ AFTERBODY PERFORMANCE OVER THE TRANSONIC Propulsion Interference Mar 1975 15 p refs MACH NUMBER RANGE C E Robinson M D High and E R Thompson In AGARD Proper accounting prediction and measurement of propulsion Airframe/Propulsion Interference Mar 1975 16 p refs system installation corrections are essential for the successful Sponsored in part by AEDC development of advanced military aircraft The results are reported of recent studies which evaluate the methods used to predict Results of an experimental research investigation on measure and integrate the aerodynamic and propulsion forces nozzle/afterbody drag are presented Experimental afterbody (and within a force accounting procedure that provides maximum boattail) drag coefficients and pressure distributions are discussed element visibility and accuracy and is applicable throughout an for an isolated strut-mounted nozzle/afterbody model for the entire airplane development cycle Improved analysis techniques Mach number range from 0 6 to 15 The experimental data are described which provide more comprehensive and accurate were obtained for the basic model with an air-cooled and a predictions of inlet performance and nozzle/aftbody drag early water-cooled ethylene/air combustor to provide hot-jet duplication in the preliminary design process Inlet analysis techniques make as well as cold-jet simulation The temperature of the nozzle use of standardized data maps for obtaining complete inlet exhaust gas was varied from 530 R (294 4 K) (burner-off) to performance characteristics Nozzle/aftbody drag calculations are approximately 2500 R (13889 K) for several nozzle pressure performed using a newly-developed truncated integral mean slope ratios from jet-off to those corresponding to a moderately technique Effects of strut interference blockage model split-line under-expanded exhaust plume The differences between the locations and other factors which introduce uncertainties into cold-jet and hot-jet results are significant and adjusting the cold-jet airframe/propulsion system data are presented Author pressure ratio to correct for the changes in the let specific heat ratio with temperature will account for most of the differences N75-23508 Air Force Flight Dynamics Lab Wright-Patterson observed Author AFB Ohio AIRFRAME/PROPULSION SYSTEM FLOW FIELD INTER- N75-2350S Boeing Co Wichita Kans FERENCE AND THE EFFECT ON AIR INTAKE AND THE INFLUENCE OF NACELLE AFTERBODY SHAPE ON EXHAUST NOZZLE PERFORMANCE AIRPLANE DRAG G K Richey L E Surber and J A Laughrey In AGARD
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Airframe/Propulsion Interference Mar 1975 31 p refs G Krenz In AGARD Airframe/Propulsion Interference Mar 1975 32 p refs The interference between the airframe flow field and the Advanced technology of airframe-propulsion-integration internal/external flow in the air intakes and exhaust nozzles of confirm the feasibility for over-the-wing engine installation of high performance tactical aircraft is shown to have a significant transport aircraft Basic areas of interaction between wing and impact on the performance and operating characteristics of these engine flows are described together with specific investigations components and hence on overall aircraft performance The associated with fore and aft engine locations For the aft location, internal flow characteristics of an mlet system closely integrated W/T results are presented with flight test data including stall with the airframe are strongly influenced by flow field nonumformi- and high speed flight characteristics Further low speed tunnel ties generated by the airframe forebody and wing particularly investigations of aircraft configurations with engine intakes well at the higher angles of attack or yaw which modern tactical in front of wing LE result in increasing lift as well as improving aircraft are capable of Comparisons are made of the inlet ambient the lift /drag ratio during T/O and landing A theoretical approach (capture plane) flow field and pressure recovery steady state was conducted using the well established panel method and and dynamic inlet distortion at the simulated engine compressor comparison of theoretical and experimental pressure distributions face for both integrated (side mounted and fuselage or wing- proved well for spacing of one nozzle diameter between the shielded) and isolated inlet systems to quantitatively assess the wing and nozzle-jet sheet Author airframe interference effects For the engine exhaust nozzles of closely integrated propulsion system/airframe configurations the N75-23512 Veremigte Flugtechnische Werke-Fokker GmbH maior influence of the airframe flow field is associated with the Bremen (West Germany) alteration of the viscous and inviscid external flow in the nozzle AIRFRAME ENGINE INTERACTION FOR ENGINE region and its effect on external aftbody/nozzle drag A detailed CONFIGURATIONS MOUNTED ABOVE THE WING discussion supported by experimental data shows the effects PART 2 ENGINE JET SIMULATION. PROBLEMS IN WIND on airframe aftbody/nozzle pressure distributions and nozzle TUNNEL TESTS installed performance with respect to twin jet interference wing B Ewald In AGARD Airframe/Propulsion Interference Mar flow aircraft tail/control surfaces interfacings and free stream 1975 17 p refs flow conditions Author A test technique developed for the VFW-Fokker low speed wind tunnel is presented In this technique the airframe model is mounted to the external mechanical balance (wire suspen- N75-23509 Deutsche Forschungs- und Versuchsanstalt fuer sion) The engine pod is mounted separately on a tail sting Luft- und Raumfahrt Porz (West Germany) suspension system Due to the design of this tail sting system DETAILED EXPERIMENTAL AND THEORETICAL ANALYSIS its angle of attack axis of rotation coincides with the corresponding OF THE AERODYNAMIC INTERFERENCE BETWEEN axis of the external balance So separate mounting of airframe LIFTING JETS AND THE FUSELAGE AND WING and engine with very small gaps is possible The air is fed to G Schulz and G Viehweger In AGARD Airframe/Propulsion the engine pod with high pressure (up to 20 atmospheres) This Interference Mar 1975 13 p refs pressure is decreased to the required nozzle exit pressure ratio by perforated plates very close to the nozzle exit Calibration An aircraft model of simple shape for pressure distribution results of this nozzle arrangement are given Typical test results measurements is used which allows the variation of all main (force measurements wing pressure distribution) are presented geometrical parameters The jets reach Mach number 1 for several engine locations (over-wing on-wing under-wing) Measurements of the velocity directional flow field are added Author The pressure distributions as well as the flow directional field allow the physical interpretation of the several aerodynamic effects N75-23S13 Messerschmitt-Boelkow-Blohm GmbH Munich By integration of the pressure field the forces and moments (West Germany) caused by the jets are obtained The integration of the directional AERODYNAMIC ASPECTS AND OPTIMISATION OF field leads to the stream lines of the complicated field of cross THRUST REVERSER SYSTEMS j blown jets Theoretical momentum considerations enable the Kurt Letter and Wolfgang Kurz In AGARD Airframe/Propulsion calculation of the jet path and lead to transcalculation rules for Interference Mar 1975 22 p ref '; flow directional fields (downwash) from one dynamic pressure ratio to another Author The present generation of commercial aircraft and future advanced military aircraft require thrust reversal for reduction of N75-23510 Deutsche Forschungs- und Versuchsanstalt fuer landing distances especially for wet or icy runways The various Luft- und Raumfahrt Brunswick (West Germany) design and integration features for jet deflection are summarized PREDICTION OF THE OPTIMUM LOCATION OF A NACELLE and the requirements and problem areas discussed under special SHAPED BODY ON THE WING OF A WING-BODY consideration of a target type reverser system The important CONFIGURATION BY INVISCID FLOW ANALYSIS engme/airframe interference problems and aerodynamic aspects S R Ahmed In AGARD Airframe/Propulsion Interference Mar associated with thrust reversal are considered Parametric 1975 12 p refs investigation of thrust reverser geometry on efficiency remgestion Some results of a basic study are presented which aims at structure heating and longitudinal stability during ground roll is the prediction of optimum location of a pylon-mounted engine presented Results are based on an intensive wind tunnel test nacelle on the wing of a wing-body configuration with the help program using various types of scale models with cold and hot of inviscid flow analysis The options considered are the underwmg jets intake suction and fixed and moving ground simulation and overwmg positions of the nacelle Varied parameters are its Emphasis is given to the overall optimization of often conflicting spanwise and chordwise location along the wing The criterion requirements from parameters like for example thrust reverser for the choice of the optimum location is the minimum possible performance and remgestion The essential influence of appropriate induced drag of the wing-body-pylon-nacelle configuration The thrust reverser operation and landing techniques at or shortly theoretical calculation of the inviscid flow is done by the so-called before touch-down on landing distance is shown Author panel method Feasibility of these predictions for subcritical flow is checked on the basis of extensive pressure and force N75-23514*# National Aeronautics and Space Administration measurements in a wind tunnel Author Langley Research Center Langley Station Va EFFECT OF WING PLANFORM AND CANARD LOCATION N75-23511 Veremigte Flugtechnische Werke-Fokker GmbH AND GEOMETRY ON THE LONGITUDINAL AERODYNAMIC Bremen (West Germany) CHARACTERISTICS OF A CLOSE-COUPLED CANARD AIRFRAME ENGINE INTERACTION FOR ENGINE WING MODEL AT SUBSONIC SPEEDS CONFIGURATIONS MOUNTED ABOVE THE WING Blair B Gloss Washington Jun 1975 86 p refs PART 1 INTERFERENCE BETWEEN WING AND INTAKE (NASA-TN-D-7910 L-9987) Avail NTIS HC $475 CSCL JET 01A
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A generalized wind-tunnel model with canard and wing Inst, Uch Zap (USSR), v 3 no 4, 1972 p 158-163 planforms typical of highly maneuverable aircraft was tested in (AD-A007661 FTD-MT-24-0564-75) Avail NTIS CSCL01/1 the Langley 7- by 10-foot high-speed tunnel at a Mach number The simulation of the interaction of aerodynamic loads and of 0 30 to determine the effect of canard location canard size structural deformation is discussed for testing structural wing sweep and canard strake on canard-wing interference to strength Author high angles of attack The maior results of this investigation (may be summarized as follows the high-canard configuration (excluding the canard strake and canard flap), for both the 60 deg N75-23521# Air Force Systems Command Wright-Patterson and 44 deg swept leading-edge wings produced the highest AFB Ohio Foreign Technology Div maximum lift coefficient and the most linear pitching-moment METHOD OF THE OPTIMIZATION OF THE LOAD- curves substantially larger gams in the canard lift and total lift CARRYING STRUCTURE OF WING ON RIGIDITY DURING were obtained by adding a strake to the canard located below VARIATION BY THE DISTRIBUTION OF THICKNESS RATIO the wing chord plane rather than by adding a strake to the G V Ukramtsev and V M Frolov 27 Jan 1975 34 p Transl canard located above the wing chord plane Author into ENGLISH from Uch Zap Tsagi (USSR), v 3 no 4 1972 p 65-76 N75-23516# Max-Planck-lnstitut fuer Stroemungsforschung (AD-A007317 FTD-MT-24-0553-75) Avail NTIS CSCL01/1 Goettingen (West Germany) A method proposed for the optimization of the load carrying UNSTEADY BEHAVIOR OF TRANSONIC FLOWS structure of a wing is discussed The procedure will determine Gerd E A Meier 1974 138 p refs In GERMAN ENGLISH the greatest flexual rigidity variation as a function of relative summary thickness -of"the power material under conditions of weight (MPIS-Mitt-59) Avail NTIS HC $5 75 Max-Planck-lnst fuer constancy and satification of some aerodynamic limitations Stroemungsforsch Goettingen West Ger 26 40 OM Author Transonic flows in a curved tunnel, on wings and in Laval-type nozzles were investigated They show similar nonsteady N75-23522j Naval Air Development Center Warmmster Pa behavior where fluctuation of quantities of state occur which Air Vehicle Technology Dept are more than 10 percent The oscillation is generated by a FLIGHT TEST FOR THE FEASIBILITY EVALUATION OF THE local instability which is based on an interaction of the CHADWICK ELECTRONIC WEIGHING SYSTEM (CHEWS) boundary layer and the shock wave at the end of the supersonic Final Report flow regime Using a one-dimensional treatment of the steady William Bellinger and William Mawhinney 14 Jan 1975 54 p nozzle flow one can establish an essential criterion for the refs occurrence of the instability of the shock induced separated flow (AD-A007516 NADC-74234-30) Avail NTIS CSCL01/3 The frequency of the oscillations is determined by several This report presents the procedures and results of the flight propagation processes The change in boundary conditions caused testing of the Chadwick Electronic Weighing System (CHEWS) by displacement of the separation is propagated into the main The consensus of opinions from pilot questionnaires concerning flow field by the speed of sound and flow velocity Changes in the system is discussed A more extensive flight test program is the back-flow regime are propagated mainly with the flow and recommended GRA back-flow velocity From this experimental evidence oscillation periods can be estimated for all cases which are experimentally observed Author (ESRO) N75-23524# Air Force Systems Command Wright-Patterson AFB Ohio Foreign Technology Div EXPERIMENTAL STUDY OF HEAT TRANSFER DURING N75-23518# Air Force Systems Command Wright-Patterson FLOW AROUND UNCAMBERED DELTA WINGS WITH AFB Ohio Foreign Technology Div BLUNTED EDGES ACCOUNT OF SHEARING STRAIN DURING THE CALCULA- N A Davydova and A Ya Yushm 8 Jan 1975 34 p refs TION OF THE OSCILLATIONS OF LOW ASPECT-RATIO Transl into ENGLISH from Tsentr Aerogidrodinamicheskn Inst. WING BY THE METHOD OF POLYNOMIALS Uch Zap (USSR) v 1 1970 p 117-125 V G Bunkov 18 Feb 1975 33 p refs Transl into ENGLISH (AD-A007316 FTD-MT-24-267-75) Avail NTIS CSCL01/1 from Uch Zap Tsent Aerogidrodmamicheskn Inst (USSR), v 3 Discrete calonmetnc sensors were used along with heat no 4 1972 p 111-119 sensitive paint to make heat transfer measurements of the (AD-A007397 FTD-MT-24-0557-75) Avail NTIS CSCL01/1 supersonic flow around uncambered delta wings at various Mach The application of the polynomial method to the calculation numbers The effect of angle of attack and degree of bluntness of oscillation and flutter for short wing aspect ratios is discussed of the cyclmdrical edges on heat transfer to the wing is The method is described as a generalization of Ritz s method investigated It is shown that the available engineering methods with the expansion of deformation in power series Author of calculation of heat exchange can be utilized to evaluate heat transfer intensity on wing Author N75-23519# Air Force Systems Command Wright-Patterson AFB Ohio Foreign Technology Div INTERACTION OF SHOCK WAVE WITH WEDGE, WHICH MOVES AT SUPERSONIC SPEED R Ya Tugazakov 12 Feb 1975 24 p refs Transl into N75-23525# Air Force Systems Command Wright-Patterson ENGLISH from Uch Zap Tsentr Aerogidrodmamicheskn Inst AFB Ohio Foreign Technology Div (USSR), v 2 no 2 1971 p 34-39 CALCULATION OF LOADS AND DEFORMATIONS OF (AO-A007302 FTD-MT-24-0343-75) Avail NTIS CSCL01/1 SWEPTBACK WING WITH THE AID OF MECHANICAL The problem of incidence during shock wave interaction with ANALOG INSTRUMENTS a wedge moving at supersonic speed was examined along with B L Merkulov 27 Jan 1975 21 p refs Transl into ENGLISH flow when bow shock pressure and incident shock are identical from Tsentr Aerogidrodinamicheskn Inst Uch Zap (USSR) v 3 Gas parameters in the interaction wave region were calculated no 5 1972 p 119-123 using the method of characteristics Author (AD-A007308 FTD-MT-24-0544-75) Avail NTIS CSCL01/1 The possibility of applying mechanical analog instruments N75-23520# Air Force Systems Command Wright-Patterson to the study of pressure distributions on the surface of a AFB Ohio Foreign Technology Div streamlined body and to the calculation of elastic deformations REPRODUCTION OF THE INTERACTION OF AERODY- of sweptback wings are examined Approximation formulas are NAMIC LOADS AND STRUCTURAL DISTORTIONS DURING proposed which determine the relationship between the aero- STRENGTH TESTS dynamic coefficients of sections perpendicular to the axis of the G N Zamula and P V Miodushevskn 24 Jan 1975 26 p wing and the coefficients of sections parallel to the planes of refs Transl into ENGLISH from Tsentr Aerogidrodmamicheskn symmetry of the aircraft Author
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N75-23526# Chrysler Corp New Orleans La Data Manage- PROTECTION REQUIREMENTS FOR AIL TYPE 55 K ment Services INSTRUMENT LANDING SYSTEM Final Report. 1 Jan AN EXPERIMENTAL INVESTIGATION OF THE AERODY- 1974 - 1 Jan 1975 NAMIC CHARACTERISTICS OF SEVERAL NOSE MOUNTED Richard H Hu Andrew W Revay Jr and Richard M Cosel CANARD CONFIGURATIONS AT SUPERSONIC MACH Jan 1975 45 p refs NUMBERS (Contract DOT-FA72WAI-356) James R Burt Jr 30 Jan 1975 621 p refs (AD-A008931 FAA-RD-75-47) Avail NTIS HC $3 75 (Contract DAAH03-74-C-0405 DA Proj 1M2-62303-A-214) The degree of susceptibility of the FAA AIL Type 55 K (AD-A007793 DMS-AR-1023. RD-75-17) Avail NTIS CSCL electronic instrument landing system to electromagnetic pulse 16/4 effects due to lightning and the devices and methods proposed Experimental aerodynamic investigations were conducted at to deal with the problem are examined Lightning protection the Ames 6- by 6-foot supersonic wind tunnel to determine the requirements types of susceptible components methods used aerodynamic characteristics of several nose mounted canard wing to determine component withstand capabilities and recommenda- configurations Canard position, geometry angular orientation, tions for specific protection devices and circunty are covered and model nose shape were varied systematically to determine Appendices include a bibliography of sources used for reference their effects on model aerodynamics The model was tested at and complete circuit and block diagrams of the affected angles of attack of -3 to 12 degrees and Mach Numbers of 1 5 subsystems Author and 2 0 Aerodynamic loads were measured separately on four canards and tail panels and the total model The vapor screen N75-23531# Mitre Corp McLean Va method was used to trace the paths of the vortices shed from AN OVERVIEW AND ASSESSMENT OF PLANS AND the canards GRA PROGRAMS FOR THE DEVELOPMENT OF THE UPGRADED THIRD GENERATION AIR TRAFFIC CONTROL SYSTEM Mar 1975 225 p refs Revised (Contract DOT-FA70WA-2448) (AD-A008940 M73-237-Rev-1 FAA-EM-75-5) Avail NTIS HC $7 50 N75-23527# Naval Intelligence Support Center Washington. D C Translation Div Information on the scope, rationale costs schedules and WING LONGITUDINAL STABILITY CRITERIA possible benefits of the air traffic control system being developed R D Irodov 13 Feb 1975 19 p refs Transl into ENGLISH for operational use in the 1980s and into the 1990s is presented from Tsentr Aerogidrodmamicheskii Inst Uch Zap (USSR) v 1 The ATC system currently in use is described and the need for improvements is identified The goals and objectives of the upgrade no 4. 1970 p 63-72 system are discussed Forecasts of future air traffic through 1975 (AD-A007430 NISC-Trans-3631) Avail NTIS CSCL 01/3 The longitudinal stability of a wing in ground effect machines are shown The major features of the air traffic control system is discussed in terms of aerodynamic configurations Author are traffic control system are discussed including need objectives, technical description benefits major issues implementation considerations benefits and schedules major milestones and resource requirements through FY83 The way in which each major feature contributes toward achieving the overall goals and N75-23528# United Aircraft Corp East Hartford. Conn objectives is discussed Overall development costs are presented Research Labs along with gross estimates of F&E costs Author PREDICTION OF ROTOR WAKE INDUCED FLOW ALONG THE ROCKET TRAJECTORIES OF AN ARMY AH-1G N75-23533*# Scientific Translation Service Santa Barbara Calif HELICOPTER Final Report. Dec 1973 - Feb 1975 Anton J Landgrebe and T Alan Egolf Mar 1975 102 p refs HIGH-CAPACITY TRANSPORT PLANES AS MODERN AIR (Contract DAAA21-74-C-0195) FREIGHT SYSTEMS Helmuth M Weiss Washington NASA Jun 1975 15 p (AD-A007878 UARL-R911810-10 PA-TR-4797) Avail NTIS CSCL 01/1 refs Transl into ENGLISH from Forden und Heben (West An analytical investigation was conducted to predict the rotor Germany) v 22 no 2, 1972 p 97-100 wake induced flow velocities along the trajectories of rockets (Contract NASw-2483) fired from an Army AH-1G helicopter Thiee components of (NASA-TT-F-16396) Avail NTIS HC S3 25 CSCL01C both the time-averaged and instantaneous induced velocities were The development of large-capacity transport planes in the predicted at selected points along the trajectories of rockets U S and USSR with freight air containers is seen as ushering fired from four wing locations Three flight conditions with in complete air freight systems with world-wide capacity Recovery helicopter flight speeds of 0 15 and 30 knots were investi- rates were observed in Swiss gravel mines to be raised by gated GRA continuously operating bucket wheel type 100 dredges Extensions and improvements were made to the type GK 81/UB 600 mobile crane oil-hydraulic container elevators and explosion-proof compressed-air hoists Author
N75-23529# Naval Intelligence Support Center Washington N75-23534*# Douglas Aircraft Co Inc Santa Monica Calif D C Translation Div ANALYSIS OF OPERATIONAL REQUIREMENTS FOR HYDROAERODYNAMIC CHARACTERISTICS OF A LOW MEDIUM DENSITY AIR TRANSPORTATION VOLUME 1 ASPECT RATIO DELTA WING NEAR A SCREEN SUMMARY A G Kostm 14 Mar 1975 10 p refs Transl into ENGLISH Mar 1975 166 p refs from Gidrodmam Bolshikh Skorostei (USSR), no 5 1968 (Contract NAS2-8135) p 113-120 (NASA-CR-137603 MDC-J4484-Vol-1) Avail NTIS (AD-A007649 NISC-Trans-3643) Avail NTIS CSCL 01/1 HC $625 CSCL 01 B An analytical theory was developed to obtain hydrodynamic The medium density air travel market was studied to determine coefficients of a low aspect ratio delta wing near a screen The the aircraft design and operational requirements The impact of general representation of the potential velocity of the theory operational characteristics on the air travel system and the includes all known results as a zero approximation wing in plane economic viability of the study aircraft were also evaluated parallel flow Wing camber effects on the coefficients are Medium density is defined in terms of numbers of people studied Author transported (20 to 500 passengers per day on round trip routes) and frequency of service ( a minumium of two and maximum of eight round trips per day) for 10 regional carriers N75-23530# Rome Air Development Center Griffiss AFB N Y The operational characteristics of aircraft best suited to serve FAA LIGHTNING PROTECTION STUDY LIGHTNING the medium density air transportation market are determined
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and a basepomt aircraft is designed from which tradeoff studies described The Kalman filter is shown to gain its superior and parametric variations could be conducted The impact of performance at the expense of real time and memory required selected aircraft on the medium density market economics and in the onboard computer Author operations is ascertained Research and technology objectives for future programs in medium density air transportation are N75-23544*# United Air Lines Inc Denver Colo identified and ranked Author IMPLICATIONS OF EQUIPPING A DC-8-61 FLEET WITH RNAV/TWO SEGMENT APPROACH AVIONICS Erik B Anderson Feb 1975 14 p refs (Contract NAS2-7475) N75-23539# Air Force Technical Applications Center Washing- (NASA-CR-137680) Avail NTIS HC S3 25 CSCL17G ton D C Foreign Technology Div Due to the costs of implementing two-segment approaches EMERGENCY EJECTION. SEQUENCE OF OPERATION with special purpose computers and the fact that such systems 3 Mar 1975 17 p Transl into ENGLISH from the monograph rely on special ground equipment not generally in use today it Besknvning och handhavande Sweden is useful to consider the possibility of adding a two-segment (AD-A007470 FTD-HC-23-0867-75) Avail NTIS CSCL01/3 approach capability to area navigation (RNAV) systems The The chair ejection sequence and parachute deployment are addition of the capability to provide two-segment approach given Author navigation in an RNAV system which already interfaces with the standard instrument landing system is estimated to cost $1430 per aircraft This includes the cost to add an approach N75-23540# Operational Research and Analysis Establishment progress display to make necessary modifications to RNAV Ottawa (Ontario) software and to develop special approach plates Author ANALYSIS OF DISTRESS AIR CASES IN RELATION TO CRASH POSITION AND INTENDED TRACK 1968 - 1973 R P Hypher E J Edmond and E C ONeill Aug 1974 N75-23549*# National Aeronautics and Space Administration 63 p Ames Research Center Moffett Field Calif (AD-A007429 ORAE-R51) Avail NTIS CSCL01/3 FOUR-DIMENSIONAL GUIDANCE ALGORITHMS FOR In distress air cases in which an aircraft crashes or force AIRCRAFT IN AN AIR TRAFFIC CONTROL ENVIRON- lands without revealing its position search methods are prescribed MENT by Canadian Forces Search and Rescue Orders and Procedures Thomas Pecsvaradi Washington Mar 1975 140 p refs (CFP 209) This paper examines the relationship between crash (NASA-TN-D-7829 A-5530) Avail NTIS HC $5 75 CSCL position and various parameters of the intended flight (Origin 01B or Last Known Position Track and Destination) A method for Theoretical development and computer implementation of determining the search area is devised and compared with the three guidance algorithms are presented From a small set of existing method embodied in CFP 209 The proposed method input parameters the algorithms generate the ground track altitude produces search areas which are smaller than the present areas profile and speed profile required to implement an experimental for a corresponding probability of coverage The overall reduction 4-D guidance system Given a sequence of waypomts that define in areas is anticipated to be about 35% over a wide spectrum a nominal flight path the first algorithm generates a realistic of cases and a period of time On the assumption that search flyable ground track consisting of a sequence of straight line time is related to area a reduction in search time of this order segments and circular arcs Each circular turn is constrained by of magnitude is expected GRA the minimum turning radius of the aircraft The ground track and the specified waypomt altitudes are used as inputs to the second algorithm which generates the altitude profile The altitude profile consists of piecewise constant flight path angle segments N75-23541# Naval Air Development Center Warmmster Pa each segment lying within specified upper and lower bounds A CRASHWORTHY ARMORED PILOT SEAT FOR HELICOP- The third algorithm generates a feasible speed profile subject to TERS Final Report constraints on the rate of change in speed permissible speed Bernard Mazelsky 18 Jan 1974 131 p refs ranges and effects of wind Flight path parameters are then (AD-A007551 N A DC-7401 8-40 USAAVSCOM-TR-73-34) combined into a chronological sequence to form the 4-D guidance Avail NTIS CSCL01C vectors These vectors can be used to drive the autopilot/ The accelerations which can occur during crashes of rotary- autothrottle of the aircraft so that a 4-D flight path could be and light fixed-wing aircraft have been shown to be intunous or tracked completely automatically or these vectors may be used fatal to human occupants Under a joint Army and Navy program to drive the flight director and other cockpit displays thereby ARA Inc developed a crash survivable seat using Government enabling the pilot to track a 4-D flight path manually Author Furnished Equipment in the form of an armored bucket restraint system and cushions The seat system was designed to meet as many of the requirements of MIL-S-58095 (AV) within the physical limitations of existing space requirements in present N75-23550# Federal Aviation Administration Washington D C helicopters GRA Office of Systems Engineering Management ENGINEERING AND DEVELOPMENT PROGRAM PLAN. EN ROUTE CONTROL N75-23543*# Analytical Mechanics Associates Inc Mountain Feb 1975 92 p View Calif (AD-A007623 FAA-ED-12-2A) Avail NTIS HC $4 75 CSCL A KALMAN FILTER FOR THE STOLAND SYSTEM 17G Stanley F Schmidt Apr 1975 67 p refs Implementation of the third generation en route ATC system (Contract NAS2-8503) Model A3d2 provides basic automation capability for processing (NASA-CR-137668 Rept-75-10) Avail NTIS HC $4 25 CSCL flight data and surveillance functions Substantial upgrading of 17G this basic capability is needed to meet the demand forecast for A simple Kalman filter for potential use in STOL navigation the en route system through the 1970s and into the 1980s systems is described The mathematical formulation of all the This document describes the development plan to build the elements of the filter us initialization and overall operation are features and functions necessary for upgrading the present third presented Simulation results show that a typical approach flight generation en route system Program objectives development to landing the Kalman filter has much smaller errors during activities implementation considerations and resource estimates navigation on TACAN data and during transition from TACAN are set forth Author to MODILS data than a complementary filter Summary type flow charts of the Kalman filter logic designed for the Sperry 1819A computer are presented Also the memory and real time N75-23554 Purdue Univ Lafayette Ind requirements of the Kalman filter and complementary filter are COMPUTER-AUGMENTED DESIGN OF AIRCRAFT WING
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STRUCTURES PhD Thesis N75-23558*# Rockwell International Corp Los Angeles Calif Pramote Tiewtranon 1974 144 p DESIGN AND ANALYSIS OF A SUPERSONIC PENETRA- Avail Univ Microfilms Order No 75-10971 TION/MANEUVERING FIGHTER A design procedure for aircraft wing structure which consists R D Child Apr 1975 182 p refs of supplying a set parameters to describe the wing geometry (Contract NAS1-13496) and optimizing the weight of the structure is developed A (NASA-CR-132633) Avail NTIS HC $7 00 CSCL01B computer display terminal is used to monitor the progress of The design of three candidate air combat fighters which the design procedure All computations are automated and results would cruise effectively at freestream Mach numbers of 1 6 are visually represented by the display terminal in the form of 2 0 and 2 5 while maintaining good transonic maneuvering graphs, figures or numbers Dissert Abstr capability is considered These fighters were designed to deliver aerodynamically controlled dogfight missiles at the design Mach N75-23555*# National Aeronautics and Space Administration numbers Studies performed by Rockwell International in May Langley Research Center Langley Station, Va 1974 and guidance from NASA determined the shape and size THE EFFECT OF CHINE TIRES ON NOSE GEAR WATER- of these missiles The principle objective of this study is the SPRAY CHARACTERISTICS OF A TWIN ENGINE AIR- aerodynamic design of the vehicles however configurations are PLANE sized to have realistic structures mass properties and propul- Thomas J Yager Sandy M Stubbs and John L McCarty May sion systems The results of this study show that air combat 1975 26 p fighters in the 15000 to 23000 pound class would cruise (NASA-TM-X-72695) Avail NTIS HC $3 75 CSCL01C supersonically on dry power and still maintain good transonic An experimental investigation was performed to evaluate the maneuvering performance Author effectiveness of nose gear chine tires in eliminating or minimizing the engine spray ingestion problem encountered on several occasions by the Merlin 4 a twin-engine propjet airplane A N75-23559*# National Aeronautics and Space Administration study of the photographic and television coverage indicated that Langley Research Center Langley Station Va under similar test conditions the spray from the chine tires EFFECT OF CANARD POSITION AND WING LEADING- presented less of a potential engine spray ingestion problem EDGE FLAP DEFLECTION ON WING BUFFET AT TRAN- than the conventional tires Neither tire configuration appeared SONIC SPEEDS to pose any ingestion problem at aircraft speeds in excess of Blair B Gloss William P Henderson and Jarrett K Huffman the hydroplaning speed for each tire however significant 16 Apr 1974 92 p refs differences were noted in the spray patterns of the two sets of (NASA-TM-X-72681) Avail NTIS HC $4 75 CSCL QIC tires at sub-hydroplaning speeds At sub-hydroplaning speeds A generalized wind-tunnel model with canard and wing the conventional tires produced substantial spray above the wing planform typical of highly maneuverable aircraft was tested The which approached the general area of the engine air inlet at addition of a canard above the wing chord plane for the lower test speeds The chine tires produced two distinct spray configuration with leading-edge flaps undeflected produced plumes at sub-hydroplaning speeds one low-level plume which substantially higher total configuration lift coefficients before buffet presented no apparent threat of ingestion and one which at onset than the configuration with the canard off and leading-edge most test speeds was observed to be below the wing leading flaps undeflected The wing buffet intensity was substantially edge and thus displaced from the intakes on the engine nacelle lower for the canard-wing configuration than the wing-alone Author configuration The low-canard configuration generally displayed the poorest buffet characteristics Deflecting the wing leading-edge N75-23556*# National Aeronautics and Space Administration flaps substantially improved the wing buffet characteristics for Langley Research Center Langley Station. Va canard-off configurations The addition of the high canard did A STUDY OF HELICOPTER INTERIOR NOISE REDUCTION not appear to substantially improve the wing buffet characteristics James T Howlett and Sherman A Clevenson May 1975 8 p of the wing with leading-edge flaps deflected Author refs Presented at the 31st Ann Natl Forum of the Amer Helicopter Soc May 1975 N75-23560# Air Force Systems Command Wright-Patterson (NASA-TM-X-72655 L-10076) Avail NTIS HC $3 25 CSCL AFB Ohio Foreign Technology Div 01C The interior noise levels of existing helicopters are discussed CALCULATION OF THE REINFORCED THIN-WALLED CONSTRUCTION BY THE METHOD OF THE FINAL along with an ongoing experimental program directed towards ELEMENT reducing these levels Results of several noise and vibration measurements on Langley Research Centers Civil Helicopter Yu I Ivanov 14 Feb 1975 36 p refs Transl into ENGLISH from Tsent Aerogidrodmamichesku Inst Uch Zap (USSR) v 3. Research Aircraft are presented including measurements taken no 1 1972 p 51-60 before and after installation of an acoustically-treated cabin The predominant noise source in this helicopter is the first stage (AD-A007307 FTD-MT-24-0427-75) Avail NTIS CSCL 01/3 planetary gear-clash in the main gear box both before and after The finite element method is utilized to study various installation of the acoustically treated cabin Noise reductions of reinforced thin-walled aircraft structures Examples of calculations up to 20 db in some octave bands may be required in order to are given of a series of constructions to illustrate the possibilities of the method J M S obtain interior noise levels comparable to commercial jet transports Author N75-23562# United Aircraft Corp . Stratford Conn Sikorsky N75-23557*# National Aeronautics and Space Administration Aircraft Div Ames Research Center Moffett Field. Calif ADVANCED OVERRUNNING CLUTCH TECHNOLOGY. CORRELATION OF LOW SPEED WIND TUNNEL AND DESIGN PHASE Technical Report. Mar - Oct 1974 FLIGHT TEST DATA FOR V/STOL AIRCRAFT Jules Kish 1974 97 p refs Woodrow L Cook and David H Mickey Apr 1975 13 p refs (Contract DAAJ02-74-C-0028) (NASA-TM-X-62423 A-5998) Avail NTIS HC $3 25 CSCL (AD-A007815) Avail NTIS CSCL 13/9 01C This report discusses the results of the definition of require- The XV-5B fan-m-wmg aircraft and the YOV-10 RCF ments and design phases of the Advanced Overrunning Clutch rotating cylinder flap aircraft were subjected to wind tunnel tests Technology program conducted by Sikorsky Aircraft for the These tests were conducted specifically to provide for correlation Eustis Directorate The purpose of this program is to develop between wind tunnel and inflight aerodynamics and noise test helicopter overrunning clutches for use at engine speeds Current data Correlation between aerodynamic and noise data are practice is to design the free-wheel unit to operate at the second presented and testing techniques that are related to the accuracy stage of gearing with speeds from 6 OOC ._ ; 000 rpm At the of the data or that might affect the correlations are discussed engine speed torque is lower and hence the free-wheel unit Author will be lighter GRA
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N76-23563# Air Force Aero Propulsion Lab Wright-Patterson significant reductions in community noise with minimum penalties AFB Ohio in airplane weight cost and in operating expense by the PARAMETRIC ANALYSIS OF AN ADVANCED MANNED application of advanced composite materials to nacelle structure INTERCEPTOR UTILIZATION Final Report. Mar -Nov and sound suppression elements Nacelle concepts using advanced 1973 liners annular splitters radial splitters translating centerbody Norman A Hirsch Jan 1975 101 p refs inlets and mixed-flow nozzles were evaluated and a preferred (AD-A007663 AFAPL-TR-74-42) Avail NTIS CSCL 15/3 concept selected A preliminary design study of the selected This report parametncally reviews the interceptor and patrol concept a mixed flow nacelle with extended inlet and no splitters, aircraft requirements to adequately defend the CONUS against was conducted and the effects on noise direct operating cost penetrating aircraft with a stand off missile and subsequently and return on investment determined Author reviews the interceptor and patrol aircraft requirements to assure patrol aircraft survivabihty against the same penetrating aircraft with an air-to-air missile In the first situation the only N75-23569*# National Aeronautics and Space Administration consideration is CONUS defense without regard for patrol aircraft Lewis Research Center Cleveland Ohio survivabihty while the latter considered both CONUS defense FULL SCALE UPPER SURFACE BLOWN FLAP NOISE and patrol aircraft survivabihty GRA L J Heidelberg L Homyak and W L Jones 1975 28 p refs Presented at the Natl Air Transportation Meeting Hartford Conn 6-8 May 1975 sponsored by the Soc of Automotive N75-23564# Defence and Civil Inst of Environmental Medicine Engr Downsview (Ontario) Behavioural Sciences Oiv (NASA-TM-X-71708 E-8322) Avail NTIS HCS375 CSCL CF5D AIRCRAFT COCKPIT-NOISE REDUCTION 20A S E Forshaw and S W Olsen Sep 1974 39 p refs A highly noise suppressed TF 34 engine was used to (DCIEM-74-R-1048) Avail NTIS HCS375 investigate the noise of several powered lift configurations A sound survey was conducted in a modified CF5D aircraft involving upper surface blown (USB) flaps The configuration to determine the effectiveness of prototype floor and torso-valve variables were nozzle type d e slot and circular with deflector) mufflers in reducing the noise produced by the cockpit air flap chord length and flap angle The results of velocity surveys conditioner The noise levels in the rear cockpit of a modified at both the nozzle exit and the flap trailing edge are also presented aircraft were about 6 10 and 12 dBA less, for air-conditioner and used for correlation of the noise data Configurations using settings full cold 60 F' and full hot respectively than in an a long flap design were 4 db quieter than a short flap typical unmodified aircraft flown under identical conditions Author of current trends in USB flap design The lower noise for the long flap is attributed primarily to the greater velocity decay of N75-23565# Aeronautical Systems Div Wright-Patterson AFB the jet at the flap trailing edge The full-scale data revealed Ohio substantially more quadrupole noise in the region near the THE STATE OF THE ART IN OIL QUALITY GAGING ON deflected jet than observed m previous sub-scale tests Author US MILITARY AND COMMERCIAL AIRCRAFT John W Long Sep 1974 45 p refs N75-23570*# National Aeronautics and Space Administration (AD-A007682 ASD-TR-74-39) Avail NTIS CSCL 01/3 Lewis Research Center Cleveland Ohio This report reviews the principal design techniques used in NASA REFAN PROGRAM STATUS oil quantity gaging systems for U S military and commercial K L Abdalla and J A Yuska 1975 35 p refs Presented at aircraft The most pertinent design details of four oil quantity the Air Transportation Meeting Hartford Conn 6-8 May 1975 gaging systems are discussed and the author s opinion as to sponsored by Soc of Automotive Eng the merits of certain characteristics of each design is given (NASA-TM-X-71705) Avail NTIS HC $3 75 CSCL21E based upon the potential of the basic design while operating in The objective of the refan program is to demonstrate the military environments An attempt is made to rate each of the technical feasibility of substantially reducing the noise levels of four designs in the following areas adequacy of performance existing JT8D powered aircraft The program consists of the vulnerability to military aircraft environments, simplicity of design design manufacturing and testing of the refan engines and and reproducibility and maintainability GRA modified nacelles and airplanes Experimental testing was completed for the refan engine both at sea level and at altitude conditions Ground testing for the B727 side- and center-engine N75-23567*# Texas A&M Univ College Station Texas installations and flight testing of the DC-9 with refan engines Engineering Experiment Station and acoustic nacelles were performed Preliminary results IMPROVEMENT OF PROPELLER STATIC THRUST ESTI- presented show that substantial noise reductions were achieved MATION Final Report Author J Brusse and C F Kettleborough May 1975 28 p refs (Grant NGR-44-001-011) N75-23573*# National Aeronautics and Space Administration (NASA-CR-132680) Avail NTIS HC $3 75 CSCL 03C Lewis Research Center Cleveland Ohio The problem of improving the performance estimation of AN APPLICATION OF MODERN CONTROL THEORY TO propellers operating in the heavily loaded static thrust condition JET PROPULSION SYSTEMS was studied The Goldstein theory was assessed as it applies to Walter C Merrill May 1975 154 p refs (Grant NGR-36-010-024) propellers operating m the static thrust A review of theoretical considerations is presented along with a summary of the attempts (NASA-TM-X-71726) Avail NTIS HC $6 25 CSCL01D made to obtain a numerical solution The chordwise pressure The control of an airbreathmg turbojet engine by an onboard distribution was determined during operation at a tip speed of digital computer is studied The approach taken is to model the 500 ft/sec Chordwise integration of the pressures leads to the turbojet engine as a linear multivariable system whose parameters spanwise load distribution and further integration would give vary with engine operating environment From this model the axial thrust Author adaptive closed-loop or feedback control laws are designed and applied to the acceleration of the turbojet engine Author N75-23568*# Lockheed-California Co Burbank CONCEPTUAL DESIGN STUDY OF ADVANCED ACOUSTIC COMPOSITE NACELLE Final Report, Jun 1974 - Feb N75-23574# National Gas Turbine Establishment Pyestock 1975 (England) R G Goodall and G W Painter May 1975 241 p refs THRUST/DRAG ANALYSIS FOR A FRONT FAN NACELLE (Contract NAS1-13233) HAVING TWO SEPARATE CO-AXIAL EXHAUST STREAMS (NASA-CR-132649 LR-27113) Avail NTIS HC $7 50 CSCL P G Street 1975 38 p refs Supersedes NGTE-321 21A ARC-34645 Conceptual nacelle designs for wide-bodied and for advanced- (ARC-CP-1311 NGTE-321 ARC-34645) Avail NTIS HCS375 technology transports were studied with the objective of achieving HMSO 90p PHI $4 10
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The forces acting on and around a high by-pass ratio front Reliability is a procurement requirement like any other fan nacelle are considered in terms of the findings of an ARC parameter such as cost, response or program time scale The panel on thrust and drag definitions for jet engines Thrust and problems peculiar to enginp control systems are examined and drag components which take account of mutual interference are some suggestions made The problems of specifying reliability defined A technique for defining an afterbody or gas generator parameters are reviewed and methods of reliability assurance cowl drag in the presence of external flow is derived and the and measurement are described Author experimental measurements required are listed Example calculations using experimental data are used to demonstrate N75-23582 Air Force Aero Propulsion Lab Wright-Patterson the technique Author AFB Ohio THE ROLE OF COMPUTERS IN FUTURE PROPULSION N75-23575# Advisory Group for Aerospace Research and CONTROLS Development Paris (France) Charles E Bentz In AGARD Power Plant Controls for Aero-Gas POWER PLANT CONTROLS FOR AERO-GAS TURBINE Turbine Eng Mar 1975 9p refs ENGINES Mar 1975 374 p refs In ENGLISH partly in FRENCH Presented The role of computers in future propulsion controls is reviewed at the 44th Meeting of the AGARD Propulsion and Energetics from two different viewpoints - the integrated avionics approach Panel Ustaoset Norway 9-13 Sep 1974 and the dedicated propulsion system approach The discussion (AGARD-CP-151) Avail NTIS HCS1000 presented suggests that a dedicated computer for the propulsion Control requirements control simulation techniques and system control will provide a more optimum solution in the control system hardware for improved reliability of aircraft gas future in terms of cost complexity and reliability An integrated turbine engines are elaborated avionic systems approach that also includes the propulsion system control poses many new problems in the areas of system management and hardware development that may overshadow any of the immediate benefits of using a central processor N75-23577 Centre d Essais de Propulseurs Saclay (France) Author CONTRIBUTION OF FLIGHT SIMULATION TESTS TO THE STUDY Of TURBOMACHINE CONTROL [CONTRIBUTION DES ESSAIS EN VOL SIMULE A L'ETUDE DE LA REGULA- N75-23583 Pratt and Whitney Aircraft East Hartford Conn TION DES TURBOMACHINES] CONTROL DESIGN CONSIDERATIONS FOR VARIABLE Vincent Nardone and Jean Claude Ripoll In AGARD Power GEOMETRY ENGINES Plant Controls for Aero-Gas Turbine Eng Mar 1975 9 p refs W K Tervo and J M Tringah In AGARD Power Plant Controls In FRENCH for Aero-Gas Turbine Eng Mar 1975 8 p refs Flight simulation tests and their use to develop controls for turbine engines under various flight conditions are discussed Variable cycle engine control requirements are described Tests examined the effects of pressure static pressure build up. Control variables and potential sensed parameters are discussed and temperature at various Mach numbers Engine response and The complexity of the job is shown to require optimal control control during the transition phase were also studied logic An application of optimal control techniques is presented Transl by E H W including simulation results Author
N75-23578 Boeing Commercial Airplane Co, Renton Wash N75-23584 Motoren- und Turbmen-Union Muenchen GmbH Propulsion Technology Controls Group (West Germany) AN AIRFRAME MANUFACTURER'S REQUIREMENTS FOR PRAC A NEW AERO GAS TURBINE ENGINE CONTROL FUTURE PROPULSION CONTROLS CONCEPT Peter W Kamber In AGARD Power Plant Controls for Aero-Gas K Bauerfemd In AGARD Power Plant Controls for Aero-Gas Turbine Eng Mar 1975 17 p refs Turbine Eng Mar 1975 14 p
Selective allocation of service bleed is presented as a means The Pressure Ratio Acceleration Control (PRAC) offers a new of extending engine life for a mix of nominal and deteriorating approach to the control of modern aero gas turbine engines engines while preserving a desired thrust distribution Rating With the exception of the use of high accuracy pressure command control is examined as a means to permit simple and transducers mounted in a temperature controlled box directly on definitive power setting where each power rating is uniquely the engine all other system components are of today s standard associated with a pushbutton or throttle position Hydromechanical of technology A simple bread board model of PRAC had been and electronic control systems are compared and it is reported built and successfully tested in conjunction with an Orpheus jet that electronics will be used for most advanced control modes engine in a high altitude test facility A more sophisticated PRAC Electronic engine controls are also presented as the foundation control system for a modern supersonic bypass engine is being for improved coordination with flight controls and for on-line tested at present in conjunction with an engine simulator and engine condition monitors Author the actual fuel system hardware on a control system rig at MTU The paper outlines the control philosophy of PRAC and N7S-23579 Rolls-Royce Ltd Derby (England) presents test results achieved so far Author CONTROL SYSTEM REQUIREMENTS DICTATED BY OPTIMIZATION OF ENGINE OPERATION N75-23585 Rolls-Royce Ltd Watford (England) Small Engine Christopher Lmley Johnson In AGARD Power Plant Controls Div for Aero-Gas Turbine Eng Mar 1975 5 p HELICOPTER ENGINE CONTROL THE PAST 20 YEARS AND THE NEXT A pneumatic mechanical flat rating system is included in Edward A Simoms and Malcolm P Perks In AGARD Power the RB 211 control system and the reason for the choice of Plant Controls for Aero-Gas Turbine Eng Mar 1975 16 p parameters on which this operates is discussed On this system the pilot sets up the engine rating and the control then maintains The first 20 years of gas turbine application to helicopters it through variations of temperature and altitude Author and the progressive evolution of their associated fully automatic engine control systems are surveyed It is only recently that the dominant performance and safety requirements of the control N7S-23581 Ministry of Defence London (England) have emerged with sufficient clarity to allow them to be viewed RELIABILITY SPECIFICATION FOR GAS TURBINE CON- by an overall systems engineering approach instead of as TROL SYSTEMS piecemeal needs A system is outlined which offers substantial C G White In AGARD Power Plant Controls for Aero-Gas reductions in size and weight over current systems without any Turbine Eng Mar 1975 9p refs sacrifice in performance or safety and with marked improvement in integrity The utilization of digital control techniques leads to
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simple handling from the cockpit with self monitoring facilities GENERALIZED DYNAMIC ENGINE SIMULATION TECH- and unambiguous reversionary control modes Such a system is NIQUES FOR THE DIGITAL COMPUTERS seen as setting a pattern for control of helicopter engines of James Sellers and Fred Teren In AGARD Power Plant Controls the future Author for Aero-Gas Turbine Eng Mar 1975 23 p refs
N75-23586 National Gas Turbine Establishment Farnborough Recently advanced simulation techniques have been developed (England) for the digital computer and used as the basis for development A DIGITAL CONTROLLER APPLIED TO THE LIMITATION of a generalized dynamic engine simulation computer program OF REHEAT COMBUSTION ROUGHNESS called DYNGEN This computer program can analyze the steady J H Waters In AGARD Power Plant Controls for Aero-Gas state and dynamic performance of many kinds of aircraft gas Turbine Eng Mar 1975 8p ref turbine engines Without changes to the basic program DYNGEN can analyze one- or two-spool turbofan engines The user must Reheat combustion roughness or buzz could cause damaging supply appropriate component performance maps and design point fluctuations in jet pipe pressure in high performance reheat information Examples are presented to illustrate the capabilities combustion systems A control scheme is described which controls of DYNGEN in the steady state and dynamic modes of operation reheat fuel flow so as to limit the level of let pipe pressure The analytical techniques used in DYNGEN are briefly discussed fluctuations to safe values Factors which affect the design and and its accuracy is compared with a comparable simulation using implementation of the controller are discussed and an indication the hybrid computer The impact of DYNGEN and similar digital given of its performance Author programs on future engine simulation philosophy is also dis- cussed Author N75-23587 Dowty Fuel Systems Ltd Cheltenham (England) AFTERBURNING REGULATION CONCEPTS N75-23594 National Gas Turbine Establishment Farnborough K Robinson In AGARD Power Plant Controls for Aero-Gas (England) Turbine Eng Mar 1975 17 p TOTAL POWERPLANT SIMULATION R V Cottmgton In AGARD Power Plant Controls for Aero-Gas Various concepts of afterburner flow regulation are examined Turbine Eng Mar 1975 24 p refs with particular reference to bypass type engines requiring rapid thrust modulation with minimum disturbance to engine operating The capability of predicting the steady state performance of conditions Logic and sequencing functions associated with a gas turbine engine is extended to include the prediction of its selection of afterburner operation are examined Afterburner transient behavior as well The development and implementation system organization is discussed briefly and the merits and short of a total powerplant simulation consisting of intake and engine comings of alternative concepts are argued Author that is capable of predicting both steady state and transient performance are described The simulation is based on the synthesis of the thermodynamic relationships describing each N75-23589 Messerschmitt-Boelkow-Blohm GmbH Munich powerplant component During the development stage digital (West Germany) simulation techniques are used although the simulation is finally AN AIR INTAKE CONTROL SYSTEM FOR A SUPERSONIC implemented on a hybrid computer in order to achieve real time FIGHTER AIRCRAFT operation Actual steady state and transient test bed results are J Peikert In AGARD Power Plant Controls for Aero-Gas Turbine then used when available to validate the simulation Author Eng Mar 1975 5 p A description of an air intake system of the two dimensional N75-23595 Lucas Aerospace Ltd Birmingham (England) external compression type and its associated air intake control USE OF SIMULATION IN THE DESIGN. DEVELOPMENT system is given The AICS comprises a wedge control only AND TESTING OF POWER PLANT CONTROL SYSTEMS Intake operating maps derived from small scale wind tunnel Stephan Nye and Robert J Vickers In AGARD Power Plant test results are shown and the resulting selection of control Controls for Aero-Gas Turbine Eng Mar 1975 13 p signals and the control concept is presented The performance of the intake and the AICS is substantiated by full scale wind The design, development and testing of an engine control tunnel test results Finally the hardware implementation of the system are discussed Two specific areas are highlighted (1) AICS from a system standpoint is also given Author Digital simulation using large scale computers where both engine and control system are represented by mathematical models for evaluation feasibility and tolerance analysis and (2) hybrid N75-23592 National Research Council of Canada Ottawa computers where a real time digital engine simulation is used (Ontario) Engine Lab in conjunction with a speed controlled rig for real time development EQUILIBRIUM PERFORMANCE ANALYSIS OF GAS of the control hardware Author TURBINE ENGINES USING INFLUENCE COEFFICIENT TECHNIQUES E P Cockshutt In AGARD Power Plant Controls for Aero-Gas N75-23596 Lucas Aerospace Ltd Birmingham (England) Turbine Eng Mar 1975 10 p refs THE USE OF DIGITAL CONTROL FOR COMPLEX POWER PLANT MANAGEMENT Starting from a specified engine design point, a computer D M Griffiths and R D Powell In AGARD Power Plant oriented technique is described for establishing the equilibrium Controls for Aero-Gas Turbine Eng Mar 1975 26 p refs off-design performance The technique involves the control system approach of linearizing the governing equations at the design The application of digital control techniques to complex point, in order to establish a matrix of engine response influence power plants is considered by describing the general structure coefficients These coefficients are then used to achieve rapid of a digital controller in regard to system requirements A convergence as the cycle iterates to an off-design operating point description is then provided of an engineered controller The For clarity of presentation the technique is developed for the characteristics of the unit are given together with details of its simple turbojet cycle but the extrapolation to turbofan cycles is construction software reliability and integrity targets From this indicated By way of illustrative example of the equilibrium analysis experience reasonable conclusions can be drawn with respect technique, attention is given to the temporary extraction of large to its area of application and of the likely future for digital amounts of air bleed from a turbofan for applications such as techniques Author flap blowing and reaction controls Engine response to this perturbation is assessed and control implications suggested N75-23597 International Harvester Co San Diego Calif Solar Author Div TEMPERATURE MEASUREMENT FOR ADVANCED GAS N75-23593' National Aeronautics and Space Administration TURBINE CONTROLS Lewis Research Center Cleveland Ohio David A Rohy. T E Duffy, and W A Compton In AGARD
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Power Plant Controls for Aero-Gas Turbine Eng Mar 1975 Turbine Eng Mar 1975 33 p 27 p refs Modern gas turbine engines with turbine inlet temperatures Based upon the flight envelope of a typical high perform- higher than metal melting temperatures must have control systems ance aircraft the relationship between the efficiency of engine which provide subsecond response to changes in gas or metal mounted fuel pumps at high fuel flow turndown ratios and the temperatures High quality data are required to provide for the fuel heat sink available to the engine and airframe is discussed most efficient engine operation consistent with engine safety The effect of the pump efficiency on the fuel heat sink is presented Recently developed instruments measure individual blade in terms of the temperature rise imparted to the fuel by the temperature and another non-immersion gas temperature sensor pump and fuel flow metering system The sources of losses of not yet fully developed will provide accurate gas temperature conventional fuel pump and metering systems which contribute data up to 1927 C These instruments are described with present to the fuel temperature rise are identified and pump and metering and potential uses in control systems Author systems which will reduce those losses are discussed Examples of pump types which are applicable to advanced turbine engines are presented in terms of performance parameters and system N75-23598 Pisa Umv (Italy) advantages Author FLUIDIC SENSORS FOR TURBOJET ENGINES D Dim and M Santochi In AGARD Power Plant Controls for Aero-Gas Turbine Eng Mar 1975 28 p refs N75-23602*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio Fluidics may replace electronics in modern advanced turbojet TRANSONIC OFF-DESIGN DRAG AND PERFORMANCE OF engine instrumentation technology for comprehensive engine THREE MIXED-COMPRESSION AXISYMMETRIC INLETS condition monitoring in highly unfavourable environments This Richard R Woollen Edward T Meleason and David A Choby paper discusses some fluidic sensors originally tested m our Washington Jun 1975 50 p refs laboratory (1) new types of rotational speed sensors utilizing (NASA-TM-X-3215 E-8146) Avail NTIS HC $3 75 CSCL air flows output being a pressure signal proportional to the value 21A to be measured suitable for analog and digital circuits and (2) An experimental investigation was conducted to determine gas stream temperature sensors using a thermometnc bulb or the off-design drag and pressure performance of three axisymmet- a bimetallic spring or a capillary tube or a turbulent jet nc supersonic inlets in the transonic speed range For typical Corresponding experimental results are summarized and com- engine airflows at Mach 0 8 the drag coefficient varied from pletely fluidic circuits for a small gas turbine and for fire detection 0 045 to 0 09 at Mach 1 2 the largest drag coefficient measured in a turbojet engine are described Author was 025 Below Mach 09 a lower drag resulted when all or at least part of the excess weight flow was spilled over the cowl rather than through the bypass doors above Mach 1 1 the lowest drag was obtained by bypassing excess flow Author N75-23599 Pierburg Luftfahrtgeraete Union GmbH Neuss (West Germany) N75-23603# Air Force Aero Propulsion Lab Wright-Patterson A NEW LIGHTWEIGHT FUEL CONTROL SYSTEM FOR AFB Ohio ELECTRICAL INPUTS HIGH TEMPERATURE TESTS OF A JP-5 TYPE FUEL Final Heinz Holzem In AGARD Power Plant Controls for Aero-Gas Report. 20 Sep - 15 Nov 1972 Turbine Eng Mar 1975 30 p refs Warren Bucher and Royce Bradley Jan 1975 31 p refs (AF Pro) 3048) Most modern control concepts for complex aero gas turbine (AD-A007662 AFAPL-TR-74-74) Avail NTIS CSCL 21/4 engines employ more and more electronic hardware for the Tests were performed to determine the thermal stability of function generating part It was therefore necessary to define a JP-5 jet fuel with varying concentrations of dissolved oxygen the requirements for a simple lightweight fuel metering system under supercritical pressure and temperature conditions Tests basically consisting of a pumping device manifolds filters and were done with the Advanced Aircraft Fuel Systems Simulator an electrically controlled metering value controlled by the electronic using a simulated engine manifold Small unintentional variations box Such a system has been specified and is being built and in the test pressure caused large changes in deposit formation developed at present This fuel system will be used in conjunction rate These variations obscured any effects of dissolved oxygen with the PRAC electronic control The paper describes this system The results indicate that tests to determine the effects of dissolved and highlights critical design and development areas Author oxygen on thermal stability of jet fuel at supercritical conditions will have to be run with carefully controlled test pressures GRA N75-23600 Dowty Fuel Systems Ltd Cheltenham (England) PUMPING SYSTEM DESIGN RELATED TO FUEL SYSTEM N75-23604# Exxon Research and Engineering Co Linden NJ SPECIFICATIONS Government Research Lab A T Miles In AGARD Power Plant Controls for Aero-Gas DEVELOPMENT OF HIGH STABILITY FUEL Final Report. Turbine Eng Mar 1975 32 p 1 Jul - 31 Dec 1974 William F Taylor and John W Grankenfeld Jan 1975 123 p Design of the pump in its context the fuel system is refs discussed System requirements are related to pump limitations (Contract N00140-74-C-0618) So varied are the requirements that the pumps have to be (AD-A007574 GRU13GAHF75) Avail NTIS CSCL 21/4 specifically designed for the system Discussion first centers on The study of oxygenated trace impurities on the stability of optimizing low pressure systems to minimize heat rejection to Humble JP-5 was extended to include a typical aliphatic-aromatic the fuel The concepts of net positive suction head and vapor ester (methyl benzoate) an aliphatic ester (phenyl formate) an liquid ratio are contrasted in the context of cavitation Description aliphatic alcohol (n-dodecyl alcohol) and a ketone (5-nonanone) of two phase flow regimes leads to particular focus on the All were evaluated in deoxygenated Humble JP-5 at the 100 PPM engine driven backing pump Design philosophy to cope with 0 level Hexanoic was also investigated Six new diolefms were contaminated fuel is followed by an analysis of turn down heat evaluated in a deoxygenated synthetic 4-component blend This to fuel problems as they affect the high pressure dry engine blend consisted of 25% (by weight) of n-dodecane 25% of pump and the afterburner pump The large afterburner turn down 2 2 5-tnmethylhexane 30% of isopropylcyclohexane and 20% of flow ratio justifies the vapor core pump design and its principle secbutylbenzene The results confirm the previous observations of operation is outlined Author that structural features play an important part in determining the influence of olefms on deposit formation A representative N75-23601 Colt Industries Inc West Hartford Conn substituted acetylene 1-decyne was also tested in the 4-compo- ADVANCED ENGINE MOUNTED FUEL PUMP TECHNOL- nent synthetic blend Two condensed ring hydrocarbons mdan OGY and tetralm were tested in a new 4-component blend Scanning John E Cygnor In AGARD Power Plant Controls for Aero-Gas electron microscope studies of deposit morphology were extended
366 N75-23775
to pure hydrocarbon blends containing various amounts of The features of existing wind tunnels involved in noise studies dissolved oxygen A survey of the use of acid washing caustic are discussed The acoustic characteristics of the MIT low noise washing and absorbents in refining of jet fuel was conducted to open |et wind tunnel are obtained by employing calibration determine the possible changes tn trace impurity content brought techniques one technique is to measure the decay of sound about by such processing steps GRA pressure with distance in the far field the other technique is to utilize a speaker which was calibrated as a sound source The N75-23605# Air Force Aero Propulsion Lab Wright-Patterson sound pressure level versus frequency was obtained in the wind AFB Ohio tunnel chamber and compared with the corresponding calibrated PRACTICAL STABILITY OF A RELUCTANCE SYNCHRO- values Fiberglas board-block units were installed on the chamber NOUS MACHINE Final Report. Oct 1973 - Mar 1974 interior The free field was increased significantly after this William U Borger Feb 1975 81 p refs treatment and the chamber, cut-off frequency was reduced to (AF Pro) 3145) 160 Hz from the original designed 250 Hz The flow field (AD-A007659 AFAPL-TR-74-118) Avail NTIS CSCL 09/3 characteristics of the rotor-tunnel configuration were studied by The ideal reluctance synchronous machine with dual rotor using flow visualization techniques The influence of open-jet windings is modeled mathematically and simulated on a digital shear layer on the sound transmission was studied by using an computer In addition it is demonstrated that practical stability Aeolian tone as the sound source A dynamometer system was of the machine exists when the bapunov theorem requirements designed to measure the steady and low harmonics of the rotor have been met GRA thrust A theoretical Mach number scaling formula was developed to scale the rotational noise and blade slap noise data of model rotors to full scale helicopter rotors Author N75-23606*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif A FORMAL STRUCTURE FOR ADVANCED AUTOMATIC N75-23617# General Dynamics/Fort Worth Tex FLIGHT-CONTROL SYSTEMS AIRCRAFT ENGINE NACELLE FIRE TEST SIMULATOR Final George Meyer and Luigi Cicolam Washington May 1975 39 p Report. 1 Apr - 1 Dec 1974 refs R J Springer Dec 1974 237 p refs (NASA-TN-D-7940 A-5710) Avail NTIS HC $3 75 CSCL (Contract F33615-74-C-2035 AF Pro) 3048) 01D (AD A007853 AFAPL-TR-74-101) Avail NTIS CSCL 01/3 Techniques were developed for the unified design of The objective of this program was to develop design rationale multimode variable authority automatic flight-control systems for test criteria and complete detail design of an aircraft engine powered-lift STOL and VTOL aircraft A structure for such systems nacelle fire test simulator The fabrication of a simulator from is developed to deal with the strong nonlmearities inherent in the detail design of this program will allow a more realistic this class of aircraft to admit automatic coupling with advanced investigation of engine nacelle fire problems and the evaluation air traffic control and to admit a variety of active control tasks of fire prevention hardware detection and extinguishment systems The aircraft being considered is the augmentor wing jet STOL generated by aircraft programs The fabrication of the simulator research aircraft Author was not a part of this program This report documents the steps taken in defining the simulator design goals and require- N75-23607# Cranfield Inst of Technology (England) Flight ments conduct,ng of preliminary design trade-off studies the Div selection of a final simulator configuration and detail design of THE INFLUENCE OF SHORT SPRINGS ON LONGITUDINAL this simulator GRA STATIC STABILITY M E Eshelby Mar 1975 41 p refs (Cranfield-Aero-29) Avail NTIS HCS375 N75-23709 Messerschmitt-Boelkow GmbH Ottobrunn (West The theory of springs as stability augmentors is discussed Germany) and comparison made between ideal long springs and the short DESIGN OF COMPOSITE STRUCTURE WITH RESPECT TO springs more commonly found in light aircraft Data and AVOID CRACK PROPAGATION information from recent flight development trails are analysed K Brunsche In AGARO Specialists Meeting on Failure Modes to provide a practical demonstration of the effects produced of Composite Mater With Organic Matrices and Their Conse- Author quences on Design Mar 1975 9 p ref
N75-23608# Cornell Umv Ithaca N Y Sibley School of Within the manifold of composite structures developed rotary Mechanical and Aerospace Engineering wings are the best known components Several types of composite RESEARCH ON HELICOPTER ROTOR NOISE Final Report. rotorblades have been developed tested and produced The 2 Oct 1973 - 31 Dec 1974 experience with fatigue testing many GFP CFP and mixed modulus A R George 10 Feb 1975 17 p refs coupons and full scale blade sections is used to make some (Contract DAHC04-74-C-0001) design recommendation how crack propagation might be avoided (AD-A007261 ARO-9372-6-E) Avail NTIS CSCL 01/3 Respect is given to both influence of fabrication and influence During the period of this contract research was carried out of environment For some cases deformation limits up to which on three main aspects of helicopter rotor noise These were no damage propagation occurs are given Author the prediction of broadband noise due to random loadings high Speed blade noise and noise due to the acceleration of solid bodies The noise due to the acceleration of solid bodies was N75-23775# Reynolds Metals Co Richmond Va Metallurgical investigated experimentally and compared to calculations based Research Div on Farassat s results The final results show excellent agreement PROGRAM TO IMPROVE THE FRACTURE TOUGHNESS between theory and experiment and a paper has been submitted AND FATIGUE RESISTANCE OF ALUMINUM SHEET AND to the Journal of Sound and Vibration reporting this work GRA PLATE FOR AIRCRAFT APPLICATIONS. VOLUME 2 Final Report. 1 Mar - 1 Jul 1974 N75-23611*# Massachusetts Inst of Tech Cambridge Fluid David S Thompson and Robert E Zinkham Sep 1974 82 p Dynamics Research Lab refs THE DEVELOPMENT OF EXPERIMENTAL TECHNIQUES (Contract F33615-74-C-5060 AF Proj 7351) FOR THE STUDY OF HELICOPTER ROTOR NOISE Final (AD-A003417 AFML-TR-73-247-Vol-2) Avail NTIS CSCL Report. Jun 1973 - Nov 1974 11/6 Sheila E Widnall. Wesley L Harris. Ymg-Chieh Albert Lee and The fatigue crack growth rate (FCGR) characteristics of a Herman M Drees Nov 1974 89 p refs Sponsored in part 7000 series and a 2000 series alloy were evaluated The bulk by Army Air Mobility R and D Lab, Moffett Field Calif of the work was carried out on thermomechanically aged (TMA) (Contract NAS2-7684) RX725 (AI-6Zn-25Mg-1 5Cu- 1 Zr) and 2048 in the TMA and (NASA-CR-137684) Avail NTIS HC $4 75 CSCL 14B •T3E9 tempers respectively Crack growth rate was reduced by
367 N75-23885 either crack branching or deviation of the crack from the plane Fatigue tests were earned out on aluminum alloy lugs with normal to the applied stress Both experimental materials were different hole diameters and configurations A strong improve- found to be sensitive to environment (high or low humidity) ment in fatigue properties was observed in cases of relative even though they were resistant to exfoliation corrosion An mtereference fits larger than 02% The effect of the stresses inverse hyperbolic tangent model fitted the data well, but the produced by the interference fit were theoretically analyzed and parameters in the model did not lend themselves to characterizing the critical stress level below which the interference fit has a FCGR material performance It was concluded that significant beneficial effect was determined A method for evaluation of benefits could be achieved by TMA processing GRA the fatigue life of interference-fit aluminum lugs is proposed Author
N75-23885*# National Aeronautics .and Space Administration N75-24032*# Boeing Aerospace Co Seattle. Wash Langley Research Center Langley Station Va DESIGN AND FABRICATION OF RENE 41 ADVANCED SUBSCALE. HYDROGEN-BURNING. AIRFHAME- STRUCTURAL PANELS INTEGRATED SCRAMJET EXPERIMENTAL AND THEO- Bruce E Greene and Russell F Northrup [1975] 59 p refs RETICAL EVALUATION OF A WATER COOLED STRUT (Contract NAS1-10749) AIRFRAME-INTEGRATED SCRAMJET EXPERIMENTAL (NASA-CR-132646) Avail NTIS HCS425 CSCL13M LEADING EDGE The efficiency was investigated of curved elements in the S Z Pmckney R W Guy H L Beach and R C Rogers May design of lightweight structural panels under combined loads of 1975 43 p refs axial compression inplane shear and bending The application (NASA-TM-X-72682) Avail NTIS HC $3 75 CSCL01C is described of technology generated in the initial aluminum A water-cooled leading-edge design for an engme/airframe program to the design and fabrication of Rene 41 panels for integrated scramiet model strut leading edge was evaluated The subsequent performance tests at elevated temperature Optimum cooling design employs a copper cooling tube brazed just designs for two panel configurations are presented The designs downstream of the leading edge of a wedge-shaped strut which are applicable to hypersonic airplane wing structure and are is constructed of oxygen-free copper The survival of the strut designed specifically for testing at elevated temperature in the leading edge during a series of tests at stagnation point heating hypersonic wing test structure located at the NASA Flight rates confirms the practicality of the cooling design A finite Research Center Fabrication methods developed to produce the difference thermal model of the strut was also proven valid by Rene panels are described and test results of smaller structural the reasonable agreement of calculated and measured values of element specimens are presented to verify the design and surface temperature and cooling-water heat transfer Author fabrication methods used Predicted strengths of the panels under several proposed elevated temperature test load conditions are presented Author N75-23906# Air Force Systems Command Wright-Patterson AFB Ohio Foreign Technology Div N75-24044# Air Force Systems Command, Wright-Patterson NATURAL OSCILLATIONS OF LIQUID IN A HORIZONTAL AFB, Ohio Foreign Technology Div CONTAINER WITH SYMMETRIC DOUBLE-CONNECTED STRESS CONCENTRATION IN AN EXPANDED PLATE WITH CROSS SECTION OPENING REINFORCED BY CENTRAL BELT I V Kolm 24 Jan 1975 17 p refs Transl into ENGLISH V I Gnshm 28 Jan 1975 22 p refs Transl into ENGLISH from Tsentr Aerogidrodmamicheskii Inst Uch Zap (USSR) v 2 from Uch Zap Tsentr Aerogidrodmamicheskii Inst (USSR) v 3, no 3 1971 p 117-120 no 6 1972 p 101-106 (AD-A007312 FTD-MT-24-0582-75) Avail NTIS CSCL 20/4 (AD-A007672 FTD-M T-24-0521-75) Avail NTIS CSCL The approximate differential equations were obtained for 20/11 determining natural vibration frequencies of liquid and coordinates The finite element method was used to determine stress of the points of application of flow forces Calculation results concentration in a plate with grooves The objective was to are compared with experimental results Other topics discussed determine the effect of proximity of the stringer to opening/ include computer techniques digital computers stability analysis aperture on stress concentration in the expanded plate Author and disturbed motion of winged flight vehicles M J S N75-24186# Informatics Inc Rockville Md N75-23946# United Aircraft Corp East Hartford Conn CIVIL AVIATION STUDIES AND INTERAGENCY COORDI- NATING ORGANIZATIONS. VOLUME 1 Research Labs Carl Modig Dec 1974 165 p refs 2 Vol NONDESTRUCTIVE HOLOGRAPHIC TECHNIQUES FOR (Contract EPA-68-01-2229) STRUCTURES INSPECTION Final Report, 1 Jul 1971 - (PB-239344/5 EPA-550/9-74-019A-Vol-1) Avail NTIS 30 Apr 1974 HC $625 CSCL 01C Robert K Erf Ronald M Gagosz James P Waters Karl A Stetson and Herbert G Aas Oct 1974 181 p refs Federal organizations set up to coordinate civil aviation policy are described including those dealing with the aircraft noise (Contract F3361 5-7 1-C-1874 AF Proj 7351) problem and commissions and agency task groups who studied (AD-A007850 UARL-N991208-36 AFML-TR-74-130) Avail civil aviation problems The evolution of these organizations from NTIS CSCL 14/2 after World War II to the present is traced It is concluded The theoretical and experimental work performed during a that (1) in the early 1960s there was no institution actively three year study concerned with a research investigation of coordinating federal aircraft noise abatement activities (2) much nondestructive holographic techniques for structures inspection of the impetus for better coordination has come from Congress are reviewed Topics discussed include the following General (3) successful coordination requires high-level agency and studies - physical environment effects General studies - surface Administration support (4) the host agency may have difficulty finish effects General studies - develop suitable techniques for securing cooperation of other agencies GRA a manufacturing or maintenance environment Specific problem investigations - maximum strain and strain patterns Specific N75-24187* Informatics Inc Rockville Md problem investigations - fatigue cracks Specific problem investigations - NDT GRA CIVIL AVIATION STUDIES AND INTERAGENCY COORDI- NATING ORGANIZATIONS,VOLUME 2 APPENDICES Carl Modig Dec 1974 180 p refs 2 Vol (Contract EPA-550/9-74-019B) N75-24031# Techmon - Israel Inst of Tech Haifa Dept of (PB-239345/2 EPA-550/9-74-0198-Vol-2) Avail NTIS Aeronautical Engineering HC $7 00 CSCL QIC FATIGUE PROPERTIES OF AIRCRAFT LUGS WITH Source documents are reproduced in whole or in part to INTERFERENCE FIT provide more detailed information on various federal organizations Alfred Buch Feb 1975 62 p refs set up to coordinate or study civil aviation policy including those (TAE-243) Avail NTIS HC $4 25 CSCL 13E dealing with the aircraft noise problem GRA
368 N75-24675
N75-24192# ARO Inc Arnold Air Force Station Tenn A digital computer program has been developed to calculate DROPLET DIAMETER AND SIZE DISTRIBUTION OF JP-4 unsteady loadings caused by motions of lifting surfaces with FUEL INJECTED INTO A SUBSONIC AIRSTREAM Final leading edge or trailing edge controls based on the subsonic Report, 22 Oct - 12 Dec 1973 kernel function approach The pressure singularities at hinge line R A Wasson Jr C R Darlington and J C Billmgsley AEDC and side edges have been extracted analytically as a preliminary Apr 1975 43 p refs step to solving the integral equation by collocation The program (AD-A007687 ARO-ETF-TR-74-92 AEDC-TR-74-1 17) Avail calculates generalized aerodynamic forces for user supplied NTIS CSCL21/4 deflection modes Optional intermediate output includes pressure A test program was conducted to determine the size and at an array of points, and sectional generalized forces From distribution of JP-4 fuel droplets when fuel was dispersed at a one to six controls on the half span can be accommodated constant fuel nozzle exit velocity into a subsonic airstream Testing Author was conducted at free-stream flight velocities ranging from 200 to 400 knots at altitudes ranging from 12000 to 25000 feet N75-24673*# National Aeronautics and Space Administration with flow rates of approximately 13 75 and 290 Ibm/min Langley Research Center, Langley Station Va Holograms of the fuel droplets were taken 18 feet downstream ANALYSIS OF VARIOUS DESCENT TRAJECTORIES FOR of the fuel nozzle exit plane Representative histograms of fuel A HYPERSONIC-CRUISE, COLD-WALL RESEARCH AIR- droplet size distribution and average fuel droplet diameter are PLANE presented Average fuel droplet diameter was not significantly Pierce L Lawing Washington Jun 1975 62 p refs affected by any of the test variables All arithmetic average fuel (NASA-TN-D-7860, L-9778) Avail NTIS HC $4 25 CSCL droplet diameter data were within a 19 to 36-micrometer 01A band GRA The probable descent operating conditions for a hypersonic air-breathing research airplane were examined Descents selected were cruise angle of attack high dynamic pressure, high lift N75-24436# Wiggins (J H ) Co Redondo Beach Calif coefficient turns and descents with drag brakes The descents SOUND AND VIBRATION MEASUREMENTS FOR CON- were parametncally exercised and compared from the standpoint CORDE SUPERSONIC TRANSPORT AND SUBSONIC JET of cold-wall (367 K) aircraft heat load The descent parameters AIRCRAFT Final Report. Jan - Jul 1974 compared were total heat load, peak heating rate, time to landing John H Wiggins 31 Jul 1974 118 p refs time to end of heat pulse and range Trends in total heat load (Contract DOT-OS-40121) as a function of cruise Mach number cruise dynamic pressure (PB-238748/8 DOT-TST-75-211 Avail NTIS HC $5 25 CSCL angle-of-attack limitation pull-up g-load heading angle, and 20A drag-brake size are presented Author Sound and structural vibration levels resulting from operations of both supersonic (SST) and conventional subsonic jet aircraft N75-24674*# Aerophysics Research Corp Bellevue Wash are analyzed The study first analyzes the potential differences AN INVESTIGATION ON THE EFFECT OF SECOND-ORDER in noisiness between SST and conventional aircraft knowing ADD! TIONAL THICKNESS DISTRIBUTIONS TO THE UPPER only the sound pressure spectra Next results of monitored SST SURFACE OF AN NACA 64 SUB 1-212 AIRFOIL and conventional aircraft flights conducted at Fairbanks Alaska Donald S Hague and Antony W Merz Jan 1975 47 p refs International Airport on February 11 -1 5 1974 are reported These Supercedes TN-194 results test the hypothesis put forth in the analytical portion of (Contract NAS2-8599) the report GRA (NASA-CR-137701 TN-194) Avail NTIS HC S3 75 CSCL 01C N75-24654*# National Aeronautics and Space Administration An investigation was conducted on a COC 7600 digital Washington D C computer to determine the effects of additional thickness KOROLEV A CHRONICLE distributions to the upper surface of an NACA 64 sub 1-212 Yaroslav Golovanov Apr 1975 231 p refs Transl into ENGLISH airfoil Additional thickness distributions employed were in the from the book Korolev Khronika Moscow Molodaya Gvardiya form of two second-order polynomial arcs which have a specified 1973 p 1-254 thickness at a given chordwise location The forward arc disappears (NASA-TT-F-16278) Avail NTIS HC $7 50 CSCL 05B at the airfoil leading edge the aft arc disappears at the airfoil, A partial biography of Sergey Pavlovich Korolev is presented trailing edge At the juncture of the two arcs x = x, continuity which covers his life from birth to the age of 28 A history of of slope is maintained The effect of varying the maximum the development of Soviet space and rocket technology during additional thickness and its chordwise location on airfoil lift those 28 years is also included M J S coefficient pitching moment, and pressure distribution was investigated Results were obtained at a Mach number of 0 2 with an angle-of-attack of 6 degrees on the basic NACA N76-24671* National Aeronautics and Space Administration 64 sub 1 - 212 airfoil, and all calculations employ the full Ames Research Center M often Field, Calif potential flow equations for two dimensional flow The relaxation LARGE-SCALE WIND-TUNNEL TESTS OF THREE VEHICLES method of Jameson was employed for solution of the potential INCORPORATING A DEPLOYABLE RIGID WING flow equations Author Terrell W Feistel and Ralph L Maki Aug 1974 64 p ref (NASA-TM-X-62405 A-5854) Avail NTIS HCS425 CSCL N76 24676*# Aerophysics Research Corp Bellevue. Wash 01B AN INVESTIGATION ON THE EFFECT OF SECOND-ORDER Wmd-tunnel tests were performed to determine the aerody- ADDITIONALTHICKNESS DISTRIBUTIONS TO THE UPPER namic characteristics of three full-scale vehicles incorporating a SURFACE OF AN NACA 64-206 AIRFOIL unique folding metal wing, and to investigate its deployment Antony W Merz and Donald S Hague Feb 1975 32 p refs characteristics The static aerodynamic data are presented without Supercedes TN-195 analysis Author (Contract NAS2-8599) (NASA-CR-137702 TN-195) Avail NTIS HC $3 75 CSCL N75-24672*# Boeing Co, Renton, Wash 01C PREDICTION OF UNSTEADY AERODYNAMIC LOADINGS An investigation was conducted on a CDC 7600 digital CAUSED BY LEADING EDGE AND TRAILING EDGE computer to determine the effects of additional thickness CONTROL SURFACE MOTIONS IN SUBSONIC COM- distributions to the upper surface of an NACA 64-206 airfoil PRESSIBLE FLOW COMPUTER PROGRAM DESCRIP- Additional thickness distributions employed were in the form of TION two second-order polynomial arcs which have a specified thickness M C Redman and W S Rowe May 1975 157 p refs at a given chordwise location The forward arc disappears at (Contract NAS1-12020) the airfoil leading edge the aft arc disappears at the airfoil (NASA-CR-132634) Avail NTIS HC $6 25 CSCL 20K trailing edge At the juncture of the two arcs x = x continuity
369 N75-24676 of slope is maintained The effect of varying the maximum Robert J McGhee William D Beasley. and Dan M Somers additional thickness and its chordwise location on airfoil lift May 1975 57 p refs coefficient pitching moment and pressure distribution was (Pro) FEDD) investigated Results were obtained at a Mach number of 0 2 (NASA-TM-X-72697) Avail NASA Industrial Applications with an angle-of-attack of 6 degrees on the basic NACA 64-206 Centers only to U S Requesters HC $4 25/MF $2 25 CSCL airfoil, and all calculations employ the full potential flow equations 01A for two dimensional flow The relaxation method of Jameson Wind-tunnel tests were conducted to determine the low-speed was employed for solution of the potential flow equations section characteristics of a 13-percent-thick airfoil designed for Author general aviation applications The results are compared with NACA 12-percent-thick sections and with the 17-percent-thick NASA airfoil The tests are conducted over a Mach number range from N75-24676*# Aerophysics Research Corp Bellevue Wash 0 10 to 0 35 Chord Reynolds numbers vary from about 2 million THEORETICAL EFFECT OF MODIFICATIONS TO THE to 9 million Author UPPER SURFACE OF TWO NACA AIRFOILS USING SMOOTH POLYNOMIAL ADDITIONAL THICKNESS DIS- TRIBUTIONS WHICH EMPHASIZE LEADING EDGE N75-24680# Royal Aircraft Establishment Farnborough PROFILE AND WHICH VARY QUADRATICALLY AT THE (England) TRAILING EDGE AN EXPERIMENTAL INVESTIGATION ON THE TRANSONIC Anthony W Merz and Donald S Hague Mar 1975 40 p FLUTTER CHARACTERISTICS OF THE CANTILEVER refs Supersedes TN-199 SWEPT-BACK WING WITH AEROFOIL SECTION. AND (Contract NAS2-8599) COMPARISON WITH THE THIN CANTILEVER SWEPT- (NASA-CR-137703 TN-199) Avail NTIS HC $3 75 CSCL BACK WING 01C T Monta E Nakai and T Kikuchi Mar 1975 21 p refs An investigation was conducted on a CDC 7600 digital Transl into ENGLISH from the Japanese report NAL-TR-361 computer to determine the effects of additional thickness (RAE-Lib-Trans-1838 BR47558. NAL-TR-361) Avail NTIS distributions to the upper surface of the NACA 64-206 and HC $325 64 sub 1 - 212 airfoils The additional thickness distribution Transonic flutter characteristics of a cantilever swept-back had the form of a continuous mathematical function which wing at Mach numbers from 0 756 to 0 978 were studied in a disappears at both the leading edge and the trailing edge The 60cm x 60cm transonic blow-down wind tunnel for comparison function behaves as a polynomial of order epsilon sub 1 at the with those of the thin cantilever swept-back wing The Reynolds leading edge and a polynomial of order epsilon sub 2 at the numbers of the experiments were over about 1 million The two trailing edge Epsilon sub 2 is a constant and epsilon sub 1 is wing models used with and without a mass of engine pod varied over a range of practical interest The magnitude of the attached had a streamwise airfoil section a sweep-back angle additional thickness y is a second input parameter and the of 20 deg at the quarter-chord point and an aspect ratio and effect of varying epsilon sub 1 and y on the aerodynamic taper ratio of 8 and 0 4 respectively The boundaries of flutter performance of the airfoil was investigated Results were obtained density and experimental flutter-speed coefficients are char- at a Mach number of 0 2 with an angle-of-attack of 6 degrees acterized by minimum values at Mach numbers in the vicinity on the basic airfoils and all calculations employ the full potential of 0 9 The flutter characteristics resemble those from previous flow equations for two dimensional flow The relaxation method tests of flat-plate cantilever swept-back wings It was found of Jameson was employed for solution of the potential flow that the aerofoil section has a stabilizing effect except in the equations Author case of the wing with engine pod at the highest Mach numbers Author N75-24677*# North Carolina State Umv Raleigh LIGHT AIRCRAFT LIFT, DRAG. AND MOMENT PREDIC- N75-24681 *# National Aeronautics and Space Administration TION A REVIEW AND ANALYSIS Langley Research Center Langley Station, Va Frederick 0 Smetana Delbert C Summey Neill S Smith and ANALYSIS OF TRANSONIC FLOW ABOUT LIFTING Ronald K Garden Washington NASA May 1975 489 p WING-BODY CONFIGURATIONS refs Richard W Barnwell Washington Jun 1975 73 p refs (Grant NGR-34-002-179) (NASA-TR-R-440 L-9969) Avail NTIS HC $4 25 CSCL 01A (NASA-CR-2523) Avail NTIS HCS1200 CSCL01A An analytical solution was obtained for the perturbation The historical development of analytical methods for predicting velocity potential for transonic flow about lifting wing-body the lift drag and pitching moment of complete light aircraft configurations with order-one span-length ratios and small configurations in cruising flight is reviewed Theoretical methods reduced-span-length ratios and equivalent-thickness-length ratios based in part on techniques described in the literature and in The analysis is performed with the method of matched asymptotic part on original work are developed These methods form the expansions The angles of attack which are considered are small basis for understanding the computer programs given to (1) but are large enough to insure that the effects of lift in the compute the lift, drag and moment of conventional airfoils (2) region far from the configuration are either dominant or comparable extend these two-dimensional characteristics to three dimensions with the effects of thickness The modification to the equivalence for moderate-to-high aspect ratio unswept wings (3) plot complete rule which accounts for these lift effects is determined An analysis configurations (4) convert the fuselage geometric data to the of transonic flow about lifting wings with large aspect ratios is correct input format (5) compute the fuselage lift and drag (6) also presented Author compute the lift and moment of symmetrical airfoils to M = 1 0 by a simplified semi-empirical procedure and (7) compute, in closed form the pressure distribution over a prolate spheroid N75-24683# European Space Research Organization Pans at alpha = 0 Comparisons of the predictions with experiment (France) indicate excellent lift and drag agreement for conventional airfoils DYNAMIC AND AEROELASTIC PROBLEMS OF STOP- and wings Limited comparisons of body-alone drag characteristics ROTORS AND THEIR ANALYTICAL TREATMENT PART 2 yield reasonable agreement Also included are discussions for ANALYTICAL EQUATIONS AND SOLUTIONS interference effects and techniques for summing the results above H Foerschmg Mar 1975 82 p refs Transl into ENGLISH to obtain predictions for complete configurations Author of Dynamische u aeroelastische Probleme des Stop-Rotors u ihre anal Behandlung Teil 2 Anal Ansaetze u Loesungsverfahr- N75-24678*# National Aeronautics and Space Administration en' DFVLR Goettingen. West Ger Report DLR-FB-73-19 1973 Langley Research Center Langley Station Va Original German report available from DFVLR Porz West Ger LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A 17 40 DM 13-PERCENT THICK AIRFOIL SECTION DESIGNED FOR (ESRO-TT-145-Pt-2 DLR-FB-73-19) Avail NTIS HC $4 75 GENERAL AVIATION APPLICATIONS An Early Domestic Based on previously derived relationships the appropriate Dissemination Report equations and solutions are presented for the analytical treat-
370 N75-24699 ment of the dynamic and aeroelastic problems of stop-rotors of Final Report. 1 Oct 1972 - 30 Sep 1973 V/STOL aircraft In particular the problems of static torsional Toshi Kubota ?8 Mar 1975 39 p refs stability, flutter behavior, and gust loads on rotor blades occurring (Contract DAHC04-72-C-0029) during the stop phase and during blade folding and retraction (AD-A008417, GALCIT-138. ARO-10869 1-E) Avail NTIS were investigated Author (ESRO) CSCL 20/4 The wake behind a self-propelled body is studied for laminar and turbulent cases For the laminar wake, asymptotic solutions are obtained with and without swirl For the turbulent wake N75-24685# European Space Research Organization Pans with the eddy-viscosity model the solution is obtained from the (France) laminar flow solution by transformation that reduces the INFLUENCE OF A PLAIN FLAP WITH A BLUNT. NOTCHED turbulent-flow equation to the equation for laminar flow With TRAILING EDGE ON THE LIFT OF A RECTANGULAR the mixing-length model for the turbulent shear stress, the far-wake WING solution becomes that of non-linear eigenvalue problem These M Tanner Mar 1975 20 p refs Transl into ENGLISH of two models yield results that do not agree with experimental "Einfluss einer Woelbungsklappe mit stumpfer gebrochener results The far-wake solution is formulated based on a two- Hmteckante auf den Auftneb emes Rechteckfluegels" DFVLR, equation model for turbulent shear—turbulent energy and Goettingen. West Ger Report DLR-FB-73-122, Oct 1973 dissipation--with an additional assumption of negligible turbulence Original German report available from DFVLR, Porz West Ger production from the mean flow GRA 9 DM (ESRO-TT-147 DLR-FB-73-122) Avail NTIS HC S3 2§ The influence of a plain flap with a blunt, notched trailing N75-24693# Army Missile Research, Development and edge on the lift of a rectangular wing was investigated in a 3m Engineering Lab. Redstone Arsenal Ala Aeroballistics wind tunnel The results show that for all the investigated flap Directorate angles from 0 to 45 deg the maximum lift coefficient is greater THEORETICAL DOWNWASH VELOCITIES ABOUT THE than for a wing with a sharp trailing edge while the flap efficiency AH-1G HELICOPTER AT HOVER AND 140 KNOTS coefficient is of approximately the same magnitude in both Alma S Marks 13 Dec 1974 161 p cases Author (ESRO) (DA Proj 1M2-62303-A-214) (AD-A008339 RD-75-21) Avail NTIS CSCL 01/3 Current programs in helicopter armament have not adequately N75-24688# ARO Inc Arnold Air Force Station, Tenn treated the problem of the rocket or missile's response to the AN INVESTIGATION OF THE FLOW FIELD OF THE A-7D aircraft's downwash In this analysis, the downwash is represented AIRCRAFT WITH SEVERAL EXTERNAL STORE LOADINGS as vortex filaments shed from the rotor tips, and the fuselage is AT MACH NUMBERS 070 AND 095 Final Report represented by a source distribution The vehicle and flight data J B Carman Jr Apr 1975 79 p refs Prepared in cooperation and the downwash velocity components for hover and forward with Arnold Eng Develop Center flight cases are given GRA (AD-A008476 A EDC-TR-75-15 AFATL-TR-75-21) Avail NTIS CSCL01/3 Wind tunnel tests were conducted using 0 05-scale models N75-24696*# United Air Lines Inc San Francisco Calif to study the flow field of the A-7D aircraft with several different THE OUT OF SERVICE GUEST PILOT EVALUATION OF external store load configurations The flow-angularity data were THE TWO-SEGMENT NOISE ABATEMENT APPROACH IN obtained at selected axial lateral and vertical positions under THE BOEING B727-200 the inboard, center and outboard pylons of both wings of the W E Nylen 30 Jan 1974 85 p aircraft Parent aircraft angles of attack were 2 6 and 10 deg (Contract NAS2-7208) at zero sideslip for free-stream Mach numbers of 0 70 and (NASA-CR-137625) Avail NTIS HCS475 CSCL 20A 095 GRA Guest pilot evaluation results of an approach profile modifica- tion for reducing ground level noise under the approach of jet N76-24689# Massachusetts Inst of Tech , Cambridge Aeroelas- aircraft runways are reported Evaluation results were used to tic and Structures Research Lab develop a two segmented landing approach procedure and SUMMARY OF MIT RESEARCH ON DYNAMIC STALL AND equipment necessary to obtain pilot airline, and FAA acceptance BLADE-VORTEX INTERACTION. 1971 - 1974 of the two segmented flight as a routine way of operating aircra't Norman D Ham Sep 1974 28 p refs on approach and landing Data are given on pilot workload and (Contract DA-31-124-ARO(D)-247) acceptance of the procedure E H W (AD-A008091 ASRL-TR-130-4. ARO-4846-17-E) Avail NTIS CSCL 01/1 A previous MIT investigation indicated that during the close interaction of a vortex with a rotating blade, the measured N76 24698# Mitre Corp. McLean, Va vortex-induced unsteady loading on the blade differed greatly SAFETY-RELATED ENGINEERING AND DEVELOPMENT from that predicted by lifting-surface theory, both in peak ACTIVITIES OF THE FEDERAL AVIATION ADMINISTRA- magnitude and in chordwise distribution The experimental results TION suggested the occurrence of local separation in the region of Jerold M Chaukm and Marvin E Kay Mar 1975 112 p most intense vortex-induced loading During the past year, (Contract DOT-FA70WA-2448) blade-vortex interaction was studied by subjecting the midsection (AD-A008395. M75-24, FAA-EM-75-2) Avail NTIS of a'pressure-instrumented airfoil, mounted horizontally and HC $525 perpendicular to the wind-tunnel airstream, to the impingement The FAAs engineering and development (E&D) program of a vortex moving periodically in the vertical plane from a directly related to the goal of improving air safety is defined point below the airfoil to a point above the airfoil and back Those safety-related E&D activities are categorized to correspond again The results of this investigation have shown that the with associated categories of aviation accidents/fatalities maximum vortex-induced lift coefficients are of the order of 0 2 Statistics on aircraft accidents/fatalities for the period January to 0 3 The vortex-induced peak loadings were found to be 1964 to December 1972 are presented for each category A independent of the frequency of vortex impingement d e, vortex summary description of each safety-related E&D activity is approach velocity) proportional to vortex strength and only presented including the safety-related goals, current status and weakly dependent upon airfoil angle of attack and angle of future plans Funding, by category, is presented for FY72-FY75 yaw GRA Author
N76-24690# California Inst of Tech Pasadena Graduate N75-24699# Air Force Weapons Lab Kirtland AFB N Mex Aeronautical Labs A RADAR AND DIRECT VISUAL STUDY OF THE HAZARD TURBULENT WAKE BEHIND A SELF-PROPELLED BODY TO AIRCRAFT FROM BIRD MIGRATIONS IN THE SOUTH
371 N75-24701
WEST Final Report. 1 Apr 1972 - 31 Dec 1973 AND FRACTURE CRITERIA ON WEIGHT AND COST OF Robert C Season Mar 1975 19 p refs TRANSPORT AIRCRAFT (AD-A008198) Avail NTIS CSCL01/2 C J Tanner G S Kruse, and B H Oman Jun 1975 109 p The increasing number of aircraft accidents caused by bird refs strikes while the aircraft is in flight is a concern of the Air (Contract NAS1-12506) Force The report concentrates on the danger during low-altitude (NASA-CR-132648) Avail NTIS HC $5 25 CSCL01C high-speed missions as well as takeoffs and landings at a fixed A preliminary design analysis tool for rapidly performing base Methods for obtaining data are discussed with results from trade-off studies involving fatigue, fracture, static strength, weight, locations throughout the U S and the data are presented to and cost is presented Analysis subprograms were developed for show the concentrated areas where birds migrate Recommenda- fatigue life, crack growth life, and residual strength and linked tions are made for a continuing study and methods for supplying to a structural synthesis module which in turn was integrated flight-plan information that would avoid concentrated bird areas into a computer program The part definition module of a cost GRA and weight analysis program was expanded to be compatible with the upgraded structural synthesis capability The resultant vehicle design and evaluation program is named VDEP-2 It is N76-24701jj! National Transportation Safety Board. Washington, an accurate and useful tool for estimating purposes at the 0 C Bureau of Aviation Safety preliminary design stage of airframe development A sample case PAN AMERICAN WORLD AIRWAYS. INCORPORATED, along with an explanation of program applications and input BOEING 707-321 C. N458PA. BOSTON. MASSACHUSETTS. preparation is presented Author NOVEMBER 1973 Aircraft Accident Report 2 Dec 1974 120 p N75-24719*# Lockheed-California Co Burbank (PB-239448/4. NTSB-AAR-74-16) Avail NTIS HCS525 CSCL FLIGHT SERVICE EVALUATION OF PRD-49/EPOXY 01B COMPOSITE PANELS IN WIDE-BODIED COMMERCIAL The Boeing 707-321C (N458PA) crash at Logan International TRANSPORT AIRCRAFT Annual Flight Service Evaluation Airport Boston. Massachusetts was investigated Results indicate Report that the probable cause of the accident was the presence of John H Wooley Jul 1974 14 p smoke in the cockpit which was continuously generated and (Contract NAS1-11621) uncontrollable The smoke led to an emergency situation that (NASA-CR-132647 LR-26580) Avail NTIS HC $3 25 culminated in loss of control of the aircraft during final ap- Fairing panels were fabricated to evaluate the fabrication proach when the crew in uncoordinated action deactivated the characteristics and flight service performance of PRD-49 yaw damper in conjunction with incompatible positioning of flight (Kevlar-49) a composite reinforcing material and to compare it spoilers and wing flaps It is explained that the spontaneous with the fiberglass which is currently in use Panel configurations chemical reaction between leaking nitric acid improperly packaged were selected to evaluate the PRD-49 with two resin matrix and stowed, and the improper sawdust packing surrounding the materials in sandwich and solid laminate construction Left and acid's package initiated the accident sequence GRA right hand versions of these configurations were installed on L-1011 s which will accumulate approximately 3000 flight hours per year per aircraft The direct substitution of PRD-49 for N76-24702| National Transportation Safety Board, Washington. fiberglass produced a twenty-six percent weight reduction on D C Bureau of Aviation Safety the panel configurations Examination of these panels revealed SIERRA PACIFIC AIRLINES. INCORPORATED CONVAIR that there was no visible difference between the PRD-49 and 340/440, N4819C NEAR BISHOP, CALIFORNIA. 13 MARCH adjacent fiberglass panels Author 1974 Aircraft Accident Report 10 Jan 1975 34 p (PB-239511/9 NTSB-AAR-75-1) Avail NTIS HCS375 CSCL N75-24720*# National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif 016 A Convair 340/440 crash near Bishop California was NASA/ARMY XV 15 TILT ROTOR RESEARCH AIRCRAFT investigated The last recorded transmission from the flight FAMILIARIZATION DOCUMENT indicated that the aircraft was climbing under visual flight rules Jan 1975 105 p Prepared in cooperation with Army Air The aircraft crashed into a foothill of the White Mountains The Mobility R and D Lab Moffett Field. Calif National Transportation Safety Board was unable to determine (NASA-TM-X-62407 A-5870) Avail NTIS HC $5 25 CSCL the probable cause of the accident nor the reason why the 01C flightcrew did not maintain a safe distance from hazardous terrain The design features and general characteristics of the during night visual flight conditions GRA NASA/Army XV-15 tilt rotor research aircraft are described This aircraft was conceived as a proof-of-concept vehicle and a V/STOL research tool for integrated wind tunnel, flight-simulation and N75-24717*# Boeing Co Seattle Wash flight-test investigations Discussions of special design provisions ADVANCED BEADED AND TUBULAR STRUCTURAL and safety considerations necessary to perform these missions PANELS VOLUME 2 FABRICATION are included in this report In addition to predictions of aircraft Max D Musgrove and Russell F Northrup [1974] 49 p refs and engine performance for the hover, helicopter and airplane (Contract NAS1-10749) flight modes, analytical estimates of the structural and dynamic (NASA-CR-132482) Avail NTIS HC $3 75 CSCL01B limitations of the XV-15 are provided Author A study was conducted to exploit the efficiency of curved elements in the design of lightweight structural panels under N75-24721*# Foster-Miller Associates. Inc Waltham Mass combined loads of axial compression mplane shear, and bending DYNAMIC HEAVE-PITCH ANALYSIS OF AIR CUSHION A summary of the total program (analysis, fabrication and test) LANDING SYSTEMS is presented in document NASA CR-2514 Detailed descriptions K M Captain A B Boghani and D N Wormley Washington of the analysis effort and of the panel tests are contained in NASA May 1975 200 p supplementary documents NASA CR-132460 and (Contract NAS1-12403) NASA-CR-132515 respectively Data are also given on the (NASA-CR-2530) Avail NTIS HC $7 00 CSCL 01B development of economical fabrication techniques to minimize A program to develop analytical tools for evaluating the the effects of fabrication limitations on optimum panel designs dynamic performance of Air Cushion Landing Systems (ACLS) Author is described The heave (vertical) motion of the ACLS was analyzed and the analysis was extended to cover coupled heave-pitch motions The mathematical models developed are based on a fundamental analysis of the body dynamics and fluid mechanics N75-24718*# General Dynamics/Convair San Diego Calif of the aircraft-cushion-runway interaction The air source COMPUTER PROGRAM TO ASSESS IMPACT OF FATIGUE characteristics flow losses in the feeding ducts trunk and cushion
372 N75-24728
the effects of fluid compressibility, and dynamic trunk deflections, ADVANCED MANEUVERABILITY OPTIONS FOR FUTURE including ground contact are considered A computer program, FIGHTERS based on the heave-pitch analysis was developed to simulate Philip V Kulwicki and James M Smnett Mar 1975 35 p the dynamic behavior of an ACLS during landing impact and refs Presented at the Avionics Sect Meeting Amer Defense taxi over an irregular runway The program outputs include ACLS Preparedness Assoc , Point Mugu Calif 20-21 Nov 1974 motions, loadings, pressures and flows as a function of time (AF Pro) 7184) To illustrate program use three basic types of simulations were (AD-A008497 AMRL-TR-74-140) Avail NTIS CSCL 01/3 carried out The results provide an initial indication of ACLS Recent developments in fighter design technology have performance during (1) a static drop (2) landing impact and emphasized air combat maneuverability High thrust-to-weight (3) taxi over a runway irregularity Author ratio engines, advanced lightweight structures improved aerody- namic efficiencies and effective flight control systems develop- N75-24722*# National Aeronautics and Space Administration ments enable realization of more responsive higher levels of air Ames Research Center. Moffett Field, Calif combat maneuverability than ever before seen in fighter aircraft LOW SPEED WIND TUNNEL TESTS ON A ONE-SEVENTH Parallel developments in high acceleration and advanced cockpit SCALE MODEL OF THE H 126 JET FLAP AIRCRAFT technologies within the aeromedical and engineering communities Georgene H Laub Apr 1975 42 p refs Prepared in cooperation have illuminated the ability to realize significant improvements with Army Air Mobility R and D Lab Moffett Field, Calif in performance levels for future tactical fighters GRA (NASA-TM-X-62433 A-6074) Avail NTIS HC $3 75 CSCL 01A N75-24726# Air Force Systems Command Wright-Patterson Low speed wind tunnel tests were performed on a one-seventh AFB Ohio Foreign Technology Div scale model of the British H 126 jet flap research aircraft over TOTAL AIRFRAME FATIGUE TEST F 104 G Final Report a range of jet momentum coefficients The primary objective Schutz 20 Mar 1975 109 p Transl into ENGLISH from was to compare model aerodynamic characteristics with those Ind Facilities Operations Corp (West Germany) no TF-81/20 of the aircraft with the intent to provide preliminary data 15 Mar 1974 p 1-106 needed towards establishing small-to-full scale correlating (AD-A007938 FTD-HC-23-0842-75) Avail NTIS CSCL 01/3 techniques on jet flap V/STOL aircraft configurations Lift and The report contains the most important information and data drag coefficients from the model and aircraft tests were found on the experimental configuration experimental sequence and to be in reasonable agreement The pitching moment coefficient the results of the F 104 G total airframe fatigue experiment and trim condition correlation was poor A secondary objective Details are contained in 31 additional partial reports In addition was to evaluate a modified thrust nozzle having thrust reversal the tables of Appendix B contain all the damage information capability The results showed there was a considerable loss of which occurred on the structure during the experiments This lift in the reverse thrust operational mode because of increased report can be used as a means of orientation for the information nozzle-wing flow interference A comparison between the model contained in the partial reports because of the cross references simulated H 126 wing jet efflux and the model uniform pressure in the text and the tables GRA distribution wing jet efflux indicated no more than 5% loss in weight flow rate Author N75-24727£ United Aircraft Corp. Stratford Conn Sikorsky N76-24723*# Techtran Corp Glen Burnie. Md Aircraft Div INCREASING THE WEAR RESISTANCE OF AIRCRAFT FLIGHT LOAD INVESTIGATION OF HELICOPTER EXTER- PARTS NAL LOADS Final Report K A Krylov Washington NASA Oct 1974 134 p refs Horace T Hone Feb 1975 75 p refs Transl into ENGLISH of the book "Povysheniye iznosostoykosti (Contract DAAJ02-74-C-0016 DA Proj 1F2-62203-AH-86) detaley samoletov Moscow, Transport Press 1974 144 p (AD-A008394 SER-50906. USAAMRDL-TR-74-104) Avail (Contract NASw-2485) NTIS CSCL 01/3 (NASA-TT-F-15759) Avail NTIS HC $5 75 CSCL01C Any cargo that is freely suspended from a helicopter fuselage, The reasons for the insufficient wear resistance of moving by any of several available methods, does not experience the parts of bolt and hinge joints in aircraft are examined The results same dynamic loads as the aircraft For various reasons the of investigations of the indicated aircraft parts are presented in load factors may be amplified and peak out of phase with those connection with the occurrence of wear in their operation which of the helicopter This has long been suspected as a major is impermissible in amount and character In addition recom- contribution to premature failures in slings, pendants, and mendations for increasing the wear resistance of parts are attachment points at the aircraft or cargo A theoretical analysis given Author of the load factor relationship during various flight maneuvers was conducted by Sikorsky Aircraft in 1971 by means of a hybrid computer simulation of the coupled motion of a CH-54 N75-24724# Boeing Vertol Co Philadelphia Pa helicopter and several types of external loads, conducted in real HEAVY LIFT HELICOPTER. CARGO HANDLING ATC time and nonreal time on a fixed-base and a moving-base PROGRAM VOLUME 2 FABRICATION OF TEST HARD- simulator Actual flight tests have now been performed on a WARE AND FIXTURES INTEGRATED TEST RIG Final CH-54 helicopter to investigate the validity of that part of the Report. Jun 1971 - Jun 1974 simulator program from which was derived the relationship Joseph Shefnn and Wendell F Hill Dec 1974 218 p between helicopter load factor and sling tension load factor (Contract DAAJ01-71-C-0840) GRA (AD-A007244 USAAMRDL-TR-74-97B-Vol-2) Avail NTIS CSCL 01/3 N7 5-24728 j Air Force Aero Propulsion Lab, Wright-Patterson This report formally documents the efforts and results of AFB, Ohio the cargo handling system segment of the Heavy Lift Helicopter FUEL TANK NON-NUCLEAR VULNERABILITY TEST (HLH) Advanced Technology Component (ATC) development PROGRAM Final Report. Jan 1973 - Feb 1974 program The purpose of the HLH/ATC was to minimize technical Allan J Ferrenberg and Joel Blickenstaff Feb 1975 141 p cost and schedule risks associated with future HLH system refs research development test and evaluation (ROTE) and production (Contract F33615-73-C-0473, AF Proj 3048) programs This was achieved by design fabrication and testing (AO-A008531, AFAPL-TR-74-83) Avail NTIS CSCL 01/3 of specific ATC hardware in three critical air vehicle subsystems The effort described was designed to obtain weapons effects rotor/drive system flight control system and cargo handling data on fuel tanks and their peripheral areas in support of an system This report covers only the cargo handling system ASD non-nuclear survivability program Specifically, the objectives GRA of this program were to obtain data to assist in determining (1) probabilities of fuel tank explosions, and (2) probabilities of N75-24725# Aerospace Medical Research Labs Wnght- fires in void areas adjacent to fuel tanks, caused by certain Patterson AFB Ohio non-nuclear combat threats An additional objective was to
373 N75-24729 evaluate the effectiveness of the level of nitrogen inertmg proposed SAFEZONE ESCAPE ALERT SYSTEM DEVELOPMENT for aircraft fuel tanks GRA PROGRAM PHASE 1 SYSTEM DEVELOPMENT E 0 Cartwright 3 Mar 1975 68 p refs N76-24729# Bolt Beranek, and Newman. Inc Cambridge Mass (Contract N62269-74-C-0523) GUIDE FOR THE DESIGN OF CONTROL STICKS IN (AD-A008561 NADC-Cs-75029-40 Rept-2-57110/4R-3191) VIBRATION ENVIRONMENTS Final Report Avail NTIS CSCL 01/3 William H Levison and Philip D Houck Feb 1975 154 p A program was conducted to establish the basic value of a refs system designed to provide the aircrewman of an escape system (Contract F33615-74-C-4041) equipped aircraft with a continuous indication of inflight escape (AD-A008533, BBN-6863 AMRL-TR-74-127) Avail NTIS capability The system, as conceived monitors aircraft dynamic CSCL 01/3 conditions such as altitude sink rate and attitude, and provides A set of manual control experiments was conducted to this data to an onboard computer Continuous computations determine the effects of control-stick parameters on tracking are made and the results displayed to the aircrewman Simulated performance in a vibration environment Preliminary experimental flight envelopes were flown in a G degree-of-freedom moving variables were stick design parameters, stick location, and presence base simulator This included spin attack and flameout approach or absence of vibration Stick parameters had little effect on simulation Two display concepts were evaluated a digital read rms tracking error under vibration conditions for the particular out of time remaining and an analog display with time remaining aircraft dynamics that were used in this study Considerable and rate of change displayed Pilot performance was measured effect on control activity was observed however which suggests and pilot opinion was registered GRA that stick design parameters will significantly influence overall performance in systems that respond at vibration frequencies N75-24734# Naval Surface Weapons Center, Dahlgren. Va Stick lokation had no significant effect on either tracking or AN ESTIMATE OF THE EFFECT OF MULTIPLE EJECTION biodynamic performance measures GRA RACK FLEXIBILITY ON SIX DEGREE OF FREEDOM STORE EJECTION CONDITIONS N75-24730# Boeing Commercial Airplane Co, Seattle, Wash Leroy Devan Mar 1975 50 p refs TEST AND PERFORMANCE CRITERIA FOR AIRPLANE (AD-A008329 NSWC/DL-TR-3252) Avail NTIS CSCL 01/3 ANTISKID SYSTEMS Final Report. Dec 1972 - Jun 1974 A theoretical structural dynamic model of a MER (Multiple H H Straub, N S Attn. and R F Yurczyk Oct 1974 21 p Ejection Rack) based upon BERNOULLI Pitch and yaw bending (Contract F33615-73-C-3017 AF Proj 1369) deflections and torsional rotation, is developed Six-degree-of- (AD-A008536, AFFDL-TR-74-118) Avail NTIS CSCL 01/2 freedom store ejection conditions are predicted Sample The basic components and operation of airplane antiskid computations were made for a M-117 bomb and constant aircraft systems are described Test and performance criteria are pull-up rates corresponding to up to a 3 9 g normal acceleration established on a system as well as component level to support The computations were for the second fourth, and sixth bombs the development of a new brake control system These criteria dropped in the normal release sequence from an A-7D right are established for the analog-hardware simulator the dynamome- wing center pylon station Ejection velocities computed do not ter and full airplane tests GRA deviate more than 15% from the rigid case Ejection pitching and rolling rates are affected more significantly by flexibility N75-24731# Kamatics Corp, Bloomfield, Conn However, the pull-up maneuver alone affects the ejection KAFLEX DRIVE SHAFT COUPLING FOR UH-1 HELICOPTER conditions to a greater extent than flexibility for most ejection DESIGN REFINEMENT Final Technical Report variables and g values greater than 2 GRA Charles J Wirth 1975 68 p refs (Contract DAAJ01-72-C-0900) (AD-A008365, KC-11174 USAAVSCOM-TR-74-76) Avail N75-24735*# Decision Sciences Corp Jenkmtown, Pa NTIS CSCL 01/3 ANALYSIS OF TECHNOLOGY REQUIREMENTS AND A KA flex coupling shaft, using flexing matal elements to POTENTIAL DEMAND FOR GENERAL AVIATION AVIONICS accommodate misalignment has been designed as a replacement SYSTEMS IN THE 1980'S Final Report J for the main drive shaft coupling of the UH-1 helicopter Previous David M Cohn John H Kayser George M Senko, and Donald program phases explored the feasibility of this approach through R Glenn Jun 1974 223 p refs analysis and test of a prototype coupling shaft The program (Contract NAS2-7888) phases covered in this report include an examination of (NASA-CR-137629) Avail NTIS HC $7 25 CSCL01C compatibility of the coupling shaft to the space envelope and The trend for the increasing need for aircraft-m-general as a operating conditions encountered in the UH-1 installation, and major source of transportation in the United States is presented refinement of the prototype design to reflect the results of this (military and commercial aircraft are excluded) Social, political, and previous examinations A mock up installation of the and economic factors that affect the aircraft industry are prototype coupling shaft is made clearances are evaluated and considered and cost estimates are given Aircraft equipment and lateral natural frequencies are measured and verified through navigation systems are discussed J R T analysis GRA
N76-24732# Pisa Univ (Italy) Inst of Aeronautics N7S-24736* National Aeronautics and Space Administration THEORETICAL AND EXPERIMENTAL RESEARCH ON THE Ames Research Center, Moffett Field Calif FATIGUE CRACK PROPAGATION IN STIFFENED PANELS. REVERSED COWL FLAP INLET THRUST AUGMENTOR AN EVALUATION OF THE PARIS THEORY Final Technical Patent Report Dan Yu Cheng, inventor (to NASA) (Santa Clara Univ) Issued A Salvetti A Frediani E Grassi and F Rossi Sep 1974 13 May 1975 7 p Filed 19 Sep 1973 Supersedes N73-32624 83 p refs (11 - 23. p 2831) Sponsored by NASA (Contract DAJA37-73-C-2881) (NASA-Case-ARC-10754-1 US-Patent-3.883,095, (AD-A008079) Avail NTIS CSCL 01/3 US-Patent-Appl-SN-398886 US-Patent-Class-244-53B, Research on the applicability of the Paris theory to aircraft US-Patent-Class-137-15 1) Avail US Patent Office CSCL riveted stiffened structures is reported This research was carried 21E out in two stages evaluation of the stress intensity factor K in An adjustable airfoil is described for varying the geometry stiffened panels and measurement of crack growth rate in stiffened of a jet inlet and an ejector inlet in a jet engine for providing and unstiffened panels GRA thrust augmentation and noise reduction The airfoil comprises essentially a plurality of segments which are extended radially outward and retracted relative to the longitudinal axis of the N75-24733# LTV Aerospace Corp Dallas, Tex Vought Systems engine as a function of a change m the pressure differential Div between the upstream and downstream surfaces of the airfoil
374 N75-24743
A servo mechanism responsive to the change in the pressure overall pressure ratio from 25 to 50 saved little fuel and slightly differential is coupled to the airfoil to extend and retract the increased takeoff gross weight Author airfoil segments to maintain the pressure at a maximum on the downstream side of the airfoil relative to the pressure on the upstream side of the airfoil At low speeds such as at take-offs N75-2474O*# National Aeronautics and Space Administration and landings the airfoil is fully extended while at high speeds it Lewis Research Center Cleveland Ohio is fully retracted Official Gazette of the U S Patent Office FLOW CHARACTERISTICS OF VARIOUS SWIRL-CAN MODULE DESIGNS N76-24737*# Boeing Commercial Airplane Co Seattle Wash Edward J Mularz Washington Jun 1975 39 p refs Prepared THE 727 AIRPLANE TARGET THRUST REVERSER STATIC in cooperation Army Air Mobility Research and Development PERFORMANCE MODEL TEST FOR REFANNEO JT8D Lab, Cleveland Ohio ENGINES (NASA-TM-X-3236 E-8190) Avail NTIS HC $3 75 CSCL C T P Chow and E N Atkey Jul 1974 195 p refs 21E (Contract NAS3-17842) Flow measurements were performed on each of six swirl-can (NASA-CR-134652 Dg-41964) Avail NTIS HC $7 00 CSCL combustor module designs under simulated combustor operating 21E conditions to find the design which exhibited a small recirculation The results of a scale model static performance test of targt* zone intense air mixing and good fuel distribution in its wake thrust reverser configurations for the Pratt and Whitney Aircrali Conditions that are favorable for producing low oxides of nitrogen JT8D-100 series engine are presented The objective of the test emissions and high combustion efficiency were investigated The was to select a series of suitable candidate reverser configura- recirculation zone the turbulence intensity and the fuel distribu- tions for the subsequent airplane model wind tunnel ingestion tion pattern are obtained in the wake region of the center module and flight controls tests Test results indicate that adequate reverse of a three module array The most promising swirl-can module thrust performance with compatible engine airflow match is design incorporates two air swirlers which discharge air in opposite achievable for the selected configurations Tapering of the lips directions (contraswirl) mixes the fuel and air upstream of the results in loss of performance and only minimal flow directivity inner swirler and has a flow area blockage of 64 3% for the Door pressure surveys were conducted on a selected number of three module array Author lip and fence configurations to obtain data to support the design of the thrust reverser system Author N75-24741 *# National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio N75-24738*# AiResearch Mfg Co Torrance. Calif TURBINE DESIGN AND APPLICATION. VOLUME 3 HYPERSONIC RESEARCH ENGINE PROJECT PHASE 2 Arthur J Classman ed Washington 1975 141 p refs SOME COMBUSTOR TEST RESULTS OF NASA AEROTHER- (NASA-SP-290-Vol-3, LC-79-185105) Avail NTIS MFS225 MODYNAMIC INTEGRATION MODEL SOD HCS2 10 CSCL 21 E Yung H Sun Albert E Gaede, and Walter C Samio May 1975 Turbine technology concepts for thermodynamic and fluid 26 p refs Presented at the 11th JANNAF Combustion Conf. dynamics are presented along with velocity diagrams losses, Pasadena, Calif. 12 Sep 1974 mechanical design operation and performance Designs discussed (Contract NAS1-6666) include supersonic turbines radial-inflow turbines and turbine (NASA-CR-132525 AiResearch-74-10818) Avail NTIS cooling F 0 S HC $375 CSCL 21 E Combustor test results of the NASA Aerothermodynamic Integration Model are presented of a ramjet engine developed for operation between Mach 3 and 8 Ground-based and flight N75-24742*# AiResearch Mfg Co Torrance. Calif experiments which provide the data required to advance the technology of hypersonic air-breathing propulsion systems as well HYPERSONIC RESEARCH ENGINE PROJECT, PHASE 2 as to evaluate facility and testing techniques are described The PRELIMINARY REPORT ON THE PERFORMANCE OF THE HRE/AIM AT MACH 6 engine was tested with synthetic air at Mach 5 6 and 7 The Yung H Sun and Walter C Samio May 1975 26 p refs hydrogen fuel was heated to 1500 R prior to injection to simulate (Contract NAS1-6666) a regeneratively cooled system Combustor efficiencies up to 95 percent at Mach 6 were achieved Combustor process in (NASA-CR-132538 AiResearch-74-10951) Avail NTIS HC $375 CSCL 21E terms of effectiveness pressure integral factor total pressure Test results of the Aerothermodynamic Integration Model recovery and Crocco s pressure-area relationship are presented are presented A program was initiated to develop a hydrogen- and discussed Interactions between inlet-combustor combustor stages combustor-nozzle and the effects of altitude combustor fueled research-oriented scramjet for operation between Mach 3 step, and struts are observed and analyzed Author and 8 The primary objectives were to investigate the internal aerothermodynamic characteristics of the engine to provide realistic design parameters for future hypersonic engine develop- N75-24739*# National Aeronautics and Space Administration ment as well as to evaluate the ground test facility and testing Lewis Research Center Cleveland Ohio techniques The engine was tested at the NASA hypersonic tunnel PRELIMINARY STUDY OF ADVANCED TURBOPROPS FOR facility with synthetic air at Mach 5 6 and 7 The hydrogen LOW ENERGY CONSUMPTION fuel was heated up to 1500 R prior to injection to simulate a G Kraft and W Strack May 1975 48 p refs regeneratively cooled system The engine and component (NASA-TM-X-71740 E-8371) Avail NTIS HCS375 CSCL performance at Mach 6 is reported Inlet performance compared 21E very well both with theory and with subscale model tests The fuel savings potential of advanced turboprops (operational Combustor efficiencies up to 95 percent were attained at an about 1985) was calculated and compared with that of an equivalence ratio of unity Nozzle performance was lower than advanced turbofan for use in an advanced subsonic transport expected The overall engine performance was computed using At the design point altitude 10 67 km and Mach 0 80 turbine-inlet two different methods The perfornjance was also compared with temperature was fixed at 1590 K while overall pressure ratio test data from other sources Author was varied from 25 to 50 The regenerative turboprop had a pressure ratio of only 10 and an 85 percent effective rotary N75-24743*# AiResearch Mfg Co Los Angeles Calif heat exchanger Variable camber propellers were used with an HYPERSONIC RESEARCH ENGINE PROJECT PHASE 2A efficiency of 85 percent The study indicated a fuel savings of INSTRUMENTATION PROGRAM Interim Technical Report. 33 percent a takeoff gross weight reduction of 15 percent and 24 Aug - 23 Nov 1967 a direct operating cost reduction of 18 percent was possible P M Parmar. ed May 1975 75 p refs when turboprops were used instead of the reference turbofan at (Contract NAS1-6666) a range of 10 200 km These reductions were 28 11 and (NASA-CR-132593. AP-67-3020 ITR-3) Avail NTIS CSCL 14 percent respectively at a range of 5500 km Increasing 21E
375 N75-24744
Instrumentation developments are reported for thrust ALUMINUM COMPOSITES FOR TURBOJET ENGINE FAN measurement gas sampling, temperature measurement pressure BLADES measurement and systems engineering Autho* "'—r P Melnyk and I J Toth May 1975 93 p (Contract NAS3-17763) N75-24744*# National Aeronautics and Space Administration (NASA-CR-134770. ER-7806) Avail NTIS HC $4 75 CSCL Langley Research Center Langley Station Va 21E VIBRATION RESPONSES OF TEST STRUCTURE NO 1 Composite fabrication was performed by vacuum press DURING THE EDWARDS AIR FORCE BASE PHASE OF diffusion bonding by both the foil-filament array and preconsoli- THE NATIONAL SONIC BOOM PROGRAM dated monotape methods The effect of matrix material fiber Donald S Fmdley, Vera Huckel and Herbert R Henderson Jun diameter, matrix enhancement fiber volume reinforcement test 1975 28 p te< temperature angle-plying, notch, impact orientation processing (NASA-TM-X-72706) Avail NTIS HC S3 75 CSCL 13B variables and fabrication methods on tensile strength and Charpy In order to evaluate reaction of people to sonic booms of impact resistance are evaluated Root attachment concepts were varying overpressures and time durations a series of closely evaluated by room and elevated temperature tensile testing, as controlled and systematic flight test studies were conducted in well as by pendulum-lzod and ballistic impact testing Composite the vicinity of Edwards AFB California, from June 3 to June 23 resistance to foreign object damage was also evaluated by ballistic 1966 The dynamic responses of several building structures were impacting of panels using projectiles of gelatin. RTV rubber and measured as a part of these studies and the measurements steel at various velocities, and impingement angles A significant made in a one-story residence structure (Edwards test structure improvement in the pendulum impact resistance of B-AI No 1) are presented Sample acceleration and strain recordings composites was achieved Author are presented from F-104 B-58. and XB-70 sonic-boom exposures along with tabulations of the maximum acceleration and strain values measured for each one of about 140 flight N75-24754# Honeywell Inc Minneapolis Minn Government tests These data are compared with similar measurements for and Aeronautical Products Div engine noise exposures of the building during simulated landing DIGITAL FLIGHT CONTROL SYSTEMS FOR TACTICAL approaches and takeoffs of KC-135 aircraft Author FIGHTERS VOLUME 3 DIGITAL FLIGHT CONTROL SYSTEM DESIGN CONSIDERATION Interim Report. Feb 1972 - Jun 1973 N75-24746*# National Aeronautics and Space Administration M A Bender. R J Gaabo, and F L Smith Jun 1974 436 p Lewis Research Center Cleveland Ohio (Contract F33615-72-C-1058 AF Proj 1987) EFFECT ON FAN FLOW CHARACTERISTICS OF LENGTH (AD-A002687 GAPD-F-0131-IR3, AFFDL-TR-73-119-Vol-3) AND AXIAL LOCATION OF A CASCADE THRUST REVERS Avail NTIS CSCL 01/4 ER The Digital Flight Control Systems for Tactical Fighters Donald A Dietrich Washington Jun 1975 37 p refs Program is a development program the objective of which is to (NASA-TM-X-3247. E-8223) Avail NTIS HC $3 75 CSCL define the technology necessary to apply digital flight control 21E techniques to the three-axis multiple flight control configuration A series of static tests were conducted on a model fan demands of advanced fighter aircraft Analysis efforts have defined with a diameter of 140 err) to determine the fan operating powerful analytical DF CS models and computer program tools characteristics the inlet static pressure contours the fan-exit which permit determination of flight control system performance total and static pressure contours and the fan-exit pressure as a function of computational parameters — word length, sample distortion parameters associated with the installation of a rate and computational delays An exercise of the programs partial-circumferential-emission cascade thrust reverser The tests using the F-4 as a model indicated 100 iterations per second variables included the cascade axial length the axial location of as satisfactory for the longitudinal axis the reverser and the type of fan inlet It was shown that significant GRA total and static pressure distortions were produced m the fan aft duct and that some configurations induced a static pressure distortion at the fan face The amount of flow passed by the N75-24755# Cranfield Inst of Technology (England) fan and the level of the flow distortions were dependent upon ON THE ADEQUATE MODEL FOR AIRCRAFT PARAMETER all the variables tested Author ESTIMATION V Klein Mar 1975 33 p refs (Cranfield-Aero-28) Avail NTIS HC $3 75 N75-24746*# National Aeronautics and Space Administration The problem of the selection of measured data from an Lewis Research Center Cleveland Ohio aircraft of an adequate model which approximates the correct EXHAUST POLLUTANT EMISSIONS FROM SWIRL-CAN model and which facilitates the successful determination of COMBUSTOR MODULE ARRAYS AT PARAMETRIC TEST unknown parameters is presented Two ways for the proper CONDITIONS model structure verification are recommended, namely sensitivity Edward J Mularz Jerrold D Wear and Peter W Verbulecz analysis and/or testing of a hypothesis as to the significance of Washington Jun 1975 33 P refs Prepared in cooperation unknown parameters m the model proposed and the analysis with Army Air Mobility R and D Lab Cleveland Ohio of residuals Some approaches towards the assessment of (NASA-TM-X-3237 E-8196) Avail NTIS HC $3 75 CSCL parameter and adequate model accuracies are proposed and an 21E example is shown Author Improved designs of swirl-can combustor modules were tested using seven-module arrays in a combustor The combustor was N75-24756*# Stanford Univ , Calif operated over a pressure range of 69 to 207 N/sq cm a fuel-air EFFECTS OF ASYMMETRY ON THE DYNAMIC STABILITY ratio range of 0015 to 0046 at a constant inlet air tempera- OF AIRCRAFT Final Technical Report ture of 733 K and at reference velocities of 23 9 and 30 6 m/sec R E Fantmo E K Parsons. J D Powell, and R S Shevell The three designs tested pe/formed with high combustion Jun 1975 259 p refs efficiency at all conditions tested and exhibited oxides of nitrogen (Gram NGR-05-020-663) emissions substantially lower than that of conventional gas turbine (NASA-CR-142857) Avail NTIS HC $8 50 CSCL 01C combustors A correlating parameter used to extrapolate oxides The oblique wing concept for transonic aircraft was proposed of nitrogen emissions to full power or takeoff conditions for to reduce drag The dynamic stability of the aircraft was large commercial turbofan engines predicts oxides of nitrogen investigated by analytically determining the stability derivatives emissions somewhat higher than those specified in the 1979 at angles of skew ranging from 0 and 45 deg and using these government emissions standards Author stability derivatives in a linear analysis of the coupled aircraft behavior The stability derivatives were obtained using a lifting N75-24747*jjf TRW Equipment Labs Cleveland Ohio line aerodynamic theory and found to give reasonable agreement DEVELOPMENT OF IMPACT RESISTANT BORON/ with derivatives developed in a previous study for the same
376 N75-24926
aircraft In the dynamic analysis no instability or large changes Carroll Bartel Charles Coughlm John Moran and Larry Watkms occurred in the root locations for skew angles varying from 0 to Oct 1974 229 p refs 45 deg with the exception of roll convergence The damping in (Contract DOT-OS-20088) roll however decreased by an order of magnitude Rolling was (PB-239388/2 WRC-74-14-2 DOT-TST-75-4) Avail NTIS a prominent feature of all the oscillatory mode shapes at high HC $7 50 HC also available from NTIS $14 00/set of 2 reports skew angles Author as PB-239386 CSCL 01E A fundamental requirement of this effort was that the noise N75-24757# Honeywell Inc, Minneapolis, Minn Systems impact of air traffic around major airports on the surrounding and Research Center community should be described and that predictions of various DIGITAL FLIGHT CONTROL SYSTEM FOR TACTICAL noise abatement alternatives should be made For this the FIGHTERS Final Report, Feb 1972 - Dec 1973 DOT/Wyle noise exposure forecast computer program was A Pent Konar Robert J Gaabo Marv A Bender. Fred L Smith developed Volume 2 of the report is a description of this program and James D Wolf Jul 1974 424 p Included are brief descriptions of the calculations performed the (Contract F33615-72-C-1058 AF Pro) 1987) subroutines that perform them and a user s guide Also included (AD-A002686 F0121-IR1 AFFDL-TR-74-69) Avail NTIS CSCL is a complete listing of the program, in FORTRAN V Inputs to 01/3 the program are a description of the airport geometry including The Digital Flight Control Systems for Tactical Fighters flight paths, aircraft noise and performance characteristics and Program is a development program the objective of which is to the aircraft fleet mix GRA define the technology necessary to apply digital flight control techniques to the three-axis multiple flight control configuration N75-24897*# Tyco Labs Inc Waltham. Mass demands of advanced fighter aircraft Analysis efforts have defined DIRECTIONALLY SOLIDIFIED LAMELLAR EUTECTIC powerful analytical OF CS models and computer program tools SUPERALLOYS BY EDGE-DEFINED, FILM-FED GROWTH which permit determination of flight control system performance Final Report as a function of computational parameters -- word length sample G F Hurlev Apr 1975 53 p refs rate and computational delays An exercise of the programs (Contract NAS3-18909) using the F-4 as a model indicated 100 iterations per second (NASA-CR-134808) Avail NTIS HC$425 CSCL11F as satisfactory for the longitudinal axis A program was performed to scale up the edge-defined, GRA film-fed growth (EFG) method for the gamma/gamma prime-beta eutectic alloy of the nominal composition Ni-197 Cb - 6 N75-24760*# National Aeronautics and Space Administration Cr-2 5 Al Procedures and problem areas are described Flat bars Ames Research Center. Moffert Field. Calif approximately 12 x 1 7 x 200 mm were grown mostly at speeds SHUTTLE SPACE LAB SIMULATION USING A LEAR JET of 38 mm/lir and tensile tests on these bars at 25 and 1000 AIRCRAFT MISSION NO 3 (ASSESS PROGRAM) C showed lower strength than expected The feasibility of growing John 0 Reller. Jr. Carr B Neel, and Robert H Mason Nov hollow airfoils was also demonstrated by growing bars over 1974 145 p refs 200 mm long with a teardrop shaped cross-section, having a (NASA-TM-X-62410 A-5907) Avail NTIS HC $5 75 CSCL major dimension of 12 mm and a maximum width of 5 mm 148 Author The third ASSESS mission using a Lear Jet aircraft conducted to continue the study of scientific experiment operations m a N75 24923# McDonnell Aircraft Co St Louis. Mo simulated Spacelab environment Prior to the mission research EVALUATION OF THE RELIABILITY AND SENSITIVITY OF planning and equipment preparation were observed and document- NDT METHODS FOR TITANIUM ALLOYS, VOLUME 2 Final ed A flight readiness review for the experiment was conducted Report, 1 May 1972 - 31 Jan 1974 Nine of the ten scheduled flights were completed during simulation Robert J Lord Jun 1974 373 p refs mission and all major science objectives were accomplished The (Contract F33615-72-C-1203 AF Proj 7351) equipment was well qualified for flight and gave little trouble, (AD-A001604. AFML-TR-73-107-Vol-2) Avail NTIS CSCL telescope malfunctions occurred early in the mission and were 11/6 corrected Both real-time and post-observation data evaluation The report describes the work conducted on a program were used to assess research progress and to plan subsequent designed to improve nondestructive testing techniques and then flight observations for maximum effectiveness Author to evaluate the capability and reproducibility of the improved nondestructive testing techniques for the evaluation of discontinui- N75-24771# Wyle Labs. Inc El Segundo Calif ties occurring in titanium Reported are penetrant dwell times AIRPORT NOISE REDUCTION FORECAST VOLUME 1 penetrant bleed-out times developer types, emulsification times, SUMMARY REPORT FOR 23 AIRPORTS Final Report. Jul and water washing parameters required to effectively penetrant 1972 - Oct 1974 inspect parts which may contain a variety of crack sizes and porosity Both post-emulsifiable and water washable fluorescent Carroll Bartel. Louis C Sutherland, and Leroy Simpson Oct 1974 253 p refs Prepared in cooperation with Speas (R Dixon) penetrants were investigated The effect of kilovoltage on Assoc . Manhasset. N Y radiographic contrast sensitivity is discussed Ultrasonic inspection (Contract DOT-OS-20088) of contour surfaces is reported and methods for improving (PB-239387/4 WRC-74-14-1) Avail NTIS HC $8 00 HC near-surface resolution are documented Methods for ultrasonic also available from NTIS $14 00/set of 2 reports as PB-239386- inspection of thin machined parts are reported GRA SET CSCL 01E A detailed analysis of cost effectiveness of two aircraft noise reduction alternatives was carried out and the results are N75-24926# Pratt and Whitney Aircraft. West Palm Beach, summarized The alternatives consisted of two different Fla modifications of civil air carrier aircraft having JT3D or JT8D PROCESS EVALUATION OF DIRECTIONALLY SOLIDIFIED engines Both alternatives assumed standard use of a two-segment NI3CB REINFORCED EUTECTICS IN TURBINE BLADE approach procedure incorporating a glide slope for landing The FORM Final Report. 16 Mar 1974 - 15 Mar 1976 analysis specified includes a detailed evaluation of noise impact P M Curran. L F Schulmeister J S Enckson. and A F Giamei at 23 airports for the years 1972. 1978 1981. and 1987 along 15 Mar 1975 106 p refs with a detailed cost analysis of implementing the alternatives (Contract N00019-74-C-0194) GRA (AD-A008435. PWA-5231) Avail NTIS CSCL 21/5 The purpose of the program was to investigate the unidirec- N75-24772# Wyle Labs Inc El Segundo Calif tional solidification of delta (Ni3Cb) reinforced eutectic alloys in AIRPORT NOISE REDUCTION FORECAST VOLUME 2 turbine blade form The liquid metal cooling (LMC) process, served NEF COMPUTER PROGRAM DESCRIPTION AND USER'S as the basic processing technique for this investigation The major MANUAL Final Report. Jul 1972 - Oct 1974 objectives of the program were to (1) evaluate solidification
377 N75-25057
process modifications to increase the temperature gradient capability of the liquid metal cooling process (2) investigate the effect of solidification conditions on the microstructure and mechanical behavior of delta (NiSCb) reinforced eutectic alloys solidified in turbine blade form and (3) evaluate the solidification characteristics associated with the fabrication of (air-cooled) eutectic turbine blade airfoils GRA
N75-25057*# West Virginia Univ Morgantown Dept of Electrical Engineering ANALYSIS AND DESIGN OF AIRCRAFT ANTENNAS Final Report. 1 Mar 1971 - 30 Jun 1975 Constantino A Balanis 30 Jun 1975 24 p (Contract NGR-49-001-049) (NASA-CR-142945) Avail NTIS HC $3 25 CSCL 09C Recording systems and other associated electronic equipment were engineered calibrated and used to measure antenna radiation patterns of aircraft structures Antenna design measured and computed results and performance are discussed Data show measured and computer data to be in agreement E H W
N75-25094*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio EXTERNAL FINS AND EJECTOR ACTION FOR REDUCING THE INFRARED EMISSION OF ENGINE EXHAUST DUCT- ING G James VanFossen Jr Washington Jun 1975 14 p refs (NASA-TM-X-3242 E-8238) Avail NTIS HC $325 CSCL 20M An analytical investigation was conducted to determine the feasibility of using external fins and ejector action on the exhaust ducting of a helicopter to reduce the infrared emission of the aircraft Temperatures were calculated for both circular disk fins and pin fins Results show that combining ejector action with fins can lower the metal temperature to acceptable levels at least for high flight speeds Author
N75-2S221 *# National Aeronautics and Space Administration Langley Research Center Langley Station Va CRACK GROWTH UNDER SPECTRUM LOADING A CRACK CLOSURE MODEL Wolf Elber [1975] 23 p refs Presented at the Symp of Fatigue Crack Growth Under Spectrum Loading 78th Ann ASTM Meeting (NASA-TM-X-72708) Avail NTIS HC $3 25 CSCL 20K A concept based on the crack-closure phenomenon was developed to replace random load spectra with constant amplitude loading in both analysis and tests The maximum load and the crack opening load in the constant amplitude loading are chosen to be equal to those for the spectrum so that both crack growth mode and the crack length at failure are equivalent to those under random load spectra The number of cycles of constant- amplitude loading is chosen so that the amount of crack growth is equal to that due to a given sequence or block of the random spectrum loading The concept was tested experimentally after predicting the equivalent number of constant-amplitude cycles for six different random load sequences The agreement between predictions and test results was good Author
N75-25298*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio CHALLENGE TO AVIATION HATCHING A LEANER PTEROSAUER Frank E Moss 1975 9 p Presented at Aeron Propulsion Com* Cleveland. 13 May 1975 (NASA-TM-X-71744) Avail NTIS HC $3 25 CSCL 10B Modifications in commercial aircraft design particularly the development of lighter aircraft are discussed as effective means of reducing aviation fuel consumption The modifications outlined include (1) use of the supercritical wing, (2) generation of the wmglet, (3) production and flight testing of composite materials, and, (4) implementation of fly-by-wire control systems Attention is also given to engineering laminar air flow control, improving cargo payloads and adapting hydrogen fuels for aircraft use LB
378 SUBJECT INDEX
AERONAUTICAL ENGINEERING / A Special Bibliography fSuppI 61) SEPTEMBER 1975
Typical Subject Index Listing
SUBJECT Aerodynamics of lifting and propulsive systems in HEADiDINI G EXTENSION j a periodically functioning regime - Optimization CYCLIC LOADS of their perforBance -Low cycle high temperature fatigue in aircraft A75-35815 jet engines: conference proceeding>rnr~aoe1-i nrtsc ' Two-dimensional transonic calculations with [AGABD-CP-155] N75-10H87 boundary layers A75-35819 An experimental investigation of the aerodynamic characteristics of several nose mounted canard REPORT configurations at supersonic Hach numbers NUMBER [AD-A007793] 1175-23526 Light aircraft lift, drag, and moment prediction: A review and analysis [NASA-CB-2523] H75-24677 The title is used to provide a description of the subject matter When the title is Low-speed aerodynamic characteristics of a insufficiently descriptive of the document content a title extension is added 13-percent thick airfoil section designed for separated from the title by three hyphens The NASA or Al AA accession number general aviation applications [NASA-TB-X-72697] B75-21678 is included m each entry to assist the user in locating the abstract in the abstract AEBODFHAHIC COEFFICIENTS section of this supplement if applicable a report number is also included as an Integrated potential formulation of unsteady aid m identifying the document supersonic aerodynamics for interacting wings [AIAA PAPEB 75-762] A75-32693 Image system solution for store aerodynamics with interference. I i-7 AIBCBiFT A75-33436 Isolating nozzle afterbody interaction parameters The influence of wind shear on aerodynamic and size effects: A new approach flight and coefficients wind tunnel tests with A 7 aircraft A75-3S«11 N75-23503 Hydroaerodynamic characteristics of a low aspect An investigation of the flow field of the A-7D ratio delta wing near a screen aircraft with several external store loadings at [AD-A0076U9] N75-23529 Mach numbers 0.70 and 0.95 AEBODYBAflIC COHFIGOBATIONS [AD-A008H76J M75-2K688 A calculation method for unsteady subsonic flow ACCELERATED LIFE TESTS about harmonically oscillating wing-body Systematic development testing for engine configurations structural integrity assurance [AIAA PAPEB 75-8611] A75-33951 A75-3U1U7 Influences of manufacturing tolerances and surface ACCESSOBIES roughness of blades on the performance of turbines Automatic Test system for Jet Engine Accessories [ASME PAPEB 75-GT-35] A75-34592 A75-32396 Subsonic and supersonic indicial aerodynamics and. ACOUSTIC NOZZLES aerodynamic transfer function for complex Mind tunnel measurements of forward speed effects configurations aerodynamic configurations on jet noise from suppressor nozzles and for subsonic and supersonic speeds using the comparison with flight test data finite element method [AIAA PAPEB 75-870] A75-33957 [NASA-CB-112818] N75-23478 ACOUSTIC PBOPAGATIOH Analysis of transonic flow about lifting wing-body General analysis of the diffraction pattern for a configurations plane acoustic wave at a wedge moving at [NASA-TB-fi-140] N75-2U681 supersonic speed AEBODYSAHIC DBAG A75-3H272 Drag effects on wing flutter ADAPTIVE COHTBOL [AIAA PAPEB 75-775] A75-32662 Identification of systems by means of adaptive model A theoretical analysis for three dimensional ram application to jet engines wings in parallel walls A75-32473 A75-33427 ADDITIVES The drag and oscillating transverse force on Application of thin-layer chromatography for vibrating cylinders due to steady fluid flow determining the wearing capacity of additives A75-35765 contained in petroleum-based aviation oils Interaction of jets of GE CF6-50 reactors with the A75-35300 wing cellules of the airbus during cruise - AEBODTHAHIC CHARACTERISTICS Hind-tunnel simulation Aerodynamic characteristics of an axisymmetric A75-35808 body undergoing a uniform pitching motion The measurement of the transonic spillage drag of [AIAA PAPEB 75-838] A75-33933 a supersonic intake A fast semidirect method for computing transonic N75-23188 aerodynamic flows An experimental investigation of the component A75-31194 drag composition of a two-dimensional inlet at Experimental results of full scale air-cooled transonic and supersonic speeds turbine tests N75-23U89 [ASHE PAPEB 75-GT-116] A75-3U653 Low speed injection effects on the aerodynamic Hatching of aircraft and engine characteristics performance at transonic speed Russian book N75-23U94 A75-35521 An experimental study of jet exhaust simulation Some problems posed by the aerodynamics of the N75-23501 dirigible balloon A75-35810
A-1 AEBODYNASIC FOBCES SDBJECT IHDEX
Exhaust plume temperature effects on nozzle Airframe: Engine interaction for engine afterbody performance over the transonic Bach configurations mounted above the wing. Part 1: number range Interference between wing and intake jet N75-23501 N75-23511 The influence of nacelle afterbody shape on 1EBODYBABIC LOADS airplane drag Aeroelastic panel optimization with aerodynamic N75-23505 damping Reynolds number effects on boattail drag of 475-33188 exhaust nozzles from wind tunnel and flight tests Reproduction of the interaction of aerodynamic N75-23506 loads and structural distortions during strength ABBODYHABIC FOBCES tests Subsonic transient lifting surface aerodynamics [AD-A007661] N75-23520 [AIAA PAPER 75-758] A75-32689 Method of the optimization of the load-carrying Active flutter suppression using trailing-edge and structure of wing on rigidity during variation tab control surfaces by the distribution of thickness ratio CAIAA PAPER 75-822] A75-32697 [AD-A007317] N75-23521 Side forces on unyawed slender inclined Calculation of loads and deformations of sweptback aerodynamic bodies wing with the aid of mechanical analog instruments A75-33135 [AD-A007308] N75-23525 Theoretical study of lift-generated vortex wakes Prediction of unsteady aerodynamic loadings caused designed to avoid rollup by leading edge and trailing edge control A75-33185 surface motions in subsonic compressible flow: Transonic potential flow calculations using Computer program description conservation form for shock-free airfoils [NASA-CB-132631] N75-24672 A75-31193 AEHODYNABIC NOISE Wind tunnel test of a flutter suppressor on a Hind tunnel measurements of forward speed effects straight wing on jet noise from suppressor nozzles and [ONERA, TP NO. 1975-31] A75-35869 comparison with flight test data Accounting of aerodynamic forces on [AIAA PAPER 75-870] A75-33957 airframe/propulsion systems for designing Research on helicopter rotor noise military aircraft [AD-A007261] N75-23608 N75-23507 AEBODYHAHIC STABILITY An estimate of the effect of multiple ejection Parachute systems of the DFVLR for stabilization rack flexibility on six degree of freedom store and salvage of flight vehicles ejection conditions [DGLR PAPER 71-013] A75-31661 [AD-A008329] N75-21731 Calculations of three-dimensional flows in a ABBODYNABIC HEATIHG linearized supersonic regime Aerodynamic heating in gaps in the presence of A75-35813 protuberances and shock wave impingement Aerodynamics of rotors - Hake equilibration CAIAA PAPER 75-670] A75-32907 A75-35811 AERODYBABIC IHTEBFEBEHCE Effects of asymmetry on the dynamic stability of Aerodynamic heating in gaps in the presence of aircraft protuberances and shock wave impingement [NASA-CR-112857] N75-21756 [AIAA PAPEE 75-670] A75-32907 AEBODYHAHIC STALLING Free-molecular interference of cylinders with S-3A stall testing and auto-throttle oblique ray reflection hypersonic flow over development/testing parallel cylinders A75-33613 A75-33339 A model for the dynamics of a separation bubble Image system solution for store aerodynamics with used to analyze control-surface buzz and dynamic interference. I stall A75-33136 [AIAA PAPER 75-867] A75-33951 Image system solution for store aerodynamics with F100 fan stall flutter problem review and solution interference. II A75-34134 A75-33137 Ground vortex - Limit to engine/reverser operation Vortex development and breakdown for high bypass ratio engine [AIAA PAPER 75-881] A75-35172 [ASBE PAPER 75-GT-3] A75-31567 Problem of supersonic flow past a slender pointed Surge and rotating stall in axial flow body with tail compressors. I - Theoretical compression system A75-35706 model Alrframe/propulsion interference [ASBE PAPER 75-GT-9] A75-31573 [AGARD-CP-150] 1)75-23185 Study on the mechanism of stall margin improvement Interaction problems between air intakes and of casing treatment of low speed axial flow aircraft compressors 1)75-23486 [ASME PAPER 75-GT-13] A75-34576 A criterion for prediction of airframe integration Propagating stall in compressors with porous walls effects on inlet stability with application to [ASBE PAPER 75-GT-59] A75-31612 advanced fighter aircraft AEROELASTICITY N75-23187 Influence of structural damping, preconing offsets Jet interference of a podded engine installation and large deflection on the flap-lag-torsional at cruise conditions stability of a cantilevered rotor blade N75-23490 [AIAA PAPER 75-780] A75-32667 Subsonic base and boattail drag, an analytical Aeroelastic panel optimization with aerodynamic approach damping N75-23I492 A75-33i)88 Theory of mixing flow of a perfect fluid around an AEBOSPACE ENVIRONMENTS afterbody and a propulsive jet Air traffic controllers' operative effectiveness N75-23193 under NAS environments Isolating nozzle afterbody interaction parameters A75-31539 and size effects: A new approach flight and AEBOTHBHBODYHABICS wind tunnel tests with A 7 aircraft Hypersonic research engine project. Phase 2: N75-23503 Some combustor test results of NASA Airframe/propulsion system flow field interference aerothermodynamic integration model and the effect on air intake and exhaust nozzle [NASA-CS-132525] N75-21738 performance Hypersonic research engine project, phase 2. N75-23508 Preliminary report on the performance of the Detailed experimental and theoretical analysis of HRE/AIB at Bach 6 the aerodynamic interference between lifting [NASA-CR-132538] N75-21712 jets and the fuselage and wing N75-23509
A-2 SOBJECT IHDEX AIBCBAF1 CONFIGURATIONS
AFTEBBODIES pour-dimensional guidance algorithms for aircraft Theory of nixing flow of a perfect fluid around an in an air traffic control environment afterbody and a propulsive jet [BASA-TN-D-7829] N75-23549 N75- 231493 Engineering and development program plan; en route Reynolds number effects on fore- and aftbody control automatic flight data processing and pressure drag air traffic control B75-23497 [AD-A007623] H75-23550 The subsonic base drag of cylindrical twin-jet and AIB 7BANSPOBTATIOH single-jet afterbodies Air transportation of radioactive materials N75-23H98 A75-33568 An experimental study of jet exhaust simulation Cargo aircraft - A look toward the future N75-23501 A75-35290 Isolating nozzle afterbody interaction parameters Analysis of operational requirements for medium and size effects: A new approach flight and density air transportation. Volume 1: Summary wind tunnel tests with A 7 aircraft [NASA-CB-137603] N75-235314 N75-23503 AIRBOBHE EQUIPMENT Exhaust plume temperature effects on nozzle The B-1 CITS system Central Integrated Test afterbody performance over the transonic Nach Subsystem number range A75-35277 N75-23504 Preliminary results from pilot aviation weather The influence of nacelle afterbody shape on self-briefing experiments airplane drag A75-35428 N75-23505 AIBBOBHE/SPACBBOHHE COMPUTERS AFTEBBURHIHG The age of the RPV data bus or the data bus comes Afterburning regulation concepts of age airborne computer test systems N75-23587 A75-35261 AGBICDLTDBB The B-1 CITS system Central Integrated Test Observing cold-night temperatures of agricultural Subsystem landscapes with an airplane-mounted radiation A75-35277 thermometer An application of modern control theory to jet A75-33103 propulsion systems considering onboard AIB BREATHIHG ENGIHBS computer Review of hammershock pressures in aircraft inlets [NASA-TH-X-71726] N75-23573 A75-34115 AIBCBAFT ACCIDENT INVESTIGATED AIB CARGO Pan American World Airways, Incorporated, Boeing High-capacity transport planes as modern air 707-321C, N458PA, Boston, Massachusetts, freight systems November 1973 aircraft accident investigation [NASA-TT-F-16396 ] N75-23533 [PB-239448/4] N75-24701 AIB COOLING Sierra Pacific Airlines, Incorporated Convair Experimental results of full scale air-cooled 340/140, N4819C near Bishop, California, 13 turbine tests March 1974 aircraft accident investigation [ASME PAPER 75-GT-116] A75-34653 [PB-239511/9] N75-24702 AIR INTAKES AIBCBAFT ACCIDENTS Airframe/propulsion interference Rescue measures in the case of accidents of the [AGAEE-CP-150 ] N75-23485 AN-12 aircraft Interaction problems between air intakes and A75-32527 aircraft Parachute systems of the DFVLR for stabilization N75-23486 and salvage of flight vehicles A criterion for prediction of airframe integration [DGLB PAPER 74-043] A75-34661 effects on inlet stability with application to AIBCBAFI ANTENNAS advanced fighter aircraft Analysis and design of aircraft antennas N75-23487 [NASA-CR-142915] N75-25057 An experimental investigation of the component AIBCBAFT APPBOACB SPACING drag composition of a two-dimensional inlet at Airborne wake vortex detection by in-flight transonic and supersonic speeds radar sensing N75-23489 A75-35425 Airframe: Engine interaction for engine AIBCBAFT BBAKES configurations mounted above the wing. Part 1: Research about effects of external flow and Interference between wing and intake jet aircraft installation conditions on thrust N75-23511 reversers performances An air intake control system for a supersonic H75-23495 fighter aircraft AIBCBAFT CABBIEBS N75-23589 The S-3A carrier suitability demonstration Reversed cowl flap inlet thrust augnentor with A75-33614 adjustable airfoil Lift-fan characteristics selection for 1980-85 [HASA-CASE-ARC-10754-1] B75-24736 V/STOL carrier onboard delivery aircraft AIB POLLOTIOS [ASME PAPEB 75-GT-98] A75-34640 Preliminary study of low emission gas turbine AIBCBAFT COHPABTHEBTS combastor with airblast fuel atomizer Response of aircraft structural compartments to [ASME PAPER 75-GT-31] A75-31588 blast pressures and fragments from high Droplet diameter and size distribution of JP-4 explosive projectiles fuel injected into a subsonic airstream [AIAA PAPER 75-751] A75-32652 [AD-A007687] H75-24192 A study of helicopter interior noise reduction Exhaust pollutant emissions from svirl-can [NASA-TH-X-72655] N75-23556 combustor module arrays at parametric test AIBCBAFT CONFIGURATIONS conditions The annals of the polymorph - A short history of [NASA-TM-X-3237] N75-2U746 variable geometry. Ill variable wing aircraft AIR TRAFFIC A75-33450 Analysis of operational requirements for medium Computational procedure for three-dimensional density air transportation. 7olume 1: Summary boundary layers on aircraft and aerospace vehicles [NASA-CH-137603] H75-23534 A75-34190 AIB TRAFFIC COSTROI Prediction of the optimua location of a nacelle Air traffic controllers' operative effectiveness shaped body on the wing of a wing-body under HAS environments configuration by inviscid flow analysis A75-31539 B75-23510 An overview and assessment of plans and programs for the development of the upgraded third generation air traffic control system [AD-A008940] N75-23531
A-3 AIBCSAFT CONTROL SDBJECT INDEX
\ Airframe' Engine interaction for engine AIRCRAFT ENGINES configurations mounted above the King. Part 2: Diagnostics of ]et aero-engines by means of Engine jet simulation problems in wind tunnel spectral analysis of lubricating oil tests A75-32470 N75-23512 Regenerative turbofans - A comparison with AIRCRAFT CONTROL nonregenerative units aircraft engine On the way to tactical aircraft robotics performance ground based radar control of F-102 A A75-33U38 A75-32452 The dynamics of atmospheric dust particles in Interaction between control augmentation system aircraft auxiliary power radial inflow turbines and aarframe dynamics on the YF-17 [AIAA PAPER 75-8414] , A75-33938 [AIAA PAPER 75-824] A75-32694 Propulsion system structural integration and TF16 active-control-system/structural dynamics engine integrity; Proceedings of the Symposium, interaction instability U.S. Naval Postgraduate School, Monterey, [AIAA PAPEB 75-823] A75-32695 Calif., September 3-6, 1974 Stone Spin Shorthand, including: Spin Data Card A75-34112 and sample Criteria Spin Set for testing Structural integrity for propulsion systems out-of-control flight A75-34113 A75-33618 YF-16 air induction system design loads associated AIRCRAFT DESIGB with engine surge B-1 - The road to first flight A75-34114 A75-32155 Propulsion system and airframe structural Minimum weight design of the F-15 empennage for integration program flutter A75-34118 [AIAA PAPER 75-777] A75-32664 High-speed rotor dynamics - An assessment of New Air Force requirements for structural safety, current technology for small turboshaft engines durability and life management A75-34127 [AIAA PAPER 75-781] A75-32668 Dynamic response of viscous-damped multi-shaft jet The flutter analysis of T-tails engines [AIAA PAPER 75-759] A75-32690 A75-34128 Variable geometry today latest swing wing Low-cycle fatigue and creep analysis of gas aircraft turbine engine components A75-33447 A75-34139 The annals of the polymorph - A short history of Experimental investigation of a new concept of variable geometry. II ^variable swept wings fuel prevaporization for aircraft engine low A75-33449 emission combustors Why so few all new General Aviation aircraft [ASBE PAPER 75-GT-6] A75-34570 design decision making factors Rotor burst protection program - Statistics on A75-33619 aircraft gas turbine engine rotor failures that Propulsion system and airfratae structural occurred in U.S. commercial aviation during 1973 integration program [ASME PAPER 75-GT-12] A75-34575 A75-34118 The refracting inlet - A new concept for aircraft Transonic airfoil analysis and design using inlet noise suppression Cartesian coordinates [ASME PAPER 75-GT-21] A75-34580 A75-34195 Missile firing tests at stationary targets in lift-fan characteristics selection for 1980-85 support of blade containment design for V/STOI carrier onboard delivery aircraft aircraft engines [ASME PAPER 75-GT-98] A75-34640 [ASME PAPER 75-GT-47] A75-34604 System concept and key problems concerning Laboratory testing of controls for aircraft pilotless, remotely-controlled combat aircraft OKF turbine engines [DGLR PAPER 74-076A] A75-34725 [ASME PAPER 75-GT-101] A75-34643 Cargo aircraft - A look toward the future Development of real time high energy X-ray imaging A75-35290 system for use in dynamic fluoroscopy of aero The An-2 aircraft /"4th revised and enlarged edition/ gas turbines Russian book [ASME PAPER 75-GT-117] A75-34654 A75-35350 The economic advantages of low and high A study of self-similarity in boundary layer temperature anti corrosion coatings on jet turbulence and its relevance to aircraft design engine parts - A case history and operation A75-35449 A75-35419 Hatching of aircraft and engine characteristics Matching of aircraft and engine characteristics Russian book Russian book A75-35521 A75-35521 Airframe: Engine interaction for engine Effect of external conditions on the functioning configurations mounted above the wing. Part 1: of a dual flow supersonic nozzle designing Interference between wing and intake jet propulsion system of military aircraft N75-23511 N75-23491 Airframe: Engine interaction for engine Accounting of aerodynamic forces on configurations mounted above the wing. Part 2: airframe/propulsion systems for designing Engine jet simulation problems in wind tunnel military aircraft tests N75-23507 N75-23512 Computer-augmented design of aircraft wing The state of the art in oil gnality gaging on US structures military and commercial aircraft N75-23554 [AD-A007682] N75-23565 Design and analysis of a supersonic Power plant controls for aero-gas turbine engines penetration/maneuvering fighter [AGARD-CP-151] N75-23575 [NASA-CR-132633] N75-23558 An airframe manufacturer's requirements for future A formal structure for advanced automatic propulsion controls flight-control systems N75-23578 [NASA-TN-D-7940] N75-23606 Control system requirements dictated by Large-scale wind-tunnel tests of three vehicles optimization of engine operation incorporating a deployable rigid wing B75-23579 aircraft design of rectangular wings using Control design considerations for variable aircraft models and wind tunnel stability tests geometry engines [NASA-TH-X-62405 ] N75-24671 N75-23583 NASA/Army XV-15 tilt rotor research aircraft Aircraft engine nacelle fire test simulator familiarization document [AD-A007853] 875-23617 [ NASA-TH-X-62407] N75-24720 SUBJECT IBDEI AIBCBAFt SAFSTT
Hypersonic research engine project. Phase 24: Test and performance criteria for airplane Instrumentation program antiskid systems [HASA-CB-132593] H75-2a7B3 [AD-A008536] 875-24730 AIRCBAFT BQOIPBBIt AIBCBAFT SAIiTBBAHCB Pnel tank noD-naclear vulnerability test program Statistical estimation of service cracks and [AD-A008531] 875-24728 maintenance cost for aircraft structures Guide for the design of control sticks in [AIAA PAPEB 75-767] A75-32657 vibration environments aircraft nanaal Reliability and maintainability allocation for control equipment avionic maintenance optimization [AD-A008533] 875-24729 A75-35252 AIBCBAFT GOIDABCE Antotest user needs at a base shop Velocity vector - The logical solution computerized Automatic Test Equipment for aircraft guidance head-up displays military avionics A75-32410 A75-35253 Four-dimensional guidance algorithms for aircraft An automated tunenp calibration of jet engine fuel in an air traffic control environment controls [HASA-TH-D-7829] B75-235149 A75-35258 AIBCBAFT HAZABDS Automatic test equipment for S-3A support Besponse of a light aircraft to a thermal exhaust A75-35279 plnne AIBCBAFT HABEOTBBS A75-35403 Advanced maneuverability options for future fighters High altitude turbulence encountered by the [AD-A008497] B75-2U725 supersonic TF-12A airplane AIBCBAFT HODBLS A75-35409 Side forces on unyawed slender inclined Aircraft turbulence encounters during commercial aerodynamic bodies operations in the vicinity of thunderstorms A7S-33435 A75-35418 Hind tunnel tests for the determination of the A radar and direct visual study of the hazard to behavior of aircraft external loads which are aircraft from bird migrations in the southwest dropped [AD-A008198] H75-24699 A75-35098 AIBCBAFT HTDBADLIC STSTBHS A model technique for exhaust system performance Automated test facility for aircraft hydraulic testing pumps and motors 875-23502 A75-32397 Large-scale wind-tunnel tests of three vehicles AIBCBAFT IHDDSTBI incorporating a deployable rigid wing Analysis of technology requirements and potential aircraft design of rectangular wings using demand for general aviation avionics systems in aircraft models and wind tunnel stability tests the 1980's technology assessment and [BASA-ln-X-62405] B75-2U671 technological forecasting of the aircraft industry On the adequate model for aircraft parameter [BASA-CB-137629] 875-24735 estimation parameterization of aircraft AIBCBAFT IBSTBDHEHTS models using mathematical models Velocity vector - The logical solution [CBAHFIELD-AEBO-28] 875-24755 aircraft guidance head-up displays AIBCBAFT BOISE A75-32410 CF5D aircraft cockpit-noise reduction Advanced gallium phosphide L.E.D. displays [DCIEB-74-H-1048] 875-23564 A75-35284 The development of experimental techniques for the Airborne Hake vortex detection by in-flight study of helicopter rotor noise radar sensing [HASA-CR-137684] 875-23611 A75-35425 Civil aviation studies and interagency AIBCBAFT I4BDIHG coordinating organizations, volume 1 S-3A stall testing and auto-throttle aircraft noise reduction development/testing [PB-239344/5] 875-24186 A75-33613 Civil aviation studies and interagency The S-3A carrier suitability demonstration coordinating organizations, volume 2: Appendices A75-33614 aircraft noise reduction HOD - An important new aid to the L.S.O Head [PB-239345/2] H75-24187 Op Display for Landing Signal Officer AIBCBAFT PABTS A75-33620 Increasing the wear resistance of aircraft parts International and O.S. design proposals for a [BASA-TT-F-15759] 875-24723 microwave landing system AIBCBAFT FEBFOBHABCE A75-3U536 Low speed injection effects on the aerodynamic Involving the expert and aviation community in the performance at transonic speed decision making structure of the D.S. HLS program 875-234914 Microwave Landing System Research about effects of external flow and A75-34537 aircraft installation conditions on thrust Surface wind speed range as a function of time reversers performances interval and mean wind speed 875-23495 A75-35413 A model technique for exhaust system performance Aeronautical requirements and procedure for testing low-level turbulence and wind shear reporting 875-23502 A75-35414 AIBCBAFT PBODDCTI08 Hind shear effects on landing touchdown point B-1 - The road to first flight A75-35420 A75-3245S Lidar techniques for measuring slant visibility Hypersonic wing test structure design, analysis, for aircraft landing operations and fabrication A75-35434 [AIAA PAPEB 75-785] A75-32670 Aerodynamic aspects and optimisation of thrust Why so few all new General Aviation aircraft reverser systems design decision making factors 875-23513 A75-33619 Implications of eguipping a DC-8-61 fleet with AIBCBAFT RELIABILITY SHAV/two-segment approach avionics New Air Force requirements for structural safety, [BASA-CR-137680] 875-23544 durability and life management The out of service guest pilot evaluation of the [AIAA PAPEB 75-781] A75-32668 two-segment noise abatement approach in the AIBCBAFT SAFETT Boeing B727-200 Stone Spin Shorthand, including: Spin Data Card [HASA-CB-137625] H75-24696 and sample Criteria Spin Set for testing Dynamic heave-pitch analysis of air cushion out-of-control flight landing systems A75-33618 [8ASA-CB-2530] H75-24721
A-5 AHCBIFT STABILITY SOBJBCT IHDEI
A crashworthy armored pilot seat for helicopters Airborne wake vortex detection by in-flight [AD-A007551] H75-23541 radar sensing Safety-related engineering and development A75-35425 activities of the Federal Aviation Administration The effects of atmospheric stability, turbulence, [AD-A008395] H75-21698 and wind shear on aircraft wake behavior Safezone escape alert system development program. A75-35426 Phase 1: System development Experimental study of the effect on span loading [AD-A008561] H75-2*733 on aircraft wakes AIBCBAFT SIABILITT [HASA-TH-X-62431] H75-23479 Advances in fan and compressor blade flatter AIRFIELD SDBFACE HOVBBBBTS analysis and predictions The effect of chine tires on nose gear water-spray A75-3I4131 characteristics of a twin engine airplane Aircraft dynamics - Bhat pilots never ask [HASA-TH-X-72695] 1175-23555 flight stability tests AIBFOIL PROFILES A75-34299 Study of a strongly asymmetric turbulent wake The influence of short springs on longitudinal behind a profile with upper-surface separation static stability A75-32954 [CRAHFIBLD-AEBO-29] 1175-23607 A modern look at conformal mapping, including AIBCBAPT STBOCTORBS doubly connected regions for computerized A method to determine a distribution function of design of airfoil main structure failures in an aircraft [AIAA PAPEB 75-842] A75-33936 A75-32468 Finite element analysis of unsteady transonic flow Response of aircraft structural compartments to [AIAA PAPER 75-875] A75-33960 blast pressures and fragments from high Transonic flow about a thick circular-arc airfoil explosive projectiles [AIAA PAPEB 75-878] A75-33962 [AIAA PAPEB 75-751] A75-32652 An inverse method for the design of multielement Applications of a quadratic extended interior high-lift systems potential flow inversion penalty function for structural optimization [AIAA PAPEB 75-879] A75-33963 [AIAA PAPEB 75-764] A75-32654 Supercritical airfoil flowfield measurements Statistical estimation of service cracks and [AIAA PAPEB 75-880] A75-33964 maintenance cost for aircraft structures Dse of numerically generated body-fitted [AIAA PAPEB 75-767] A75-32657 coordinate systems for solution of the Aeroelastic panel optimization with aerodynamic Navier-Stokes eguations damping A75-34186 A75-33488 Transonic airfoil analysis and design using The effect of water path variations on ultrasonic Cartesian coordinates through-transmission sensitivity for A75-34195 adhesively bonded aircraft honeycomb structures Computer simulation of transonic flow past A75-34203 airfoils with boundary layer correction Titanium casting - Industrial development - A75-34196 Economic aspects A method for calculating flows through plane A75-35159 airfoil lattices Reproduction of the interaction of aerodynamic A75-34245 loads and structural distortions during strength Extension of the parabolic method for the tests transonic flow. I - Steady flow. II - Unsteady [AD-A007661] 1175-23520 flow Program to improve the fracture toughness and A75-35215 fatigue resistance of aluminum sheet and plate An investigation on the effect of second-order for aircraft applications, volume 2 additional thickness distributions to the upper [AD-A003417] N75-23775 surface of an HACA 64 sub 1-212 airfoil Fatigue properties of aircraft lugs with using flow equations and a CDC 7600 digital interference fit computer [TAE-243] H75-24031 [NASA-CB-137701] B75-24674 Flight service evaluation of PBD-49/epoxy An investigation on the effect of second-order composite panels in wide-bodied commercial additional thickness distributions to the upper transport aircraft surface of an NACA 64-206 airfoil using flow [HASA-CR-132647] H75-24719 eguations and a CDC 7600 digital computer Theoretical and experimental research on the [NASA-CB-137702] U75-24675 fatigue crack propagation in stiffened panels, Theoretical effect of modifications to the upper an evaluation of the Paris theory surface of two NACA airfoils using smooth [AD-A008079] N75-24732 polynomial additional thickness distributions Analysis and design of aircraft antennas which emphasize leading edge profile and which [NASA-CK-142945] H75-25057 vary guadratically at the trailing edge AIBCBAF1 TIBES using flow eguations and a CDC 7600 computer The effect of chine tires on nose gear water-spray [HASA-CB-137703] 1175-24676 characteristics of a twin engine airplane Low-speed aerodynamic characteristics of a [NASA-TB-X-72695 ] N75-23555 '13-percent thick airfoil section designed for AIBCBAFT WAKES general aviation applications Theoretical study of lift-generated vortex wakes [NASA-TB-X-72697] N75-24678 designed to avcid rollup AIRFOILS A75-33485 A rigorous solution of the Navier-Stokes eguations A three-dimensional solution of flows over wings for unsteady viscous flow at high Reynolds with leading-edge vortex separation numbers around oscillating airfoils [AIAA PSPEB 75-866] A75-33953 [AIAA PAPER 75-863] A75-33950 Inviscid to turbulent transition of trailing Calculation of transonic flows using an extended vortices integral eguation method [AIAA PAPEB 75-883] A75-33965 [AIAA PAPER 75-876] A75-33961 Experimental study of the effect of span loading Turbine airfoil life prediction by mission analysis on aircraft wakes A75-34143 [AIAA PAPEB 75-885] A75-33967 Transonic potential flow calculations using Vortex development and breakdown conservation form for shock-free airfoils [AIAA PAPEF 75-881] A75-35172 A75-34193 wake vortex decay near the ground A fast semidirect method for computing transonic [AIAA PAPEB 75-882] A75-35173 aerodynamic flows A predictive model of wake vortex transport A75-34194 A75-35423 Effectiveness of spoilers on the GA(H)-1 airfoil The motion of wake vortices in the terminal with a high performance Fowler flap environment [NASA-CB-2538] B75-23484 A75-35424 SOBJECT IBDEX iBBBSTIHG 6BAB
Prediction of unsteady aerodynamic loadings caused ALTEBBATIBG COBHBBT by leading edge and trailing edge control Practical stability of a reluctance synchronous surface notions in subsonic compressible flow: machine Computer program description [AD-A007659] B75-23605 [HASA-CB-13263II] B75-2«672 ALOHIBOH ALLOTS AIBFBAHB HiTBHIiLS Corrosion control in naval aircraft Development and testing under static conditions of 475-32830 a B-A1 load transfer element Program to improve the fracture toughness and [AliA PAPEB 75-788] A75-32675 fatigue resistance of aluainum sheet and plate Ion vapor deposited aluainum improves structure for aircraft applications, volume 2 durability airframe corrosion protective [AD-A003II17] B7S-23775 coatings Fatigue properties of aircraft lugs with [AIAA PAPEB 75-807] A75-32680 interference fit Determination of surface roughness of materials [T4E-243] B75-21031 A75-33331 Development of impact resistant boron/aluminum Boron/aluminum £or advanced technology aircraft composites for turbojet engine fan blades cost and weight advantages [BASA-CR-131770] B75-2«7«7 [AIAA PAPEB 75-790] A75-33762 ALOSIBDB C04TIBGS AIBFRAHES Ion vapor deposited aluminum improves structure Propulsion system and airfrane structural durability airframe corrosion protective integration program coatings 475-311118 (AIAA PAPEB 75-807] 475-32680 Airframe/propulsion interference 4H-2 4IBCH4FI [AGABD-CP-150] B75-23U85 The An-2 aircraft /ilth revised and enlarged edition/ Interaction problems between air intakes and Russian book aircraft A75-35350 N75-23<(86 ANALOG COHPDTEBS A criterion for prediction of airframe integration Implications of equipping a DC-8-61 fleet with effects on inlet stability with application to BB4V/two-segment approach avionics advanced fighter aircraft [BASA-CB-137680] B75-235UU S75-23487 AHALOG SIHOliTIOB Twin jet exhaust system test techniques Dynamic simulator for advanced gas turbine engine integrating airframe and propulsion system for component tests wind tunnel models A75-3II1116 B75-23500 ABBOLAB FLOS Accounting of aerodynamic forces on Spatial supersonic flow through annular cascades airframe/propulsion systems for designing [ASHE PAPER 75-GT-113] 475-31650 military aircraft ABTEBBA DESIGB H75- 23507 Small antennas fractional wavelength design Airframe/propulsion system flow field interference for wideband applications and the effect on air intake and exhaust nozzle A75-35827 performance Analysis and design of aircraft antennas H75-2350b [KASA-CB-1U291I5] B75-25057 Airframe: Engine interaction for engine 4HIEBI4 BADI4IIOB PATIEBHS configurations mounted above the wing. Part 1: Analysis and design of aircraft antennas Interference between wing and intake jet [HASA-CR-1U291I5] B75-25057 H75-23511 ABTIAIBCBAFT HISSILES Airframe: Engine interaction for engine Parametric analysis of an advanced manned configurations mounted above the wing. Part 2: interceptor utilization Engine jet simulation problems in wind tunnel [4D-A007663] B75-23563 tests ABTIOIIDAHTS N75-23512 Changes in the properties of hydrogenated fuels Subscale, hydrogen-burning, daring prolonged storing airframe-integrated-scramjet: Experimental and 475-35299 theoretical evaluation of a water cooled strut AHTISKID DEVICES airframe-integrated-scramjet: Experimental Test and performance criteria for airplane leading edge antiskid systems [BASA-TH-X-72682] N75-23885 [AD-4008536] B75-2U730 nondestructive holographic technigues for 4BIOBOV 4IBCBAFT structures inspection Rescue measures in the case of accidents of the [AD-A007850] N75-239U6 AB-12 aircraft Turbulent wake behind a self-propelled body 475-32527 [AD-A0081117] H75-2U690 APPHOACB COB1BOL Total airframe fatigue test P 10» G Velocity vector - The logical solution [AD-A007938] N75-2U726 aircraft guidance head-up displays AIBPLABE PBODOCTIOS COSTS A75-321I10 Boron/aluminum for advanced technology aircraft HOD - An important new aid to the L.S.O Bead cost and weight advantages Op Display for Landing Signal Officer [AIAA PAPEB 75-790] 475-33762 475-33620 AIBPOBTS Simulator evaluation of manually flown curved (JLS The motion of wake vortices in the terminal approaches Bicrowave Landing System environment 475-3H535 475-3511211 International and D.S. design proposals for a Airport noise reduction forecast. Volume 1: microwave landing system Summary report for 23 airports 475-311536 [PB-239387/H] B75-2U771 ARCTIC BEGIOBS 4IBSHIFS Loran-C compared with other navigation aids in Some problems posed by the aerodynamics of the meeting future Canadian needs dirigible balloon 475-35796 475-35810 4BE4 BAVIGAIIOB ALGOBITHBS Implications of equipping a DC-8-61 fleet with Four-dimensional guidance algorithms for aircraft BB4V/two-segment approach avionics in an air traffic control environment [H4S4-CR-137680] B75-235«« [HASA-TB-D-7829] H75-235U9 ABBBSIIHG GEAR AIL-BBATHBB IABDIHG STSTBBS The S-3A carrier suitability demonstration Velocity vector - The logical solution A75-33611 aircraft guidance head-up displays 475-32410
4-7 ABBOB RINGS SUBJECT INDEX
ABHOR RINGS The age of the RF7 data bus or the data bus comes A three-dimensional solution of flows over wings of age airborne computer test systems with leading-edge vortex separation A75-35261 [AIAA PAPEB 75-866] 475-33953 Software management and the compiler for F-111 ASPECT BAUD Automatic Test Equipment Drag effects on wing flutter A75-35261 [AIAA PAPEH 75-775] A75-32662 Flight test results of an automatic support system ASTBBBTBI on board a TF-12A airplane for jet engine Effects of asymmetry on the dynamic stability of inlet air control aircraft 475-35272 [NASA-CB-142857] N75-21756 The B-1 CITS system Central Integrated Test ATBOSPBBBIC BODHDABt LAIEB Subsystem The influence of wind shear on aerodynamic A75-35277 coefficients Automatic test equipment for S-3A support 475-35111 A75-35279 A study of self-similarity in boundary layer AVIONICS turbulence and its relevance to aircraft design The multi-mission Mirage F and operation A75-33832 475-35419 Beliability and maintainability allocation for ATMOSPHERIC SODELS avionic maintenance optimization The influence of wind shear on aerodynamic A75-35252 coefficients Autotest user needs at a base shop 475-35411 computerized Automatic Test Equipment for ATHOSPHEBIC TURBULENCE military avionics High altitude turbulence encountered by the A75-35253 supersonic YP-12A airplane The age of the BPV data bus or the data bus comes 475-35409 of age airborne computer test systems Aeronautical requirements and procedure for A75-35261 low-level turbulence and wind shear reporting AIIAL COBPBBSSIOB LOADS 475-35411 Design and fabrication of Bene 11 advanced Aircraft turbulence encounters during commercial structural panels their performance under operations in the vicinity of thunderstorms axial compression, shear, and bending loads 475-35118 [NASA-CB-132646] 1175-21032 A study of self-similarity in boundary layer Advanced beaded and tubular structural panels. turbulence and its relevance to aircraft design Volume 2: Fabrication and operation [HASA-CB-1 32482] S75-24717 475-35119 AXIAL FLOR TUBBINES The effects of atmospheric stability, turbulence, Three dimensional characteristics of turbulent and wind shear on aircraft wake behavior wakes behind rotors of axial flow turnomacbinery 475-35126 [ASBE PAPEB 75-GT-1] A75-34566 ATOHIZEBS Surge and rotating stall in axial flow preliminary study of low emission gas turbine compressors. I - Theoretical compression system combustor with airblast fuel atomizer model [ASI1E PAPEB 75-GT-31] 475-31588 [ASBE PAPEB 75-GT-9] A75-34573 ATTACK AIBCBAFT Study on the mechanism of stall margin improvement Mitsubishi's mentor - Supersonics from Nagoya of casing treatment of low speed axial flow T-2 close support fighter and trainer compressors A75-33118 [ASBE PAPEB 75-GT-13] A75-34576 An estimate of the effect of multiple ejection Propagating stall in compressors with porous walls rack flexibility on six degree of freedom store [ASBE PAPEB 75-GT-59] A75-34612 ejection conditions Experimental results of full scale air-cooled [AD-A008329] N75-21731 turbine tests AUTOMATIC CONTBOL [ASBE PAPEB 75-GT-116] A75-31653 Statistical analysis of the functioning guality of AXISIBBETBIC BODIES regulators with random parameter scatter Aerodynamic characteristics of an axisymmetric A75-32171 body undergoing a uniform pitching motion AUTOMATIC FLIGHT CONTBOL [AIAA PAPEB 75-838] A75-33933 Four-dimensional guidance algorithms for aircraft AXISIBHETBIC FLOR in an air traffic control environment Search for the final period of decay of the [NASA-TH-D-7829] S75-23519 axisymmetric turbulent wake Engineering and development program plan; en route A75-32439 control automatic flight data processing and An axisymmetric separated and reattached flow on a air traffic control longitudinal blunt circular cylinder [AD-A007623] 1175-23550 [ASBE PAPEB 75-APB-14] 475-35101 A formal structure for advanced automatic flight-control systems [NASA-TN-D-7910] N75-23606 B AOTOBATIC LANDING CONTBOL B-1 AIBCBAFT Simulator evaluation of manually flown curved BLS B-1 - The road to first flight approaches Hicrowave Landing System A75-32455 A75-31535 Variable geometry today latest swing wing international and U.S. design proposals for a aircraft microwave landing system A75-33447 A75-31536 B-1 airborne strategic deterrent AOTOBATIC TEST EQUIPMENT A75-33550 Automatic Test system for Jet Engine Accessories Analytical prediction of fatigue crack growth at A75-32396 cold-worked fastener holes computerized Automated test facility for aircraft hydraulic design for B-1 aircraft punps and motors [4I4A PAPBB 75-805] A75-33763 A75-32397 Beview of haamershock pressures in aircraft inlets Autotest user needs at a base shop A75-34115 computerized Autonatic Test Equipment for The B-1 CITS system Central Integrated Test military avionics Subsystem A75-35253 A75-35277 An automated tnnenp calibration of jet engine fuel controls A75-35258
A-8 SOBJECT IBDBX CARGO lIBCBirt
B-58 AIBCBAFT BOBOI ALLOTS vibration responses of test structure no. 1 during Development of impact resistant boron/aluminum the Edwards iir Force Base phase of the national composites for turbojet engine fan blades sonic boom program F-104, B-58, and XB-70 [BASA-CB-134770] 875-24747 sonic boom ezposares BOBOB BEIBPOBCED BATBBIALS [BASA-TB-I-72706 ] H75-24744 Development and testing under static conditions of B-70 AIBCBAFT a B-A1 load transfer element Vibration responses of test structure no. 1 daring [AIAA PAPEB 75-788] 475-32675 the Edwards Air Force Base phase of the national Boron/aluminum for advanced technology aircraft sonic boon prograi P-104, B-58, and XB-70 cost and weight advantages sonic boon exposures [4144 P4PEB 75-790] 475-33762 [HlSi-TH-X-72706] B75-24744 BOOIDABI IAIEB FLOf BBABIB6S Computer simulation of transonic flow past Current seal designs and future reqnirements for airfoils with boundary layer correction turbine engine seals and bearings 475-31196 A75-34123 Two-dimensional transonic? calculations with Fracture failure nodes in lightweight bearings boundary layers 475-31110 475-35819 BEHDI1S FATIGOB BOOBDABT IATEB SBPAB4TIOB Blade vibration - Sone key elements in design Study of the interaction and three-dimensional verification separation effects of a boundary layer in a 475-31132 supersonic laminar regime French book BEBDIB6 HOBEITS 475-35150 Design and fabrication of Rene 41 advanced BODBDABT 14IEB STABILITT structural panels their perfornance under Unsteady boundary layers over rotating blades axial compression, shear, and bending loads [ASHB P4PEB 75-GT-61] 475-31617 [BASA-CB-132646] B75-21032 BOOBDABI VALUE PBOBLBBS BBBDIHG VIBBATIOI Transonic airfoil analysis and design using Analytical displacements and vibrations of Cartesian coordinates cantilevered unsymmetnc fiber composite laminates 475-31195 [4144 PAPEB 75-757] 475-32688 BUBBLES BIOGBiPHI 4 model for the dynamics of a separation bubble Korolev: 4 chronicle a biography of Sergey used to analyze control-surface buzz and dynamic Favlovich Korolev stall [BASA-TT-F-16278] H75-21651 [4144 P4PEB 75-867] 475-33951 BIPLABBS BOCKLIBG The 4n-2 aircraft /4th revised and enlarged edition/ Crippling/column buckling analysis and test of Russian book graphite/epoxy-stiffened panels 475-35350 [4144 P4PEB 75-753] 475-32684 BIBDS Evaluation of bead-stiffened metal panels for 4 radar and direct visual study of the hazard to hypersonic aircraft and space systems design aircraft from bird migrations in the southwest [AI44 P4PEB 75-815] 475-32701 [4D-4008198] H75-21699 BLADB TIPS 4 study of casing treatment stall margin improvement phenomena for axial compressor CALIBBATIHG rotor blade tips 4n automated tuneup calibration of jet engine fuel [4SHE P4PEB 75-G1-60] 475-34613 controls EL4ST LOADS 475-35258 Response of aircraft structural compartments to CAHBEBED IIBGS blast pressures and fragments from high Studies and research on marine hulls working with explosive projectiles natural ground effect [4144 P4PEB 75-751] 475-32652 B75-23475 BLOBIBG CANABD COBFIGDBAIIOBS Haxinum lift of upper surface bloving STOL Effect of wing planform and canard location and aircraft with swept wings geometry on the longitudinal aerodynamic [4144 PAPEB 75-868] 475-33955 characteristics of a close-coupled canard wing BLOBT BODIES model at subsonic speeds Computation of noneguilibrium three-dimensional [BASA-TH-D-7910] 1175-23514 inviscid flow over blunt-nosed bodies flying at An experimental investigation of the aerodynamic supersonic speeds characteristics of several nose mounted canard [4144 P4PEB 75-835] A75-33931 configurations at supersonic Bach numbers An axisymmetric separated and reattached flow on a [AD-4007793] N75-23526 longitudinal blunt circular cylinder Effect of canard position and wing leading-edge [4SBE P4PEB 75-4PH-14] 475-35101 flap deflection on wing buffet at transonic speeds BODIES OF BEVOLOTIOI [B4S4-TM-X-72681] B75-23559 Problem of supersonic flow past a slender pointed CABTI1EVEB PLATES body with tail Analytical displacements and vibrations of 475-35706 cantilevered unsymmetric fiber composite laminates BODT-ilBG 4HD TAIL COBFIGORATIOBS [4IAA P4PEB 75-757] 475-32688 Integrated potential formulation of unsteady CABBOH FIBEB BEIBFOBCED PLASTICS supersonic aerodynamics for interacting wings Impact fracture of composite sandwich structures [4144 P4PEB 75-762] 475-32693 [AIAA PAPEB 75-748] 475-32673 BODT-BIBG COBFIGDBATIOBS Crippling/column buckling analysis and test of Image system solution for store aerodynamics with graphite/epoxy-stiffened panels interference. II ' [4144 P4PEB 75-753] 475-32684 475-33437 C4BGO BOEIBG 707 4IBCB4FT Flight test for the feasibility evaluation of the Pan American World Airways, Incorporated, Boeing Chadwick Electronic Weighing System (CHEWS) 707-321C, B4S8P4, Boston, Hassachusetts, [4D-4007516] N75-23522 November 1973 aircraft accident investigation Flight load investigation of helicopter external [PB-239448/4] N75-24701 loads BOEIBG 727 4IHCHAFT [4D-4008394] S75-24727 The out of service guest pilot evaluation of the CABGO AIBCB4FT two-segment noise abatement approach in the Cargo aircraft - 4 look toward the future Boeing B727-200 475-35290 [N4S4-CB-137625] H75-24696
4-9 CABIBSIA1 COOBDIIATBS SUBJECT IIDB*
Heavy lift helicopter; cargo handling ATC program. CIBCOLAB CILIBDBES Volume 2: Fabrication of test hardware and An axisymaetric separated and reattached flow on a fixtures integrated test rig longitudinal blunt circular cylinder [AD-A007244] N75-24721 [ASBE PAPEB 75-APB-11] A75-35101 CABtBSIAN COORDINATES CIVIL AVIATIOH Transonic airfoil analysis and design using Civil aviation studies and interagency Cartesian coordinates coordinating organizations, volume 1 175-3H195 aircraft noise reduction CASCADE FLOH [PB-239344/5] N75-24186 A method for calculating flows through plane Civil aviation studies and interagency airfoil lattices coordinating organizations, volume 2: Appendices A75-34245 aircraft noise reduction propagating stall in conpressors with porous walls [PB-239315/2] N75-21187 [ASHE PAPEB 75-61-59] A75-34612 CLUTCHES Trailing edge flows over turbomachiae blades and Advanced overrunning clutch technology, design phase the Kutta-Joukowsky condition [AD-A007815] 1175-23562 [ASBE PAPEE 75-GT-94] A75-31636 COAXIAL FLOW Spatial supersonic flow through annular cascades Thrnst/drag analysis for a front fan nacelle [ASHE PAPEB 75-GT-113] A75-34650 having two separate co-axial exhaust streams Effect on fan flow characteristics of length and [ABC-CP-1311] N75-23574 axial location of a cascade thrust reverser COCKPITS [NASA-TB-X-3247] N75-24745 CF5D aircraft cockpit-noise reduction CASBS (COSTAIHEES) [DCIEB-74-B-1048] N75-23564 Rapid verification of engine rotor and case COLD IEATHEB flexibilities by a modal comparison algorithm Observing cold-night temperatures of agricultural A75-34119 landscapes with an airplane-mounted radiation CASING thermometer Study on the nechanism of stall margin improvement A75-33103 of casing treatment of low speed axial flow COLD IOBKING compressors Analytical prediction of fatigue crack growth at [ASHE PAPEB 75-GT-13] A75-31576 cold-worked fastener holes computerized A study of casing treatment stall margin design for B-1 aircraft improvement phenomena for axial compressor [AIAA PAPEE 75-805] A75-33763 rotor blade tips COBBDSTION CBABBEBS [ASBE PAPEB 75-GT-60] A75-31613 Experimental investigation of a new concept of CAST ALLOTS fuel prevaporization for aircraft engine low Titanium casting - Industrial development - emission combustors Economic aspects [ASBE PAPEB 75-GT-6] A75-31570 A75-35159 Preliminary study of low emission gas turbine CATHODE EAY TOBES combustor with airblast fuel atomizer A holographic visor helmet-mounted display system [ASBE PAPEB 75-GT-31] A75-34588 A75-35283 Excess noise from gas turbine exhausts CAVITIES [ASBE PAPEB 75-GT-61] A75-34614 Stress concentration in an expanded plate with Development of a high-heat-release combustor for opening reinforced by central belt the F100 gas turbine [AD-A007672] N75-21014 [ASBE PAPEB 75-GT-86] A75-31631 CDC COHPDTBBS Exhaust pollutant emissions from swirl-can An investigation on the effect of second-order combustor module arrays at parametric test additional thickness distributions to the upper conditions surface of an NACA 64 sub 1-212 airfoil [NASA-TB-X-3237] 875-21716 using flow eguations and a CDC 7600 digital COHBOSTIOB COBTBOL computer A digital controller applied to the limitation of [NASA-CH-137701] N75-24674 reheat combustion roughness An investigation on the effect of second-order N75-23586 additional thickness distributions to the upper COBBDSTION EFFICIENCY surface of an NACA 61-206 airfoil using flow Experimental investigation of a new concept of eguations and a CDC 7600 digital computer fuel prevaporization for aircraft engine low [NASA-CB-137702] B75-24675 emission combustors Theoretical effect of modifications to the upper [ASHE PAPEB 75-GT-6] A75-31570 surface of two N&CA airfoils using smooth Flow characteristics of various swirl-can module polynomial additional thickness distributions designs exhaust flow simulation, flow which emphasize leading edge profile and which characteristics, and combustion efficiency of vary guadratically at the trailing edge • jet engine fuels using flow eguations and a CDC 7600 computer [NASA-TB-X-3236] H75-21710 [NASA-CR-137703] 875-21676 COBBEBCIAL AIBCBAFT CBBASICS Air transportation of radioactive materials Design and analysis of a ceramic stator vane A75-33568 [ASBE PAPER 75-GT-100] A75-3U612 Challenge to aviation: Hatching a leaner pterosauer CH-54 BELICOPTEB improving commercial aircraft design for Flight load investigation of helicopter external greater fuel efficiency loads [NASA-TB-X-71711] N75-25298 [AD-A008391] N75-24727 COBPILEBS CHANNEL FLOI Software management and the compiler for F-111 A theoretical analysis for three dimensional ram Automatic Test Equipment wings in parallel walls A75-3526U A75-33127 COBPONENT RELIABILITY CBABHBLS (DATA TBABSHISSIOH) Systematic development testing for engine The age of the BPV data bus or the data bus comes structural integrity assurance of age airborne computer test systems A75-31147 A75-35261 COBPOSITE BATEBIALS CHEBICAL BACHIIIBG Hechanics of composite materials Book Chemical milling review A75-32163 A75-32810 The effect of water path variations on ultrasonic CHBOBATOGBAPHT through-transmission sensitivity for Application of thin-layer chromatography for adhesively bonded aircraft honeycomb structures determining the wearing capacity of additives A75-31203 contained in petroleum-based aviation oils Design of composite structure with respect to A75-35300 avoid crack propagation N75-23709
A-10 SOBJECT IBDEX COBTBOL SDBFACBS
Plight service evaluation of PRD-U9/epoxy Bapid verification of engine rotor and case coDposite panels in vide-bodied commercial flexibilities by a modal comparison algorithm transport aircraft A75-31119 [BASA-CB-132647] N75-24719 Philosophy, design, and evaluation of soft-mounted Process evaluation of directionally solidified engine rotor systems NI3Cb reinforced eutectics in turbine blade forn A75-34130 [AD-A008435] 1175-24926 Turbine Engine Structural Integrity Program /EBSIP/ COHPOSITB STBOCTOBES A75-34137 Boron/aluminum for advanced technology aircraft Analysis of rotor fragment impact on ballistic cost and weight advantages fabric engine burst containment shields [AIAA PAPEB 75-790] A75-33762 A75-3H141 COHPBESSOB BLADES Turbine airfoil life prediction by mission analysis Advances in fan and compressor blade flutter A75-34143 analysis and predictions Supercritical wing sections II: A handbook A75-31H31 numerical computations Blade vibration - Some key elements in design A75-34975 verification Computer-augmented design of aircraft wing A75-34132 structures Hisslie firing tests at stationary targets in N75-23554 support of blade containment design for COHPOTEBIZBD SIHOLATIOH aircraft engines Transonic flow about a thick circular-arc airfoil [ASHE PAPEH 75-GT-17] A75-34604 [AIAA PAPEB 75-878] A75-33962 Propagating stall in compressors with porous vails Computer simulation of transonic flow past [ASHE PAPER 75-G1-59] A75-34612 airfoils with boundary layer correction COBPBESSOB BOTOBS A75-34196 Bapid verification of engine rotor and case Wind-tunnel tests and computer simulations of flexibilities by a modal comparison algorithm buoyant wing-tip vortices A75-31H19 A75-35 A-11 COBE FLOS SOBJECT IBDEX Active flutter suppression using trailing-edge and CBACKING (FBACTOBIHG) tab control surfaces Statistical estimation of service cracks and [AIAA PAPEB 75-822] A75-32697 maintenance cost for aircraft structures A model for the dynamics of a separation bubble [AIAA PAPEB 75-767] A75-32657 used to analyze control-surface buzz and dynamic CBABES stall High-capacity transport planes as modern air [AIAA PAPER 75-867] A75-33954 freight systems Maximum lift of upper surface blowing STOL [NASA-TT-F-16396] N75-23533 aircraft with swept vings CRASH LABDIHG [AIAA PAPEB 75-868] A75-33955 Analysis of distress air cases in relation to Hind tunnel test of a flutter suppressor on a crash position and intended track: 1968 - 1973 straight wing [AD-A007U29] 875-23540 [ONERA, IP NO. 1975-31] "~ A75-35869 CBASHES CORE FLOW Pan American Horld Airways, Incorporated, Boeing Vortex development and breakdown 707-321C, M158PA, Boston, Massachusetts, [AIAA PAPEB 75-881] A75-35172 November 1973 aircraft accident investigation COSEOSIOB PBBVBHTIOH [PB-239148/4] B75-21701 Ion vapor deposited aluminum improves structure Sierra Pacific Airlines, Incorporated Convair durability airframe corrosion protective 310/410, H4819C near Bishop, California, 13 coatings March 1971 aircraft accident investigation [AIAA PAPEB 75-807] A75-32680 [PB-239511/9] B75-21702 Corrosion control in naval aircraft CBEEP ANALYSIS A75-32830 Low-cycle fatigue and creep analysis of gas COBHOSIOH BESISTABCE turbine engine components The economic advantages of low and high A75-31139 temperature anti corrosion coatings on jet CBOSS FLOI engine parts - A case history Image system solution for store aerodynamics with A75-35449 interference. I COBHOSIOH TESTS A75-33136 The dynamics of atmospheric dust particles in Image system solution for store aerodynamics with aircraft auxiliary power radial inflow turbines interference. II [AIAA PAPEB 75-811] A75-33938 A75-33437 COST ANALYSIS Computational procedure for three-dimensional Computer program to assess impact of fatigue and boundary layers on aircraft and aerospace vehicles fracture criteria on weight and cost of A75-34190 transport aircraft CBDISIBG FLIGHT [NASA-CB-132648] H75-24718 Jet interference of a podded engine installation Analysis of technology reguirements and potential at cruise conditions demand for general aviation avionics systems in B75-23490 the 1980's technology assessment and CDBVATOBE technological forecasting of the aircraft industry Unsteady behavior of transonic flows shock [HASA-CB-137629] N75-2U735 induced oscillation COST EFFECTIVEHESS [HPIS-HITT-59] H75-23516 Stochastic model for fatigue crack size and cost CDRVED PABBLS effective design decisions for aerospace Evaluation of bead-stiffened metal panels for structures hypersonic aircraft and space systems design [AIAA PAPEB 75-766] A75-32656 [AIAA PAPEB 75-815] A75-32701 Implications of eguipping a DC-8-61 fleet with CV-340 AIBCBAFT BNAV/two-segment approach avionics Sierra Pacific Airlines, Incorporated Convair [NASA-CB-137680] N75-235U4 310/440, H4819C near Bishop, California, 13 Airport noise reduction forecast. Volume 1: Harch 1974 aircraft accident investigation Summary report for 23 airports [PB-239511/9] H75-24702 [PB-239387/4] N75-24771 CYCLIC HTDBOCABBOHS COST ESTIHATES Development of high stability fuel Statistical estimation of service cracks and [AD-A007574] H75-23604 maintenance cost for aircraft structures CYLIHDBICAL BODIES [AIAA PAPEB 75-767] A75-32657 Aerodynamic characteristics of an axisymmetric CODPLINGS body undergoing a uniform pitching motion RAflex drive shaft coupling for OH-1 helicopter. [AIAA PAPER 75-838] A75-33933 Design refinement Problem of supersonic flow past a slender pointed [AD-A008365] H75-24731 body with tail CBACK IHITIiTIOH A75-35706 A fracture mechanics approach to turbine airfoil design [ASBE PAPEB 75-GT-79] A75-34628 CBACK PBOPAGATIOH DASSAULT AIBCBAFT Stochastic model for fatigue crack size and cost The multi-mssion Mirage F effective design decisions for aerospace A75-33832 structures DATA ACQUISITION [AIAA PAPER 75-766] A75-32656 The B-1 CITS system Central Integrated Test Analytical prediction of fatigue crack growth at Subsystem cold-worked fastener holes computerized A75-35277 design for B-1 aircraft DATA MABAGBMEBT [AIAA PAPER 75-805] A75-33763 Software management and the compiler for F-111 A fracture mechanics approach to turbine airfoil Automatic Test Equipment design A75-35261 [ASHE PAPEB 75-GT-79] A75-34628 DATA PBOCESSIBG Design of composite structure with respect to Air traffic controllers' operative effectiveness avoid crack propagation under DAS environments H75-23709 A75-34539 Theoretical and experimental research on the Engineering and development program plan; en route fatigue crack propagation in stiffened panels, control automatic flight data processing and an evaluation of the Paris theory air traffic control [AD-A008079] H75-21732 [AD-A007623] H75-23550 Crack growth under spectrum loading: A crack DATA PBOCESSIBG TBRMIBALS closure model Preliminary results from pilot aviation weather [NASA-TH-X-72708] H75-25221 self-briefing experiments A75-35428 A-12 SOBJECT I8DEI 1IGIBE COISBOL Dill BBCOBDIBG DTB1BIC HODBLS Stone Spin Shorthand, including: Spin Data Card Drag effects on wing flutter and sample Criteria Spin Set for testing [AIAA F1PEB 75-775] 175-32662 ont-of-control flight DIBABIC BBSPOBSB A75-33618 Response of aircraft structural compartments to DBCISIOB B1KIBG blast pressures and fragments fro* high Ihy so few all new General Aviation aircraft explosive projectiles design decision Halting factors [1111 PIPES 75-751] 175-32652 175-33619 Dynanic response of viscous-damped multi-shaft jet Involving the expert and aviation community in the engines decision oaking structure of the D.S. BLS program 175-34128 Bicrovave Landing System Aircraft dynamics - Bhat pilots never ask 175-3*537 flight stability tests DELTA iIHGS 175-34299 Experimental stady of heat transfer daring flow Structural response of fiber composite fan blades around uncaubered delta wings with blunted edges [1SBE PIPES 75-GT-78] 175-34627 [AD-A007316] B75-23524 Generalized dynamic engine simulation techniques Hydroaerodynamic characteristics of a low aspect for the digital computers ratio delta wing near a screen B75-23593 [ID-A007649] B75-23529 DIBASIC STBDCTOBAL ABA1YSIS DBSCBBT TBAOBCTOBIES System identification of a complex structure Analysis of various descent trajectories for a helicopter gearbox dynamics from shake test data hypersonic-cruise, cold-wall research airplane [1111 PIPEH 75-809] 175-32705 [NASA-TN-D-7860] B75-24673 Vibration analysis of multi-symmetric structures DESIGH ASALTSIS [AIAA PAPEB 75-808] 175-32706 Current seal designs and future reguirements for turbine engine seals and bearings A75-34123 Design and analysis of a ceramic stator vane ECOBOSIC ABALISIS [1SHE PAPEB 75-GT-100] A75-34642 Titanium casting - Industrial development - Guide for the design of control sticks in Economic aspects vibration environments aircraft nanual A75-35159 control eguipment The economic advantages of low and high [AD-A008533] N75-24729 temperature anti corrosion coatings on jet DIFFBACTIOB PATTEHBS engine parts - 1 case history General analysis of the diffraction pattern for a A75-354J49 plane acoustic wave at a wedge moving at EJECTIOB SEATS supersonic speed Emergency ejection, seguence of operation 175-34272 [1D-1007470] H75-23539 DIGITAL SYSTBBS EJBCTOBS Digital flight control systems for tactical Concurrent mixing and diffusion in three dimensions fighters. Volume 3. Digital flight control ejector performance systen design consideration [1IAA PAPEB 75-873] A75-35170 [AD-A002687] B75-24754 ELASTIC DEFOHBATIOB Digital flight control system for tactical fighters Reproduction of the interaction of aerodynamic * [AD-A002686] B75-24757 loads and structural distortions during strength DIGITAL TECBHIQOES tests The use of digital control for couple* power plant [1D-A007661] B75-23520 management ELASTIC SISTBBS H75-23596 Formation of flexibility matrices of a structure Digital flight control systems for tactical based on known yields at arbitrary points fighters. Volume 3. Digital flight control A75-32995 system design consideration BLECTBIC BOTOBS [AD-A002687] H75-2U754 Automated test facility for aircraft hydraulic Digital flight control system for tactical fighters pumps and motors [AD-A002686] N75-24757 175-32397 DISPLAY DEVICES Practical stability of a reluctance synchronous A holographic visor helmet-mounted display system machine A75-35283 [AD-1007659] B75-23605 Advanced gallium phosphide L.E.D. displays ELECTBIC POBEB PLABTS A75-35284 Besponse of a light aircraft to a thermal exhaust DISTBIBDTIOH POBCTIOBS plume A method to determine a distribution function of A75-35403 main structure failures in an aircraft ELECTBOSIC COBTBOL 175-32468 A new lightweight fuel control system for DOBBBASB electrical inputs considering gas turbine Theoretical downwash velocities about the AH-1G engines helicopter at hover and 140 knots B75-23599 [AD-A008339] B75-24693 ELECTBOHIC FILTEBS DB1G Interaction between control augmentation system Thrust/drag analysis for a front fan nacelle and airframe dynamics on the YF-17 having two separate co-axial exhaust streams [1111 PAPEB 75-824] A75-32694 [ABC-CP-1311] H75-23574 ELE71TOBS (LIFTS) DB1G BESSOBBBEHT High-capacity transport planes as modern air Transonic off-design drag and performance of three freight systems mixed-compression axisymmetric inlets [BASA-TT-F-16396] B75-23533 [BASA-TB-X-3215] B75-23602 EBEBGY COBSBBVATIOB DUCTED FIBS Preliminary study of advanced turboprops for low A design study of a fan augmented ramjet energy consumption [ASBE PAPER 75-GT-97] A75-34639 [H1SA-TB-X-71740] B75-24739 DOST EHEBGY COBSDBPTIOH The dynamos of atmospheric dust particles in Preliminary study of advanced turboprops for low aircraft auxiliary power radial inflow turbines energy consumption [AIAA PAPER 75-844] A75-33938 [KASA-TB-X-71740] B75-24739 DIH1HIC COBTBOL EBGIBE COBTBOL A means of dynamic control of radar reflectivity Statistical analysis of the functioning quality of of an antenna or other object by means of a regulators with random parameter scatter gaseous plasma shroud A75-32471 A75-34854 A-13 BIGIIE DBSIGI SUBJECT IBDBI Laboratory testing of controls for aircraft Performance development of the Gem turboshaft engine turbine engines for helicopter application [ASHB PAPBB 75-GT-101] A75-34643 [ASHE PAPBH 75-GT-28) 475-34586 in application of modern control theory to jet Preliminary study of low emission gas turbine propulsion systems considering onboard combustor with airblast fuel atomizer coipater [ASBE PAPER 75-GT-31] 475-34588 [HASA-TH-X-71726 ] N75-23573 Hissile firing tests at stationary targets in Pover plant controls for aero-gas turbine engines support of blade containment design —;- for [AG4HD-CP-151] N75-23575 aircraft engines Contribution of flight Emulation tests to the [ASHE PAP1B 75-GT-47] 475-34604 study of turbonachine control Development of a high-heat-release combustor for N75-23577 the F100 gas turbine An airframe manufacturer's requirements for future [ASHE PAPER 75-GT-86] 475-31631 propulsion controls A design study of a fan augmented ramjet N75-23578 [ASHE PAPER 75-GT-97] 475-31639 Control system requirements dictated by NASA refan program status for noise reduction optimization of engine operation of JT8D turbofan engine N75-23579 [HASA-TH-X-71705] S75-23570 Reliability specification for gas turbine control Turbine design and application, volume 3 systems [NASA-SP-290-VOL-3] N75-21711 N75-23581 Hypersonic research engine project, phase 2. Control design considerations for variable Preliminary report on the performance of the geometry engines HRE/AIH at Bach 6 N75-2J583 [S4SA-CR-132538] N75-24712 PR4C: 4 new aero gas turbine engine control concept Hypersonic research engine project. Phase 2A: N75-23584 Instrumentation program Helicopter engine control: The past 20 years and [N4SA-CB-132593] B75-24743 the next EBGIBB FAILURE N75-23585 Diagnostics of jet aero-engines by means of Eguilibrium performance analysis of gas turbine spectral analysis of lubricating oil engines using influence coefficient techniques A75-32470 N75-23592 F100 fan stall flutter problem review and solution Ose of simulation in the design, development and A75-34134 testing of power plant control systems Analysis of rotor fragment impact on ballistic N75-23595 fabric engine burst containment shields The use of digital control for complex power plant 475-31141 management Botor burst protection program - Statistics on N75-23596 aircraft gas turbine engine rotor failures that Fluidic sensors for turbojet engines occurred in O.S. commercial aviation during 1973 N75-23598 [ASHE PAPER 75-GT-12] A75-34575 ENGIHE DBSIGH Hissile firing tests at stationary targets in Identification of systems by means of adaptive model support of blade containment design for application to ]et engines aircraft engines 475-32473 [ASHE PAPER 75-GT-47] A75-34604 Materials for gas turbines review ENGINE INLETS AT 5-32 839 Review of hammershock pressures in aircraft inlets Regenerative turbofans - A comparison with 475-31115 nonregenerative units aircraft engine The refracting inlet - A new concept for aircraft performance inlet noise suppression 475-33438 [ASHE PAPER 75-GT-21] A75-34580 Propulsion system structural integration and Flight test results of an automatic support system engine integrity; Proceedings of the Symposium, on board a IF-124 airplane for ]et engine U.S. Naval Postgraduate School, Honterey, inlet air control Calif., September 3-6, 1974 A75-35272 475-34112 ENGINE HONITOBING INSTROHBNTS Structural integrity for propulsion systems Hypersonic research engine project. Phase 2A: 475-34113 Instrumentation program YF-16 air induction system design loads associated [NASA-CR-132593] N75-24743 with engine surge ENGINE BOISE 475-34111 The refracting inlet - A new concept for aircraft Control of gas turbine stator blade vibrations by inlet noise suppression means of enamel coatings [ASHE PAPER 75-GT-21] A75-34580 475-31116 Excess noise from gas turbine exhausts Rapid verification of engine rotor and case [ASHE PAPER 75-GT-61] 475-34614 flexibilities by a modal comparison algorithm N4S4 refan program status for noise reduction 475-31119 of JT8D turbofan engine Design and development of low-cost, self-contained [N4S4-TH-X-71705] B75-23570 bearing lubrication systems for turbine engines BHGINE P4BTS 475-31121 Current seal designs and future requirements for Philosophy, design, and evaluation of soft-mounted turbine engine seals and bearings engine rotor systems 475-34123 475-31130 Low-cycle fatigue and creep analysis of gas Blade vibration - Some key elements in design turbine engine components verification 475-31139 475-31132 Dynamic simulator for advanced gas turbine engine Turbine Engine Structural Integrity Program /ENSIP/ component tests 475-3t137 475-34146 Analysis of rotor fragment impact on ballistic The economic advantages of low and high fabric engine burst containment shields temperature anti corrosion coatings on jet 475-34111 engine parts - A case history Design of fabricated static structures for long A75-35419 cyclic life E8GIHB TESTS A75-31112 Automatic Test System for Jet Engine Accessories Turbine airfoil life prediction by mission analysis A75-32396 A75-31143 Transmissivity of light - One of the quantities Experimental investigation of a new concept of usable in the diagnostics of oil in a motor fuel prevaporization for aircraft engine low 475-32172 emission combustors [ASHE PAPER 75-GT-6] 475-31(570 A-11 SUBJECT IHDEI FABBICS Philosophy, design, and evaluation of soft-mounted EXHAUST HOZZLBS engine rotor systems Effect of simulated forward flight on subsonic jet A75-34130 exhaust noise P100 fan stall flatter problem review and solution [AIAA PAPEB 75-869] A75-33956 A75-31134 Beynolds number effects on boattail drag of Dynamic simulator for advanced gas turbine engine exhaust nozzles from wind tunnel and flight tests component tests 875-23506 A75-31146 EXHADST SISTERS Systematic development testing for engine External fins and ejector action for reducing the structural integrity assurance infrared emission of engine exhaust ducting A75-34117 [NASA-TB-X-3212] 875-25091 Ground vertex - Lioit to engine/reverser operation EIPEBIHEHTAL DESIGB for high bypass ratio engine Advanced overrunning clutch technology, design phase [ASBE PiPEB 75-GT-3] 475-31567 [AD-A007815] 875-23562 Bissile firing tests at stationary targets in BITEBBAL STOBBS support of blade containment design for Image system solution for store aerodynamics with aircraft engines interference. I [ASBE PAPER 75-61-17] A75-31601 A75-33436 Laboratory testing of controls for aircraft Image system solution for store aerodynamics with turbine engines interference. II [ASHE PAPER 75-GT-101] A75-34613 A75-33137 Experimental results of full scale air-cooled An investigation of the flow field of the A-7D turbine tests aircraft with several external store loadings at [ASME PAPEB 75-GT-116] A75-31653 Hach numbers 0.70 and 0.95 EQOILIBBIUH BQOATIOBS [AD-A008176] 875-21688 Aerodynamics of rotors - Bake equilibration An estimate of the effect of multiple ejection A75-35811 rack flexibility on six degree of freedom store EQOILIBEIOB BETROCS ejection conditions Equilibrium performance analysis of gas turbine [AD-A008329] 875-21734 engines using influence coefficient techniques N75-23592 EQOIPHEST SPECIFICATION Pumping system design related to fuel system F-14 AIBCBAFT specifications Variable geometry today latest swing wing N75-23600 aircraft ESCAPE SYSTEBS A75-33117 Safezone escape alert system development program. F-15 AIBCBAFT Phase 1: System development Hinimum weight design of the F-15 empennage for [AD-A008561] N75-21733 flutter BUBOPEAB AIRBUS [AIAA PAPEB 75-777] A75-32661 Interaction of jets of GE CP6-50 reactors with the F-16 AIBCBAFT wing cellules of the airbus during cruise - The random decrement technique applied to the Hind-tunnel simulation YF-16 flight flutter tests A75-35808 [AIAA PAPEB 75-776] A75-32663 EOTECTIC ALLOTS YF16 active-control-system/structnral dynamics Directionally solidified lamellar eutectic interaction instability superalloys by edge-defined, film-fed growth [AIAA PAPEB 75-823] A75-32695 including tensile tests YF-16 - A rare opportunity flight test program [NASA-CB-134808] N75-24897 A75-33615 Process evaluation of directionally solidified YF-16 air induction system design loads associated NI3Cb reinforced eutectics in turbine blade form with engine surge [AD-A008435] N75-2U926 A75-31114 EXHAUST DIFFOSEBS F-17 AIBCBAFT Concurrent nixing and diffusion in three dimensions Interaction between control augmentation system ejector performance and airframe dynamics on the YF-17 [AIAA PAPEB 75-873] A75-35170 [AIAA PAPEB 75-824] A75-32694 EXHAUST FLOR SIHDLJTIOH F-102 AIBCBAFT Flow characteristics of various swirl-can module On the way to tactical aircraft robotics designs exhaust flow simulation, flow ground based radar control of F-102 A characteristics, and combustion efficiency of A75-32452 jet engine fuels F-104 AIBCBAFT [NASA-TH-X-3236] N75-21710 Total airframe fatigue test F 104 G EXBADST GASES [AD-A007938] 875-21726 Preliminary study of low enission gas turbine Vibration responses of test structure no. 1 during combustor with airblast fuel atomzer the Edwards Air Force Base> phase of the national [ASBE PAPEB 75-GT-31] A75-34588 sonic boom program F-101, B-58, and XB-70 Excess noise from gas turbine exhausts sonic boom exposures [ASHE PAPEB 75-GT-61] A75-31611 [HASA-TH-X-72706] 875-21741 Response of a light aircraft to a thermal exhaust F-111 AIBCBAFT plume Variable geometry today latest swing wing A75-35403 aircraft An experimental study of jet exhaust simulation A75-33147 H75-23501 Software management and the compiler for F-111 A model technique for exhaust system performance Automatic Test Equipment testing A75-35261 H75-23502 FABBICATIOB Exhaust plume tenperatnre effects on nozzle Fabrication of one-piece-forged thin-walled parts afterbody perfornance over the transonic Bach having variable cross section Russian book number range A75-33150 H75-23501 Design of fabricated static structures for long Thrust/drag analysis for a front fan nacelle cyclic life having two separate co-axial exhaust streams A75-31142 [ABC-CP-1311] 875-23571 PABBICS Exhaust pollutant emissions from swirl-can Analysis of rotor fragment impact on ballistic coabttstor nodule arrays at parametric test fabric engine burst containaent shields conditions A75-31141 [HASA-TH-X-3237] H75-21716 A-1S FAILOBB ANALYSIS SUBJECT INDEX PAILDEE ANALYSIS FIHITE DIFFBBEBCB TBEOBI A method to determine a distribution function of A modern look at conformal mapping, including main structure failures in an aircraft doubly connected regions for computerized A75-32468 design of airfoil Crippling/column buckling analysis and test of [AIAA PAPEB 75-842] A75-33936 graphite/epoxy-stiffened panels Computational procedure for three-dimensional [AIAA PAPEB 75-753] A75-3268U boundary layers on aircraft and aerospace vehicles FAILURE BODES A75-34190 Fracture failure modes in lightweight bearings A fast semidirect method for computing transonic A75-34140 aerodynamic flows FABHLAHOS A75-34194 Observing cold-night temperatures of agricultural Calculations of three-dimensional flows in a landscapes with an airplane-mounted radiation linearized supersonic regime thermometer A75-35813 A75-33103 FINITE ELEMENT METHOD FASTENBBS Analytical displacements and vibrations of Analytical prediction of fatigue crack growth at cantilevered unsymmetric fiber composite laminates cold-worked fastener holes computerized [AIAA PAPEB 75-757] A75-32688 design for B-1 aircraft Oscillatory supersonic lifting surface theory [AIAA PAPEE 75-805] A75-33763 using a finite element doublet representation FATIGUE (HATBBIALS) [AIAA PAPEB 75-761] A75-32692 Program to improve the fracture toughness and Finite element analysis of unsteady transonic flow fatigue resistance of aluminum sheet and plate [AIAA PAPEB 75-875] A75-33960 for aircraft applications, volume 2 A finite-element method for lifting surfaces in [&D-A003417] N75-23775 steady incompressible subsonic flow Computer program to assess impact of fatigue and [NASA-CB-142811] N75-23477 fracture criteria on weight and cost of Subsonic and supersonic indicial aerodynamics and transport aircraft aerodynamic transfer function for complex [SASA-CB-1326U8] H7S-24718 configurations aerodynamic configurations Theoretical and experimental research on the for subsonic and supersonic speeds using the fatigue crack propagation in stiffened panels, finite element method an evaluation of the Paris theory [NASA-CB-142818] H75-23478 [AD-A008079] N75-24732 Calculation of the reinforced thin-walled Crack growth under spectrum loading: A crack construction by the method of the final element closure model [AD-A007307] N75-23560 [SASA-TH-X-72708 ] 875-25221 FIDS FATIGUE LIFE External fins and ejector action for reducing the Stochastic model for fatigue crack size and cost infrared emission of engine exhaust ducting effective design decisions for aerospace [NASA-TH-X-3242] N75-25094 structures FIBBS [AIAA PAPER 75-766] A75-32656 Aircraft engine nacelle fire test simulator Total airframe fatigue test F 101 G [AD-A007853] 1175-23617 [AD-A007938] N75-24726 FLAPS (COHTBOL SDBFACBS) FATIGUE TESTS Calculation of static longitudinal aerodynamic A method to determine a distribution function of characteristics of STOL aircraft with upper main structure failures in an aircraft surface blown flaps A75-32468 [NASA-CB-137646] B75-23483 low-cycle fatigue and creep analysis of gas Full scale upper surface blown flap noise turbine engine components [NASA-TM-X-71708] H75-23569 A75-34139 Beversed cowl flap inlet thrust angmentor with Fatigue properties of aircraft lugs with adjustable airfoil interference fit [NASA-CASE-ABC-10754-1] N75-24736 [TAE-243] H75-24031 FLEXIBILITY FEEDBACK CONTBOL Method of the optimization of the load-carrying Interaction between control augmentation system structure of wing on rigidity during variation and airframe dynamics on the YF-17 by the distribution of thickness ratio [AIAA PAPEB 75-824] A75-3269U [AD-A007317] N75-23521 FIGBTEB AIBCBAFT FLEXIBLE BODIES The multi-mission Mirage F Bapid verification of engine rotor and case A75-33832 flexibilities by a modal comparison algorithm System concept and key problems concerning A75-34119 pilotless, remotely-controlled conbat aircraft OKF PLIGHT CHABACTEBISTICS [ DGLB PiPEB 74-076A] A75-34725 The An-2 aircraft /4th revised and enlarged edition/ Flight test results of an automatic support system Russian book on board a TF-12A airplane for Jet engine A75-35350 inlet air control FLIGBT COBTHOL A75-35272 Digital flight control systems for tactical A criterion for prediction of airframe integration fighters. Voluie 3. Digital flight control effects on inlet stability with application to system design consideration advanced fighter aircraft [AD-A002687] H75-24754 N75-23487 Digital flight control system for tactical fighters Emergency ejection, sequence of operation [AD-A002686] H75-24757 [AD-A007470] H75-23539 FLIGBT PATHS Design and analysis of a supersonic Analysis of distress air cases in relation to penetration/maneuvering fighter crash position and intended track: 1968 - 1973 [NASA-CB-132633] N75-23558 [AD-A007429] H75-23540 Parametric analysis of an advanced manned Four-dimensional guidance algorithms for aircraft interceptor utilization in an air traffic control environment [AD-A007663] H75-23563 [SASA-TH-D-7829] S75-23549 Advanced maneuverability options for future fighters The out of service guest pilot evaluation of the [AD-A008497] H75-24725 tvo-segment noise abatement approach in the Digital flight control systems for tactical Boeing B727-200 fighters. Volnne 3. Digital flight control [NASA-CB-137625] B75-24696 system design consideration FLIGHT SAFETY [AD-A002687] H75-24754 Stone Spin Shorthand, including: Spin Data Card Digital flight control system for tactical fighters and sample Criteria Spin set for testing [AD-A002686] H75-24757 out-of-control flight A75-33618 A-16 SDEJECT IHDEX FLOOBOSCOPY FLIGHT SIBOLATIOB An axisymietric separated and reattached flow on a Effect of simulated forward flight on sabsonic jet longitudinal blunt circular cylinder exhaust noise [ASBB PAPEB 75-APH-14] A75-35101 [AIAA PAPEB 75-869] 175-33956 Flow characteristics of various swirl-can module Rind tunnel tests for the determination of the designs exhaust flow siaulation, flow behavior of aircraft external loads which are characteristics, and combustion efficiency of dropped jet engine fuels A75-35098 [HASA-TH-X-3236] 875-20700 An experimental study of jet eihaast simulation Effect on fan flow characteristics of length and H75-23501 axial location of a cascade thrust reverser Contribution of flight simulation tests to the [BASA-TB-X-32H7] B75-24745 study of turboaachine control FLOi DISTOBTIOB H75-23577 Ground vortex - Limit to engine/reverser operation FLIGHT SIMULATORS for high bypass ratio engine Becent advances in in-flight simulator technology [ASBE PAPEB 75-GT-3] A75-31567 A75-33187 FLOI DISTBIBDTIOB Simulator evaluation of manually flown carved HLS Supercritical airfoil flowfield measurements approaches Hicrowave Landing System [AIAA PAPEB 75-880] A75-33964 A75-3H535 Airframe/propulsion system flow field interference FLIGHT STABILITY TESTS and the effect on air intake and exhaust nozzle Interaction between control augmentation system performance and airfraae dynamics on the IF-17 H75-23508 [AIAA PAPEB 75-8211] A75-32691 An investigation of the flow field of the A-7D YF16 active-control-system/structural dynamics aircraft with several external store loadings at interaction instability Bach numbers 0.70 and 0.95 [AIAA PAPEB 75-823] A75-32695 [AD-A008076] H75-21688 Aircraft dynamics - Hhat pilots never ask FLO! BQOATIOHS flight stability tests A method for calculating flows through plane A75-3«299 airfoil lattices FLIGHT TESTS A75-34245 B-1 - The road to first flight Integral equations for the calculation of the flow A75-32U55 about accelerated slender bodies for a greater, The random decrement technique applied to the equal, or less than 1 YF-16 flight flutter tests A75-3520* [AIAA PAPEB 75-776] A75-32663 An investigation on the effect of second-order B-1 airborne strategic deterrent additional thickness distributions to the upper A75-33550 surface of an HACA 61 sub 1-212 airfoil S-3A stall testing and auto-throttle using flow equations and a CDC 7600 digital development/testing computer A75-33613 [NASA-CB-137701] H75-2t674 The S-3A carrier suitability demonstration An investigation on the effect of second-order A75-3361U additional thickness distributions to the upper YF-16 - A rare opportunity flight test program surface of an NACA 64-206 airfoil using flow A75-33615 equations and a CDC 7600 digital computer Stone Spin Shorthand, including: Spin Data Card [HASA-CR-137702] 1175-24675 and sample Criteria Spin Set for testing Theoretical effect of modifications to the upper out-of-control flight surface of two NACA airfoils using smooth A75-33618 polynomial additional thickness distributions Rotor Systems Research Aircraft /BSRA/ which emphasize leading edge profile and which A75-33621 vary quadratically at the trailinq edge Systematic development testing for engine using flow equations and a CDC 7600 computer structural integrity assurance [HASA-CR-137703] 875-21676 A75-31147 PLOH BEGDLATOBS Flight test results of an automatic support system Afterburning regulation concepts on board a YF-12A airplane for ]et engine H75-23587 inlet air control FLOH STABILITY A75-35272 The effects of atmospheric stability, turbulence, A predictive model of wake vortex transport and wind shear on aircraft wake behavior A75-35423 A75-35Q26 Comparison of flight and wind tunnel tests of an Study on the establishment of flow in a wind executive airplane tunnel functioning by induction A75-35806 A75-35811 Analysis of wake vortex flight test data behind a PLOI THEOBY T-33 aircraft Theory of mixing flow of a perfect fluid around an [BASA-CR-137669] H75-23U82 afterbody and a propulsive jet Isolating nozzle afterbody interaction parameters N75-23U93 and size effects: A new approach flight and FLOH TELOCITY wind tunnel tests with A 7 aircraft Search for the final period of decay of the N75-23503 axisymmetric turbulent wake Reynolds number effects on boattail drag of A75-32439 exhaust nozzles from wind tunnel and flight tests Local momentum theory and its application to the N75-23506 rotary wing Flight test for the feasibility evaluation of the [AIAA PAPEB 75-865] A75-33952 Chadwick Electronic Weighing System (CHERS) Calculation of transonic flows using an extended [AD-A007516] H75-23522 integral equation method Correlation of low speed wind tunnel and flight [AIAA PAPEB 75-876] A75-33961 test data for V/STOL aircraft Telocity and rolling-moment measurements in the [NASA-TB-X-62U23] H75-23557 wake of a swept-wing model in the 40 by 80 foot Flight service evaluation of PRD-49/epoxy wind tunnel composite panels in wide-bodied commercial [BASA-TB-I-62414] M75-23I481 transport aircraft PI01DIC CIBCOITS [NASA-CR-132617] N75-21719 Fluidic sensors for turbojet engines Flight load investigation of helicopter external 875-23598 loads FLOOBOSCOEY [AD-A008394] 875-214727 Development of real time high energy X-ray imaging FLO! CHABACTBB1STICS system for use in dynamic fluoroscopy of aero Three dimensional characteristics of turbulent gas turbines wakes behind rotors of axial flow turbomachinery [ASBE PAPEB 75-GT-117] A75-346S4 [ASHE PiPEB 75-G1-1] A75-3U566 A-17 F10TTEB II1LISIS SDBJBCT IBDEI FLOCTBB AIAITSIS A new lightweight fuel control system for The random decrement technique applied to the electrical inputs considering gas turbine TF-16 flight flatter tests engines [AIAA PAPBB 75-776] A75-32663 H75-23599 Hiniiui veight design of the F-15 empennage for PDBL IBJBCIIOH flutter Experimental investigation of a new concept of [AIAA PAPEB 75-777] 175-32664 fuel prevaporization for aircraft engine low The flutter analysis of T-tails emission combustors / [AIAA PAPBB 75-759] A75-32690 [ASHE PAPBB 75-GT-6] A75-34570 The supersonic doublet-lattice nethod - A FOEL FOBPS comparison of tvo approaches based on kernel Pumping system design related to fuel systen functions specifications [AIAA PAPEB 75-760] A75-32691 H75-23600 Oscillatory supersonic lifting surface theory Advanced engine mounted fuel pump technology using a finite element doublet representation H75-23601 [AIAA PAPEB 75-761] A75-32692 FUEL TAHKS Active flutter suppression using trailing-edge and Fuel tank non-nuclear vulnerability test program tab control surfaces [AD-A008531] S75-24728 [AIAA PAPEB 75-822] A75-32697 FDBL TESTS Advances in fan and compressor blade flutter Influence of protective additions on the anti-wear analysis and predictions properties of jet fuels A75-34131 A75-35298 F100 fan stall flutter problem review and solution FOIL SCALE TESTS A75-3141311 Experimental results of full scale air-cooled Rind tunnel test of a flutter suppressor on a turbine tests straight wing [ASBE PAPEB 75-GT-116] A75-34653 [OHBBA, TP HO. 1975-31] 475-35869 FOHCTIOBS (BATBEBATICS) Prediction of unsteady aerodynamic loadings caused Applications of a quadratic extended interior by leading edge and trailing edge control penalty function for structural optimization surface motions in subsonic compressible flow: [AIAA PAPEB 75-764] A75-32654 Computer program description FUSELAGES [NASA-CB-132634] N75-24672 Side forces on unyawed slender inclined FOBGIBG aerodynamic bodies Fabrication of one-piece-forged thin-walled parts A75-33435 having variable cross section Bussian book Detailed experimental and theoretical analysis o£ A75-33150 the aerodynamic interference between lifting FBACTDBB HECBAHICS jets and the fuselage and wing Fracture failure modes in lightweight bearings H75-23509 A75-34140 A fracture mechanics approach to turbine airfoil design [ASBE PAPER 75-GI-79] A75-34628 GALLIDH PHOSPHIDES FBACTOBE STBBHGTB Advanced gallium phosphide L.E.D. displays Impact fracture of composite sandwich structures A75-35284 [AIAA PAPEH 75-718] A75-32673 GAS DYH1BICS Program to improve the fracture toughness and Integral eguations for the calculation of the flow fatigue resistance of aluminum sheet and plate about accelerated slender bodies for B greater, for aircraft applications, voluie 2 egnal, or less than 1 [AD-A003417] H75-23775 A75-35204 FBACTOBES (BATBBIALS) GAS FLOS Computer program to assess impact of fatigue and Free-molecular interference of cylinders with fracture criteria on weight and cost of oblique ray reflection hypersonic flow over transport aircraft parallel cylinders [HASA-CB-132648] H75-24718 A75-33339 FBEE HOLECDLAB F10B GAS IHJECTIOH Free-molecular interference of cylinders with Study on the establishment of flow in a wind oblique ray reflection hypersonic flow over tunnel functioning by induction parallel cylinders A75-35811 A75-33339 GAS TDBBIHE BBGIBBS FBEE VIBBATION naterials for gas turbines review Advances in fan and compressor blade flutter A75-32839 analysis and predictions The dynamics of atmospheric dust particles in A75-34131 aircraft auxiliary power radial inflow turbines FBICTIOH FACTOB [AIAA PAPE8 75-844] A75-33938 Experimental investigation of friction on a plate Design and development of low-cost, self-contained in the flow of a rarefied gas bearing lubrication systems for turbine engines A75-33346 A75-34121 FDEL COBSOHPTIOH Current seal designs and future requirements for Challenge to aviation: Hatching a leaner pterosauer turbine engine seals and bearings improving commercial aircraft design for A75-34123 greater fuel efficiency Low-cycle fatigue and creep analysis of gas [NASA-TB-X-71744] B75-25298 turbine engine components FDBL CONTROL A75-34139 Automatic Test System for Jet Engine Accessories Turbine airfoil life prediction by mission analysis A75-32396 A75-34143 An automated tuneup calibration of jet engine fuel Dynamic simulator for advanced gas turbine engine controls component tests A75-35258 A75-34146 FOBL COBBOSIOI Rotor burst protection program - Statistics on Changes in the properties of hydrogenated fuels aircraft gas turbine engine rotor failures that during prolonged storing occurred in U.S. commercial aviation during 1973 A75-35299 [ASBE PAPEB 75-GT-12] A75-34575 FDE1 FLOB BEGOLATOBS The refracting inlet - A new concept for aircraft A digital controller applied to the limitation of inlet noise suppression reheat combustion roughness [ASBE PAPEB 75-GT-21] A75-34580 N75-23586 Performance development of the Gem turboshaft engine for helicopter application [ASBE PAPEB 75-GT-28] A75-34586 A-18 SUBJECT IHDBI BEAT TBABSFBB COBPFICIEBIS Preliminary study of Ion emission gas turbine GBOOBD BASED COHTBOL combustor with airblast fuel atomizer On the way to tactical aircraft robotics [ASHE PAPEB 75-GT-31] A75-3U588 ground based radar control of F-102 A Excess noise froo gas turbine exhausts A75-32M52 [ASHE PAPEB 75-GT-61] A75-316U GBOOHD EFFECT laboratory testing of controls for aircraft A theoretical analysis for three dimensional ram turbine engines wings in parallel walls [ASHE PAPEB 75-G1-101] A75-3<4643 A75-33127 Development of real time high energy X-ray imaging Hake vortex decay near the ground system for use in dynamic fluoroscopy of aero [AIAA PAPEB 75-882] A75-35173 gas turbines Ground effects for jet lift VTOL [ASHE PAPEB 75-61-117] A75-316511 [BASA-TT-F-16359] B75-23«80 Power plant controls for aero-gas turbine engines GBOOBD EFFECT BACHIHES [AGABD-CP-151] N75-23575 Studies and research on marine hulls working with Beliability specification for gas turbine control natural ground effect systems B75-23175 H75-23581 Ring longitudinal stability criteria The role of computers in future propulsion controls [AD-A007130] B75-23527 H75-23582 Eydroaerodynamic characteristics of a low aspect PBAC: A new aero gas turbine engine control concept ratio delta wing near a screen N75-2358H [AD-A007619] S75-23529 Helicopter engine control: The past 20 years and GBODBD TESTS the next B-1 - The road to first flight N75-23585 A75-32455 Afterburning regulation concepts GBODBD BIBD N75-23587 Surface wind speed range as a function of time Equilibrium performance analysis of gas turbine interval and mean wind speed engines using influence coefficient techniques A75-35113 H75-23592 GOBS (OBDBAHCB) Generalized dynamic engine simulation techniques Theoretical downwash velocities about the AH-1G for the digital computers helicopter at hover and 110 knots B75-23593 [AD-A008339] B75-21693 Total powerplant simulation COST LOADS H75-23591I A study of self-similarity in boundary layer Dse of simulation in the design, development and turbulence and its relevance to aircraft design testing of power plant control systems and operation H75-23595 A75-35U19 Temperature measurement foe advanced gas turbine GDSTS controls Surface wind speed range as a function of time H75-23597 interval and mean wind speed Fluidic sensors for turbojet engines A75-35U13 ^ N75-23598 A new lightweight fuel control system for H electrical inputs considering gas turbine engines B-54 BELICOPTEB H75-23599 Flight load investigation of helicopter external Pumping system design related to fuel system loads specifications [AD-AOOSSgu] H75-24727 N75-23600 HAHDBOOKS Advanced engine mounted fuel pump technology Supercritical wing sections II: A handbook N75-23601 numerical computations GAS TtJBBINES A75-3U975 Control of gas turbine stator blade vibrations by HABBOBIC BOTIOB means of enamel coatings Finite element analysis of unsteady transonic flow A75-3M116 (AIAA PAPER 75-875] A75-33960 Design and analysis of a ceramic stator vane H1BBOBIC OSCIILATIOB [ASHE PAPEH 75-GT-100] A75-31612 A calculation method for unsteady subsonic flow GEABS about harnonically oscillating wing-body System identification of a complex structure configurations helicopter gearbox dynamics from shake test data (AIAA PAPER 75-86U] A75-33951 [AIAA PAPEB 75-809] A75-32705 BEAD-OP DISPLAYS GENERAL AVIATIOB AIBCBAFT Velocity vector - The logical solution Why so few all new General Aviation aircraft aircraft guidance head-up displays design decision making factors A75-32110 A75-33619 HOD - An important new aid tp the L.S.O Head Preliminary results from pilot aviation weather Op Display for Landing Signal Officer self-briefing experiments A75-33620 A75-35128 A holographic visor helmet-mounted display system Comparison of flight and wind tunnel tests of an A75-35283 executive airplane BEAI BESISTABT ALLOTS A75-35806 Directionally solidified lamellar eutectic Low-speed aerodynamic characteristics of a snperalloys by edge-defined, film-fed growth 13-percent thick airfoil section designed for including tensile tests general aviation applications [BASA-CB-131808] H75-2U897 [NASA-TH-X-72697] B75-2M678 BEAT SHIBLDIBG GOVBBHHBBT PBOCOBBBIBT Hypersonic wing test structure design, analysis, B-1 airborne strategic deterrent and fabrication A75-33550 [AIAA PAPEB 75-785] A75-32670 GOVBBBBEBT/IBDOSfBT BELATIOHS Analysis of rotor fragment impact on ballistic Problems of federal and state court jurisdiction fabric engine burst containment shields and venue in products liability litigation - A75-311U1 Defendants viewpoint aviational products BEAT TBABSPBB A75-33565 Experimental study of heat transfer during flow Air transportation of radioactive materials around uncaibered delta wings with blunted edges A75-33568 [AD-A007316] 875-2352* Consequential and special damages - Tempest in the BEAT TBABSFBB COBFPICIBBTS tariff liability and clan rules for Unsteady boundary layers over rotating blades handling air freight (ASHE PAPEB 75-GT-6I4] A75-3«617 A75-33569 A-19 HEAVIHG SDBJECT INDEX HEAVING Evaluation of bead-stiffened metal panels for Dynamic heave-pitch analysis of air cushion hypersonic aircraft and space systems design landing systems [AIAA PAPER 75-815] A75-32701 [NASA-CR-2530] N75-21721 Analysis of various descent trajectories for a HELICOPTER COHTBOL hypersonic-cruise, cold-wall research airplane Recent advances in in-flight simulator technology [NASA-TN-D-7860] N75-21673 475-33187 HYPERSONIC COHBUSTIOH HELICOPTBB DESIGH Hypersonic research engine project. Phase 2: Bell Helicopter/NASA/Army XV-15 status report Some combustor test results of NASA A75-33617 aerothemodynamic integration model / Rotor Systems Research Aircraft /ESRA/ [NASA-CH-132525] - ' H75-21738 A75-33621 HYPERSONIC FLO! ' Summary of HIT research on dynamic stall and Free-molecular interference of cylinders with blade-vortex interaction, 1971 - 1971 oblique ray reflection hypersonic flow over [AD-A008091] N75-21689 parallel cylinders Heavy lift helicopter; cargo handling ATC program. A75-33339 Volume 2: Fabrication of test hardware and HYPERSONIC VEHICLES fixtures integrated test rig Hypersonic research engine project, phase 2. [AD-A007211] N75-21721 Preliminary report on the performance of the KAflex drive shaft coupling for HH-1 helicopter. HBE/4IH at Hach 6 Design refinement [NAS4-CR-132538] B75-21712 [AD-A008365] N75-21731 HELICOPTER ENGINES High-speed rotor dynamics - An assessment of current technology for small tarboshaft engines IBAGB INTENSIFIERS A75-3U127 Development of real time high energy X-ray imaging Performance development of the Gem turboshaft engine system for use in dynamic fluoroscopy of aero for helicopter application gas turbines [ASHE PAPER 75-GT-28] A75-34586 [ASBE PAPEB 75-GT-117] 475-31651 Helicopter engine control: The past 20 years and IHPACT DAHAGE the next Impact fracture of composite sandwich structures N75-23585 [AIAA PAPER 75-718] 475-32673 HELICOPTER FBOPELLEB DRIVE IHPACT PfiEDICTIOH System identification of a complex structure Analysis of rotor fragment impact on ballistic helicopter gearbox dynamics from shake test data fabric engine burst containment shields [AIAA PAPER 75-809] 475-32705 475-31111 HBLICOPTBB WAKES IHPACT RESISTANCE Prediction of rotor wake induced flow along the Development of impact resistant boron/aluminum rocket trajectories of an Army AH-1G helicopter composites for turbojet engine fan blades [AD-A007878] 1175-23528 [NASA-CR-131770] N75-21717 HE1ICOPTBBS IHPEDANCB BATCHING Flight test for the feasibility evaluation of the Small antennas fractional wavelength design Chadwick Electronic Weighing System (CHEWS) for wideband applications [AD-A007516] N75-23522 A75-35827 A crashworthy armored pilot seat for helicopters INCOBPBESSIBLE FLOS [AD-A007551 ] »75-23511 Dse of numerically generated body-fitted A study of helicopter interior noise reduction coordinate systems for solution of the [NASA-TH-X-72655] S75-23556 Navier-Stokes equations Research on helicopter rotor noise A75-31186 [AD-A007261] N75-23608 A finite-element method for lifting surfaces in The development of experimental techniques for the steady incompressible subsonic flow study of helicopter rotor noise [SASA-CH-112811] N75-23177 [NASA-CR-137681] H75-23611 INFINITE SPAN WINGS Theoretical downwash velocities about the AH-1G Studies and research on marine hulls working with helicopter at hover and 110 knots natural ground effect [AD-A008339] 1175-21693 N75-23175 HELHETS INFRARED IHAGEBI A holographic visor helmet-mounted display system Passive infrared imaging systems 475-35283 475-31881 HIGH SIBENGTH ALLOYS INFHABED SCANNERS Engineering titanium alloys Russian book Passive infrared imaging systems 175-35519 475-31881 HIGH TEBPEBATDRE GASES INFRARED SPECTBA Jet-induced thermal effects for VIOL aircraft External fins and ejector action for reducing the [ASHE PAPER 75-GT-96] 475-31638 infrared emission of engine exhaust ducting HIGH TEHPBBAIDBE TESTS [NASA-TB-X-3212] S75-25091 High temperature tests of a JP-5 type fuel INLET PBESSDBE [AD-4007662] H75-23603 Review of hammershock pressures in aircraft inlets HOLOGBAPHT 475-31115 A holographic visor helmet-mounted display system Experiments concerning the response of supersonic 475-35283 nozzles to fluctuating inlet conditions Nondestructive holographic techniques for noise measurement structures inspection [ASHE PAPEB 75-GT-10] A75-31597 [4D-4007850] N75-23916 INSTBDHENT EBBOBS HOIETCOHB STRUCTURES FAA lightning protection study: Lightning The effect of water path variations on ultrasonic protection requirements for AIL type 55 K through-transmission sensitivity for instrument landing system adhesively bonded aircraft honeycomb structures [4D-A008931] N75-23530 475-31203 IHSTBOHENT LAHDIHG SYSTBHS BYDROGBS4TIOI FAA lightning protection study: Lightning Changes in the properties of hydrogenated fuels protection requirements for AIL type 55 K during prolonged storing instrument landing system A75-35299 [AD-A008931] N75-23530 HYPERSONIC AIRCRAFT INTAKE SYSTBBS Hypersonic wing test structure design, analysis, The measurement of the transonic spillage drag of and fabrication a supersonic intake [AIAA PAPER 75-785] A75-32670 N75-23188 A-20 SUBJECT IIDBZ JBt THSOST Temperature measurement for advanced gas turbine Droplet diameter and size distribution of JP-4 controls fuel injected into a subsonic airstreai H75-23597 [AD-A007687] 175-24192 IHTEGBAL EOOHIOIS Plow characteristics of various swirl-can lodule Calcolation of transonic flows nsing an extended designs exhaust flow simulation, flow integral equation nethod characteristics, and combustion efficiency of [AIAA PAPEB 75-876] 175-33961 jet engine fuels Integral equations for the calculation of the flov [BASA-TH-X-3236] B75-24740 about accelerated slender bodies for B greater, JBT BB6IBBS equal, or less than 1 Automatic Test System for Jet Engine Accessories A75-35204 A75-32396 IITBBFBBEICE DEIS Identification of systems by means of adaptive model Subsonic base and boattail drag, an analytical application to jet engines approach A75-32073 H75-23492 Dynamic response of visco'ns-daaped multi-shaft jet The subsonic base drag of cylindrical twin-jet and engines single-jet afterbodies A75-34128 H75-23498 Design of fabricated static structures for long IBTEBHATIOIAL COOPEBATIOH cyclic life International and U.S. design proposals for a A75-34142 microwave landing system in automated tuneup calibration of jet engine fuel 475-34536 controls IHVISCID HOI A75-35258 Computation of nonegnilibnum three-dimensional Flight test results of an automatic support system inviscid flow over blunt-nosed bodies flying at on board a IF-12A airplane for jet engine supersonic speeds inlet air control [Alii PIPES 75-835] A75-33931 A75-35272 Inviscid to turbulent transition of trailing The economic advantages of low and high vortices temperature anti corrosion coatings on jet [AIAA PAPER 75-883] i75-33965 engine parts - A case history Theory of mixing flov of a perfect fluid around an A75-35449 afterbody and a propulsive jet Interaction of jets of GE CF6-50 reactors with the H75-23493 wing cellules of the airbus during cruise - Prediction of the optunnn location of a nacelle Rind-tnnnel simulation shaped body on the wing of a wing-body A75-35808 configuration by inviscid flow analysis Full scale upper surface blown flap noise 1175-23510 [HASA-TH-X-71708] B75-23569 101 IBPACT The 727 airplane target thrust reverser static Ion vapor deposited aluminum improves structure performance model test for refanned JT8D engines durability airframe corrosion protective [HASA-CB-134652] B75-24737 coatings Exhaust pollutant emissions from swirl-can [AIAA PAPEB 75-807] A75-32680 combnstor module arrays at parametric test conditions [H1SA-TII-I-3237] H75-24746 JBT EXBAUST JBT AIRCBAFT Effect of simulated forward flight on subsonic jet The notion of wake vortices in the terminal exhaust noise environment [Alii PIPER 75-869] i75-33956 A75-35424 Jet interference of a podded engine installation The 727 airplane target thrust reverser static at cruise conditions performance model test for refanned JT8D engines H75-23490 [NASA-CH-134652] B75-24737 JET FLAPS JBT AIBCBAFT WOISE Low speed wind tunnel tests on a one-seventh scale Effect of simulated forward flight on subsonic jet model of the H.126 jet flap aircraft exhaust noise [HiSi-TB-X-62433] H75-24722 [AIAi PAPEB 75-869] A75-33956 JET FLOB Wind tunnel measurements of forward speed effects Theory of mixing flow of a perfect fluid around an on jet noise from suppressor nozzles and afterbody and a propulsive jet comparison with flight test data B75-23493 [AIAA PAPEB 75-870] A75-33957 JBT IHPIHGEBBHT Experiments concerning the response of supersonic Jet-induced thermal effects for VIOL aircraft nozzles to fluctuating inlet conditions [ASBE PAPEB 75-GT-96] A75-34638 noise measurement JBT LIFT [ASBE PAPER 75-GT-40] A75-34597 Detailed experimental and theoretical analysis of Sound and vibration measurements for Concorde the aerodynamic interference between lifting supersonic transport and subsonic jet aircraft jets and the fuselage and wing [PB-238748/8] ' H75-24436 B75-23509 Airport noise reduction forecast. Volume 1: JET HIIIBG FLOI Summary report for 23 airports Concurrent mixing and diffusion in three dimensions [PB-239387/4] N75-24771 ejector performance Airport noise reduction forecast. Volume 2: KEF [AIAA PAPEB 75-873] A75-35170 computer program description and user's manual JET PBOPDLSIOI [PB-239388/2] N75- 24772 Twin jet exhaust system test techniques JET COBTEOL integrating airframe and propulsion system for An air intake control system for a supersonic wind tunnel models fighter aircraft H75-23500 N75-23589 Airframe: Engine interaction for engine JBT BHGIHB FUELS configurations mounted above the wing. Part 2: Influence of protective additions on the anti-wear Engine jet simulation problems in wind tunnel properties of jet fuels tests A75-35298 875-23512 Changes in the properties of hydrogenated fuels JET TBBUST during prolonged storing Thrust/drag analysis for a front fan nacelle A75-35299 having two separate co-axial exhaust streams High tenperature tests of a JP-5 type fuel [ABC-CP-1311] 875-23574 [AD-A007662] H75-23603 Development of high stability fuel [AD-A007574] 1175-23604 A-21 K11H1I FILTBBS SOBJECI IBDEI LEGAL LIABILITY Problems of federal and state court jurisdiction and venue in products liability litigation - KALBA1 PILTEBS Defendants viewpoint aviational products A Kalian filter for the stoland system A75-33565 [BASA-CB-137668] H75-23543 Consequential and special damages - Tempest in the KBBBBL FOBCIIOBS tariff liability and claim rules ,for The supersonic doublet-lattice method - 1 handling air freight coiparison of two approaches based on kernel A75-33569 functions LIFE (DDBABIIITI) [AIAA PAPEE 75-760] 175-32691 Increasing the wear resistance of aircraft parts KOTIA-JODKOBSKI COBDIIIOH [HASA-TT-F-15759] B75-24723 Trailing edge flovs over tnrbomachine blades and LIFT the Kutta-Joukowsky condition S-3A stall testing and auto-throttle [ASHB PAPEB 75-GT-94] A75-34636 development/testing, A75-33613 The drag and oscillating transverse force on vibrating cylinders due to steady fluid flow LiMIBAB BOUBDAB? 1AYBB A75-35765 Computational procedure for three-dimensional Ground effects for jet lift VIOL boundary layers on aircraft and aerospace vehicles [BASA-TT-F-16359] 875-23*80 A75-34190 Influence of a plain flap with a blunt, notched Stud; of the interaction and three-dimensional trailing edge on the lift of a rectangular wing separation effects of a boundary layer in a [ESBO-TT-147] B75-24685 supersonic laminar regime French book LIFT ADGHEHTATIOH A75-35450 Maximum lift of upper surface blowing STOL LANIHAB FLO! aircraft with swept wings Use of numerically generated body-fitted [AIAA PAPEB 75-868] A75-33955 coordinate systems for solution of the An inverse method for the design of multielement Navier-Stokes eguations high-lift systems potential flow inversion A75-34186 [AIAA PAPEB 75-879] A75-33963 LAHIBATES LIFT FABS Mechanics of composite materials Book Lift-fan characteristics selection for 1980-85 A75-32463 V/STOL carrier onboard delivery aircraft Analytical displacements and vibrations of [ASHE PAPEB 75-GT-98] A75-34640 cantilevered unsymmetric fiber composite laminates LIFTIHG BODIES [AIAA PAPEB 75-757] A75-32688 Subsonic transient lifting surface aerodynamics Structural response of fiber conposite fan blades [AIAA PAPEB 75-758] A75-32689 [ASHE PAPEB 75-GT-78] A75-34627 Oscillatory supersonic lifting surface theory LiSDIBG AIDS using a finite element doublet representation HDD - An important new aid to the L.S.O Head [AIAA PAPEB 75-761] A75-32692 Dp Display for Landing Signal Officer A theoretical analysis for three dimensional ram 175-33620 wings in parallel walls liBDIBG GBAB A75-33427 The effect of chine tires on nose gear water-spray Theoretical study of lift-generated vortex wakes characteristics of a twin engine airplane designed to avoid rollup [BASA-TH-X-72695] H75-23555 A75-33485 LATEBAL STABILIfT Aerodynamics of lifting and propulsive systems in Side forces on unyawed slender inclined a periodically functioning regime - Optimization aerodynamic bodies of their performance A75-33135 A75-35815 LATTICES (BATBEBATICS) A finite-element method for lifting surfaces in The supersonic doublet-lattice method - A steady incompressible subsonic flow comparison of two approaches based on kernel [NASA-CB-142811] B75-23477 functions Analysis of transonic flow about lifting wing-body [AIAA PAPEB 75-760] A75-32691 configurations LAV (JDBISPEDDEHCE) [BASA-TB-B-440] H75-24681 Problems of federal and state court jurisdiction LIFTIHG BOTOBS and venue in products liability litigation - Dynamic and aeroelastic problems of stop-rotors Defendants viewpoint aviational products and their analytical treatment. Part 2: A75-33565 Analytical equations and solutions V/STOL Conseguential and special damages - Tempest in the aircraft tariff liability and claim rules for [ESBO-TT-145-PT-2] B75-24683 handling air freight LIGBT AIBCBAFT A75-33569 Besponse of a light aircraft to a thermal exhaust LEADIBG BDGB SLATS plume Effect of canard position and wing leading-edge A75-35403 flap deflection on wing buffet at transonic speeds Light aircraft lift, drag, and moment prediction: [S&SA-TH-X-72681 ] H75-23559 A review and analysis LEADIBG EDGES [NASA-CB-2523] 1175-24677 Subscale, hydrogen-burning, LIGBT EMITTING DIODES airframe-integrated-scramjet: Experimental and Advanced gallium phosphide L.E.D. displays theoretical evaluation of a water cooled strut A75-35284 airframe-integrated-scramjet: Experimental LIGHT TBABSHISSIOB leading edge Transmissivity of light - One of the quantities [HASA-TM-X-72682] N75-23885 usable in the diagnostics of oil in a motor Theoretical effect of modifications to the upper A75-32472 surface of two NACA airfoils using smooth LIGHTBIBG polynomial additional thickness distributions FAA lightning protection study: Lightning which emphasize leading edge profile and which protection requirements for AIL type 55 K vary guadratically at the trailing edge instrument landing system using flow equations and a CDC 7600 computer [AD-A008931] N75-23530 [HASA-CR-137703] N75-21676 LIQDID SLOSBIHG LEAS JET AIECRAFT Batural oscillations of liquid in a horizontal Shuttle spacelab simulation using a Lear jet container with symmetric double-connected cross aircraft: Bissicn no. 3 (ASSESS program) section [NiSA-TH-X-62410 ] B75-24760 [AD-A007312] H75-23906 A-22 SOBJECT IBDET. HECBABICAL PBOPBBTIES LOiD DISIBIBOTIOB (FOBCBS) LOGS Development and testing under static conditions of Fatigue properties of aircraft lugs with a B-A1 load transfer element interference fit [AIAA P1PEB 75-788) A75-32675 [TAE-2U3] H75-24031 LOADS (FOBCBS) Calculation of the reinforced thin-walled M construction by the method of the final element [AD-A007307] H75-23560 BAGSETOBIDBODYBAHICS Flight load investigation of helicopter external The problem of diffraction of a strong loads magnetogasdynamic shock wave by a wedge [AD-A00839U] B75-24727 A75-32518 LOHGITODIBAL COSTEOL 81IHTAIHABILITY Calculation of static longitudinal aerodynamic Reliability and maintainability allocation for characteristics of STOL aircraft with upper avionic maintenance optimization surface blovn flaps A75-35252 [HASA-CB-137646] H75-23<483 Automatic test eguipment for S-3A support LOHGITDDIHAL STABILITI A75-35279 Calculation of static longitudinal aerodynanic HAH HACHIHE STSTEHS characteristics of STOI aircraft Kith upper Air traffic controllers' operative effectiveness surface blovn flaps under HAS environments [ NASA-CB-1376146] B75-23483 A75-3M539 Bing longitudinal stability criteria BAHUAL COHTBOL [AD-A007030] 875-23527 Simulator evaluation of manually flown curved HIS The influence of short springs on longitudinal approaches Microwave Landing System static stability A75-3U535 [CBAHFIELD-AEBO-29] H75-23607 HABOFACTOBIBG LOBAB C Influences of manufacturing tolerances and surface Loran-C compared with other navigation aids in roughness of blades on the performance of turbines meeting future Canadian needs [ASME PAPEB 75-GT-35] A75-34592 A75-35796 HABIBE TBCBHOLOGI LOB ASPECT BATIO Studies and research on marine hulls working with Account of shearing strain during the calculation natural ground effect of the oscillaticns of Ion aspect-ratio wing by H75-23475 the method of polynomials HAS3 FLOR [AD-A007397] H75-23518 A model for the dynamics of a separation bubble LOR ASPECT BATIO RUGS used to analyze control-surface buzz and dynamic Applications of a quadratic extended interior stall penalty function for structural optimization [AIAA PAPEB 75-867] A75-3395U [AIAA PAPEB 75-76»] A75-32654 HATEBIALS HABDLIBG LOR COST Heavy lift helicopter; cargo handling 4TC program. Design and development of low-cost, self-contained Volume 2: Fabrication of test hardware and bearing lubrication systems for turbine engines fixtures integrated test rig A75-3<|121 [AD-A0072U4] B75-2«72» LOR LEVEL TORBDLESCE HATEBIALS SCIBBCE Aeronautical requirements and procedure for Materials for gas turbines review low-level turbulence and wind shear reporting A75-32839 A75-35U14 HATBEHATICAL HODELS LOR SPEED A model for the dynamics of a separation bubble Low-speed aerodynamic characteristics of a used to analyze control-surface buzz and dynamic 13-percent thick airfoil section designed for stall general aviation applications [AIAA PiPEB 75-867] A75-3395U [HASA-TH-X-72697] H75-24678 Surge and rotating stall in axial flow LOR SPEED RIBD TOBBELS compressors. I - Theoretical compression system Bind tunnel tests for the determination of the model behavior of aircraft external loads which are [ASHE PAPEB 75-GT-9] A75-31573 dropped A study of self-similarity in boundary layer A75-35098 turbulence and its relevance to aircraft design Low speed wind tunnel tests on a one-seventh scale and operation model of the B.126 jet flap aircraft A75-35419 [SAS4-TH-X-621I33] H75-21722 A predictive model of wake vortex transport LOR VISIBILITY A75-35423 Lidar technigues for measuring slant visibility On the adequate model for aircraft parameter for aircraft landing operations estimation parameterization of aircraft A75-35»3t models using mathematical models LOBRICABT TESTS [CBAHFIELD-AEBO-28] H75-2U755 Diagnostics of jet aero-engines by means of HAIBIX HETBODS spectral analysis of lubricating oil Formation of flexibility matrices of a structure A75-32U70 based on known yields at arbitrary points Transnissivity of light - One of the quantities A75-32995 usable in the diagnostics of oil in a motor HEASDBIHG IBSTBDHEBTS A75-32472 The state of the art in oil quality gaging on OS LOBBICATIHG OILS military and commercial aircraft Diagnostics of jet aero-engines by means of [AD-A007682] B75-23565 spectral analysis of lubricating oil HECBABICAL DEVICES A75-32170 Control system requirements dictated by Transmissivity of light - One of the quantities optimization of engine operation usable in the diagnostics of oil in a motor B75-23579 A75-32472 HECBABICAL PBOPEBTIBS Application of thin-layer chromatography for Mechanics of composite materials Book determining the wearing capacity of additives A75-32«63 contained in petroleum-based aviation oils Crippling/column buckling analysis and test of A75-35300 graphite/epoxy-stiffened panels The state of the art in oil quality gaging on OS [AIAA PAPEB 75-753] A75-3268* military and commercial aircraft Corrosion control in naval aircraft [AD-A007682] M75-23565 A75-32830 LDBBICATIOB SYSTEMS Materials for gas turbines review Design and development of low-cost, self-contained A75-32839 bearing lubrication systems for turbine engines Chemical milling review A75-3H121 A75-32810 A-23 BETAL PIBISHIHG SUBJECT IHDEI Titanium casting - Industrial development - BISSILE LADHCHEBS ECODODIC aspects An estimate of the effect of multiple ejection A75-35159 rack flexibility on six degree of freedom store Engineering titanium alloys Russian book ejection conditions 475-35519 [AD-A008329] H75-24734 Advanced beaded and tubular structural panels. BISSILB TRAJECTORIES Volume 2: Fabrication Prediction of rotor wake induced flow along the [NASA-CR-132482] N75-24717 rocket trajectories of an Army AH-1G helicopter BBTAL FIHISHISG [AD-A007878] H75-23528 Surface finishing particularly for use in HISSIOB PLABBIHG smoothing irregularities on aluminum aircraft Shuttle spacelab simulation using a Lear jet wings aircraft: Mission no. 3 (ASSESS program) [HASA-CASE-BSC-12631-1 ] H75-23476 [HASA-TB-X-62410] S75-24760 BETAL HATBIX COHPOSITES BOBEBTDB THBORI Development and testing under static conditions of Local Bomentum theory and its application to the a B-A1 load transfer element rotary wing [AIAA PAPEB 75-788] A75-32675 [AIAA PAPEB 75-865] A75-33952 Boron/aluminum for advanced technology aircraft BBCA AIRCRAFT cost and weight advantages Variable geometry today latest swing wing [AIAA PAPER 75-790] A75-33762 aircraft Developoeat of impact resistant boron/aluminum A75-33447 composites for turbojet engine fan blades BDLTIPLEIIBG [NASA-CB-13lt770] N75-24747 The age of the BPV data bus or the data bus comes BETAL PLATES of age airborne coaputer test systems Stress concentration in an expanded plate with A75-35261 opening reinforced by central belt [AD-A007672] H75-24044 BETAL SHEETS N Determination of surface roughness of materials BACELLES A75-33331 The influence of nacelle afterbody shape on BBTAL SURFACES airplane drag Corrosion control in naval aircraft H75-23505 A75-32830 Prediction of the optimum location of a nacelle Determination of surface roughness of materials shaped body on the wing of a wing-body A75-33331 configuration by inviscid flow analysis BBTEOBOLOGICAL IBSTBDHEHTS B75-23510 Preliminary results from pilot aviation weather Conceptual design study of advanced acoustic self-briefing experiments composite nacelle for achieving reductions A75-35428 in community noise and operating expense BETHOD OF CHARACTERISTICS [BASA-CB-1326U9] 1175-23568 Spatial supersonic flow through annular cascades Thrust/drag analysis for a front fan nacelle [ASBE PAPER 75-GT-113] A75-34650 having two separate co-axial exhaust streams HICBOIAVE LAHDIHG STSTBBS [ABC-CP-1311] N75-23574 Simulator evaluation of manually flown curved BLS Aircraft engine nacelle fire test simulator approaches Bacrowave Landing Systen [AD-A007853] H75-23617 A75-34535 BAVIBB-STOKBS EQOATIOH International and U.S. design proposals for a A rigorous solution of the Navier-Stokes eguations microwave landing system for unsteady viscous flow at high Reynolds A75-34536 numbers around oscillating airfoils Involving the expert and aviation community in the [AIAA PAPEB 75-863] A75-33950 decision making structure of the U.S. BLS program Dse of numerically generated body-fitted Bicrowave Landing System coordinate systems for solution of the A75-34537 Havier-Stokes eguations BILITART AIRCRAFT A75-31186 Rescue measures in the case of accidents of the BAVIGATIOB AIDS AK-12 aircraft Loran-C compared with other navigation aids in A75-32527 meeting future Canadian needs New Air Force requirements for structural safety, A75-35796 durability and life management A Kalman filter for the Stoland system [AIAA PAPER 75-781] A75-32668 [HASA-CB-137668] B75-235 A-24 SUBJECT IHDBI PBBFOBBAICB IBSI3 Conceptual design study of advanced acoustic OBEB1TOB PBBPOBH1HCB composite nacelle for achieving redactions Air traffic controllers' operative effectiveness in community noise and operating expense under BAS environments [HASA-CB-132609] H75-23568 A75-34539 HASA cefan prograi status for noise redaction OPTICAL BADAB of JT8D tarbofan engine lidar techniques for measuring slant visibility [HASA-TH-X-71705] B75-23570 for aircraft landing operations Civil aviation studies and interagency A75-35434 coordinating organizations, voluie 1 OPTIBIZATIOB aircraft noise redaction Applications of a quadratic extended interior [PB-2 39344/5] H75-211186 penalty function for structural optimization Civil aviation studies and interagency [AIAA PAPEB 75-764] 475-32651 coordinating organizations, volnie 2: Appendices Reliability and maintainability allocation for aircraft noise redaction avionic maintenance optimization [PB-239345/2] B75-24187 A75-35252 The ont of service gqest pilot evaluation of the Aerodynamics of lifting and propulsive systems in two-segment noise abatement approach in the a periodically functioning regime - Optimization Boeing B727-200 of their performance [BASA-CB-137625] B75-24696 A75-35815 Airport noise redaction forecast. Volume 1: Control design considerations for variable Sninary report for 23 airports geometry engines [PB-239387/4] B75-2U771 B75-23583 Airport noise redaction forecast. volume 2: SEF OSCIUATIRG CILIBDBBS computer prograa description and user's manual The drag and oscillating transverse force on [PB-239388/2] B75-2U772 vibrating cylinders due to steady fluid flow HOIDESTBOCTIVB TESTS A75-35765 Nondestructive holographic techniques for OSCIIIATIBG FLO! structures inspection Dnsteady behavior of transonic flows shock [AD-A007850] B75-23946 induced oscillation Evaluation of the reliability and sensitivity of [BPIS-BITT-59] B75-23516 DDT methods for titanium alloys. Volume 2 OSCIILATIOB DAHPEBS [AD-A001604] H75-2<4923 Rind tunnel test of a flutter suppressor on a HOHBQOILIBBIOH FLOI straight wing Computation of non equilibrium three-dimensional [OHEBA, TP HO. 1975-31] A75-35869 inviscid flow over blunt-nosed bodies flying at supersonic speeds [AIAA PAPEB 75-835] A75-33931 BOSS COHES PAHEL PLDTTBB An experimental investigation of the aerodynamic The supersonic doublet-lattice method - A characteristics of several nose nounted canard comparison of two approaches based on kernel configurations at supersonic Bach numbers functions [AD-A007793] H75-23526 [AIAA PAPEB 75-760] A75-32691 HOSE REBELS Aeroelastic panel optimization with aerodynamic The effect of chine tires on nose gear water-spray damping characteristics of a twin engine airplane A75-33488 [HASA-TK-I-72695] H75-23555 PABELS HOZZLB FLOI Advanced beaded and tubular structural panels. Isolating nozzle afterbody interaction parameters Volume 2: Fabrication and size effects: A new approach flight and [HASA-CB-132482] H75-21717 Kind tunnel tests with A 7 aircraft PABABOLIC DIFPEBEBTIAL EQOATIOBS H75-23503 Extension of the parabolic method for the Airframe/propulsion system flow field interference transonic flow. I - Steady flow. II - Dnsteady and the effect on air intake and exhaust nozzle flow performance A75-35215 N75-23508 PABACHDTBS BOZZLB GEOMETRY Emergency ejection, sequence of operation On some problems encountered in a theoretical [AD-A007470] B75-23539 study of the external flow over a nozzle PABAHBTBBIZiTIOB configuration in transonic flight On the adequate model for aircraft parameter N75-23499 estimation parameterization of aircraft BOHERICAL AHALISIS models using mathematical models Blade vibration - Some key elements in design [CBAKFIELD-AEBO-28] H75-24755 verification CABTICLE SIZE DISIBIBDTIOH A75-31132 Droplet diameter and size distribution of JP-4 Calculation of the separated flow at a fuel injected into a subsonic airstream thin-section wing of finite span [AD-A007687] N75-24192 A75-34262 PARTICLE TBAJBCTOBIBS Supercritical wing sections II: A handbook The dynamics of atmospheric dust particles in numerical computations aircraft auxiliary power radial inflow turbines A75-34975 [AIAA PAPEB 75-84U] A75-33938 NOHBBICAL IBTEGBATIOH PASSBBGEB AIBCBAFT Integrated potential formulation of unsteady Comparison of flight and wind tunnel tests of an supersonic aerodynamics for interacting wings executive airplane [AIAA PAPEB 75-762] A75-32693 A75-35806 BDBBBICAL BBATBEB FOBECASTIHG PilLOADS A predictive model of wake vortex transport Rind tunnel tests for the determination of the A75-35423 behavior of aircraft external loads which are dropped A75-35098 PEBFOBBABCE PBEDICTIOB OHBOABD EQOIPHEHT Total powerplant simulation Automatic test equipment for S-3A support H75-23594 A75-35279 PEBFOBHAHCE TESTS OPBBiTIOBAL FBOBLEHS Performance development of the Gen turboshaft engine Aircraft turbulence encounters during commercial for helicopter application operations in the vicinity of thunderstorms [ASHE PAPEB 75-GT-28] A75-34586 A75-35418 Influences of manufacturing tolerances and surface roughness of blades on the performance of turbines [ASHE PAPEB 75-GT-35] A75-34592 A-25 PILOT PBBPOBH1ICB SOBJBCT IIDBI PHOT PBBPOBHAICB PBBSSOBB PULSES TF-16 - A rare opportunity flight test program Sound radiation from a bounded thin inhomogeneoas A75-33615 plate reinforced with s ribs and driven by Simulator evaluation of manually flown curved MLS boundary-layer pressure fluctuations approaches Microwave Landing Systen A75-33117 A75-31535 PBBSSOBB BBOOCTIOB Preliminary results from pilot aviation weather An airframe manufacturer's requirements for future self-briefing experiments propulsion controls A75-35128 875-23578 PIPES (TDBBS) PBESSOBE BBGOLATOBS Fabrication of one-piece-forged thin-vailed parts PBAC: A new aero gas turbine engine control concept having variable cross section Russian book B75-23581 175-33150 PBODOCT DEVELOPMENT PITCH (IHCLIBATIOI) Ihy so few all new General Aviation aircraft Dynanic heave-pitch analysis of air cushion design decision making factors landing systems A75-33619 [NASA-CB-2530] 875-21721 Development of impact resistant boron/aluminum PI1CHIBG HOBBHTS composites for turbojet engine fan blades Aerodynanic characteristics of an azisymmetric [HASA-CB-131770] B75-21717 body undergoing a uniform pitching motion PROJECTILE CBATERIB6 [AIAA PAPEE 75-838] A75-33933 Impact fracture of composite sandwich structures PLASBA-ELECTHOBAGRETIC IBTERACTIOB [AIAA PAPER 75-718] A75-32673 A means of dynamic control of radar reflectivity' PROJECTILES of an antenna or other object by means of a Besponse of aircraft structural compartments to gaseous plasma shroud blast pressures and fragments from high A75-31851 explosive projectiles PLASTIC AIBCBAPT S1BDCTOBBS [AIAA PAPEB 75-751] A75-32652 Impact fracture of composite sandwich structures PBOPBLLABT ADDITIVES [Alii PAPBB 75-718] 175-32673 Influence of protective additions on the anti-wear PLASTIC DEFOBBATIOB properties of jet fuels Calculation of loads and deformations of sweptback A75-35298 wing with the aid of mechanical analog instruments PBOPELLABT STOBAGE [AD-A007308] H75-23525 Changes in the properties of hydrogenated fuels PHBDHATIC COBTBOL during prolonged storing Control system requirements dictated by A75-35299 optimization of engine operation PBOPELLEB DBIVE B75-23579 Improvement of propeller static thrust estimation POLYIMIDB BESIHS [BASA-CB-132680] 875-23567 Structural response of fiber composite fan blades PBOPELLEB EFFICIENCY [ASHE PAPEB 75-GT-78] A75-31627 Improvement of propeller static thrust estimation POLYHOBIALS [BASA-CB-132680] B75-23567 Account of shearing strain during the calculation PBOPOLSIOB of the oscillations of low aspect-ratio wing by Accounting of aerodynamic forces on the method of polynomials airframe/propulsion systems for designing [AD-A007397] H75-23518 military aircraft POBOOS BALLS B75-23507 Propagating stall in compressors with porous walls PBOPOLSIOB SYSTBB COBFIGOBATIOBS [ASME PAPER 75-61-59] A75-31612 Development of a high-heat-release combustor for POTEBTIAL FLOR the F100 gas turbine An inverse method for the design of multielement [ASHE PAPEB 75-GT-86] A75-31631 high-lift systems potential flow inversion A design study of a fan augmented ramjet [AIAA PAPER 75-879] A75-33963 [ASME PAPEB 75-GT-97] A75-31639 Transonic potential flow calculations using Advanced engine mounted fuel pump technology conservation form for shock-free airfoils N7 5-23601 A75-31193 PBOPOLSIOB SYSTEB PBBFOBHABCE A method for calculating flows through plane Regenerative turbofans - A comparison with airfoil lattices nonregenerative units aircraft engine A75-31245 performance POSER EFFICIENCY A75-33138 Small antennas fractional wavelength design Structural integrity for propulsion systems for wideband applications A75-31113 A75-35827 Performance development of the Gem turboshaft engine POSER SPECTBi for helicopter application Excess noise from gas turbine exhausts [ASME PAPEB 75-GT-28] A75-31586 [ASME PAPER 75-GT-61] A75-346111 A design study of a fan augmented ramjet PREDICTION AHALYSIS TECHBIQDES [ASME PAPEB 75-GT-97] A75-31639 Turbine airfoil life prediction by mission analysis Lift-fan characteristics selection for 1980-85 A75-3U113 V/STOL carrier onboard delivery aircraft Light aircraft lift, drag, and moment prediction: [ASME PAPEB 75-GT-98] A75-31610 A review and analysis Aerodynamics of lifting and propulsive systems in [NASA-CR-2523] 875-21677 a periodically functioning regime - Optimization PBBSSOBB DIS1BIBOTIOB of their performance An inverse method for the design of multielement A75-35815 high-lift systems potential flow inversion PBOPOLSIVE EFFICIENCY [AIAA PAPEB 75-879] A75-33963 The role of computers in future propulsion controls Supercritical airfoil flowfield measurements S75-23582 [AIAA PAPER 75-880] A75-33961 PBOTECTIOB Transonic airfoil analysis and design using FAA lightning protection study: Lightning Cartesian coordinates protection requirements for AIL type 55 K A75-3U195 instrument landing system PBESSDBE DBAG [AD-A008931] 875-23530 Reynolds number effects on fore- and aftbody PBOTBCTIVB COATI8GS pressure drag Control of gas turbine stator blade vibrations by B75-23197 means of enamel coatings PBESSDBE EFFECTS A75-31116 Response of aircraft structural compartments to A fracture mechanics approach to turbine airfoil blast pressures and fragments from high design explosive projectiles [ASME PAPEB 75-GT-79] A75-31628 [AIAA PAPEB 75-751] A75-32652 A-26 SDBJECT IBDEI BBSEABCB ABD DBVELOPHBHT The economic advantages of low and high BECTABG01AB SIHGS temperature anti corrosion coatings on jet Large-scale wind-tunnel tests of three vehicles engine parts - A case history incorporating a deployable rigid wing A75-35119 aircraft design of rectangular wings using PDBPS aircraft models and wind tunnel stability tests intonated test facility for aircraft hydraulic [HASA-TH-X-62405] H75-21671 pumps and motors Influence of a plain flap with a blunt, notched A75-32397 trailing edge on the lift of a rectangular wing [ESBO-TT-117] H75-21685 BBFLECTAHCE Free-molecular interference of cylinders with QUALITY COHTBOL obligue ray reflection hypersonic flow over Systematic development testing for engine parallel cylinders structural integrity assurance A75-33339 A75-31117 A means of dynamic control of radar reflectivity of an antenna or other object by means of a gaseous plasma shroud A75-31851 HADAB ABTEHHAS BEFBACTED IAVES A means of dynamic control of radar reflectivity The refracting inlet - A new concept for aircraft of an antenna or other object by means of a inlet noise suppression gaseous plasma shroud [ASME PAPEB 75-GT-21] A75-31580 A7 5-31851 BEGOLAIOBS BADAB APPEOACH COHTBOL Statistical analysis of the functioning guality of Hake vortex decay near the ground regulators with random parameter scatter [AIAA PAPER 75-882] A75-35173 A75-32171 Airborne wake vortex detection by in-flight BEI8FOBCED PLASTICS radar sensing Mechanics of composite materials Book A75-35125 A75-32163 BADAB CKOSS SECTIOBS BEIBFOBCEBEHT (STRUCTURES) A means of dynamic control of radar reflectivity Evaluation of bead-stiffened metal panels for of an antenna or other object by means of a hypersonic aircraft and space systems design gaseous plasma shroud [AIAA PAPEB 75-815] A75-32701 A75-34851 Calculation of the reinforced thin-walled BADAB HBASURBHEHT construction by the method of the final element Lidar technigues for measuring slant visibility [AD-A007307] B75-23560 for aircraft landing operations BEIBFOBCIHG FIBEBS A75-35031 Analytical displacements and vibrations of BADAB TRACKIIG cantilevered unsymmetric fiber composite laminates A radar and direct visual stndy of the hazard to [AIAA PAPER 75-757] A75-32688 aircraft from bird migrations in the southwest Process evaluation of directionally solidified [AD-A008198] B75-24699 NI3Cb reinforced eutectics in turbine blade form BADIO AHTEBHAS [AD-A008135] B75-2U926 Small antennas fractional wavelength design BELAIATIOB fl&TBOD (HATHEHATICS) for wideband applications Computer simulation of transonic flow past A75-35827 airfoils with boundary layer correction RADIOACTIVE HATERIALS A75-34196 Air transportation of radioactive materials BELIABILITY BHGIBEEBIHG A75-33568 Reliability and maintainability allocation for RABJET ENGIBES avionic maintenance optimization A design study of a fan augmented ramjet A75-35252 [ASHE PAPER 75-61-97] A75-3U639 Reliability specification for gas turbine control Hypersonic research engine project. Phase 2: systems Some combustor test results of NASA B75-23581 aerothermodynamic integration model BBBOTELY PILOTED VEHICLES [HASA-CR-132525] B75-24738 On the way to tactical aircraft robotics BAHDOH LOADS ground based radar control of F-102 A Crack growth under spectrum loading: A crack A75-32152 closure model System concept and key problems concerning [NASA-Tli-X-72708 ] 875-25221 pilotless, remotely-controlled combat aircraft OKF BAHDOB BOISE [DGLR PAPEB 71-076A] A75-34725 Statistical analysis of the functioning quality of The age of the BPV data bus or the data bus comes regulators with random parameter scatter of age airborne computer test systems A75-32U71 &75-35261 BAHDOH PROCESSES BEBE 11 The random decrement technigue applied to the Design and fabrication of* Rene 11 advanced YF-16 flight flutter tests structural panels their performance under [AIAA PAPEB 75-776] A75-32663 axial compression, shear, and bending loads BABBFIED GAS DYHABICS [HASA-CB-132616] B75-21032 Experimental investigation of friction on a plate BESCOE OPBBATIOBS in the flow of a rarefied gas Bescue measures in the case of accidents of the A75-33316 AB-12 aircraft BBAL TIHE OPBRATIOH A75-32527 Development of real time high energy X-ray imaging Parachute systems of the DFVLR for stabilization system for use in dynamic fluoroscopy of aero and salvage of flight vehicles gas turbines [DGLB PAPER 71-013] A75-31661 [ASHE PAPEB 75-GT-117] A75-31654 Analysis of distress air cases in relation to BBATTACHBD FLOW crash position and intended track: 1968 - 1973 An axisymmetric separated and reattached flow on a [AD-A007129] S75-23510 longitudinal blunt circular cylinder RESEARCH AIBCBAFT [ASBE PAPEB 15-APH-1H] A75-35101 Rotor Systems Research Aircraft /BSRA/ BECOVEBY PARACHUTES A75-33621 Parachute systems of the DFVLR for stabilization Analysis of various descent trajectories for a and salvage of flight vehicles hypersonic-cruise, cold-wall research airplane [DGLB PAPEB 71-013] .A75-31661 [BASA-TH-D-7860] H7S-21673 BSCTABGOL4B FAHBLS RESEARCH ABD DBTELOPBBBT Crippling/column buckling analysis and test of Corrosion control in naval aircraft graphite/epoiy-stiffened panels A75-32830 [AIAA PAPER 75-753] A75-32681 A-27 BBSOHAHT FBEQOBHCIES SUBJECT IHDEX Structural integrity for propulsion systems KAflex drive shaft coupling for DH-1 helicopter. 475-34113 Design refinement BBSOHAHT FBBQOBHCIES [AD-A008365] B75-24731 Natural oscillations of liquid in a horizontal BOTATIHG SHAFTS container with symmetric double-connected cross Dynamic response of viscous-damped multi-shaft jet section engines [AD-A007312] N75-23906 A75-34128 BBSOHABT VIBBATIOH BOTATIHG STALLS Control of gas turbine stator blade vibrations by Study on the mechanism of stall margin improvement means of enamel coatings of casing treatment of low speed axial flow 475-34116 compressors BBTBACTABLB BQOIPBBHT [4SBE PAPEB 75-GT-13] A75-31576 Dynamic and aeroelastic problems of stop-rotors BOTOB AEBODTHAHICS and their analytical treatment. Part 2: Influence of structural damping, preconing offsets Analytical equations and solutions V/STOL and large deflection on the flap-lag-torsional aircraft stability of a cantilevered rotor blade [ESBO-TT-145-PT-2] H75-21683 [AIAA PAPER 75-780] 475-32667 BBYBOLDS HOBBBB Local momentum theory and its application to the Beynolds number effects on fore- and aftbody rotary wing pressure drag [AIAA PAPEB 75-865] A75-33952 N75-23497 High-speed rotor dynamics - An assessment of Beynolds number effects on boattail drag of current technology for small turboshaft engines exhaust nozzles from wind tunnel and flight tests A75-31127 N75-23506 Aerodynamics of rotors - Wake equilibration BIBS (SDPPOBTS) A75-35814 Sound radiation from a bounded thin inhomogeneous Dynamic and aeroelastic problems of stop-rotors plate reinforced with N ribs and driven by and their analytical treatment. Part 2: boundary-layer pressure fluctuations Analytical equations and solutions V/ST01 475-33117 aircraft BIGID BOTOBS [ESRO-TT-145-PT-2] H75-24683 Influence of structural damping, preconing offsets BOIOB BLADES and large deflection on the flap-lag-torsional Three dimensional characteristics of turbulent stability of a cantilevered rotor blade wakes behind rotors of axial flow tnrbomachinery [AIAA PAPEB 75-780] A75-32667 [ASME PAPEB 75-GI-1] A75-34566 BIGID STBOCTOBES Botor burst protection program - Statistics on Theoretical and experimental research on the aircraft gas turbine engine rotor failures that fatigue crack propagation in stiffened panels, occurred in O.S. commercial aviation during 1973 an evaluation of the Paris theory [ASBE PAPEB 75-GT-12] A75-34575 [AD-A008079] N75-24732 Spatial supersonic flow through annular cascades BOLLEB BBABIHGS [ASBE PAPEB 75-GT-113] A75-34650 Design and development of low-cost, self-contained BOTOB BLADES (TDBBOHACBIBEBI) bearing lubrication systems for turbine engines Influence of mistuning on rotor-blade vibrations A75-34121 A75-33483 BOLLIHG HOHEHTS A study of casing treatment stall margin Theoretical study of lift-generated vortex wakes improvement phenomena for axial compressor designed to avoid rollup rotor blade tips 475-331(85 [ASBE PAPEB 75-GT-60] A75-34613 Some wind tunnel measurement of the trailing Unsteady boundary layers over rotating blades vortex development behind a sweptback wing - [ASBE PAPER 75-GT-64] A75-34617 Induced rolling moments on intercepting wings BOTOB SPBBD [AIAA PAPER 75-881] 475-33966 Dynamic simulator for advanced gas turbine engine Velocity and rolling-moment measurements in the component tests wake of a swept-wing model in the 40 by 80 foot A75-34116 wind tunnel BDB TIBE (COBPDTEBS) [NASA-TB-X-62414] 1175-23181 A fast semidirect method foe computing transonic BOTABY STABILITY aerodynamic flows Surge and rotating stall in axial flow A75-34194 compressors. I - Theoretical compression system model [ASUS PAPEB 75-GT-9] A75-34573 A study of casing treatment stall margin S-3 AIBCBAFT improvement phenomena for axial compressor S-3A stall testing and auto-throttle rotor blade tips development/testing [ASBB PAPEB 75-G1-60] 475-34613 A75-33613 BOTAB7 BUGS The S-3A carrier suitability demonstration Influence of structural damping, preconing offsets A75-33614 and large deflection on the flap-lag-torsional Automatic test equipment for S-3A support stability of a cantilevered rotor blade A75-35279 [AI44 PAPEB 75-780] 475-32667 SAFBTI BABAGBBEBT Botor Systems Besearch Aircraft /BSBA/ Hew Air Force requirements for structural safety, 475-33621 durability and life management Local domentum theory and its application to the [AIAA PAPBB 75-781] 475-32668 rotary wing HDD - An important new aid to the L.S.O Head [AIAA P4PEB 75-865] 475-33952 Op Display for Landing Signal Officer Prediction of rotor wake induced flow along the A75-33620 rocket trajectories of an Army AH-1G helicopter Safety-related engineering and development [AD-A007878] 875-23528 activities of the Federal Aviation Administration Advanced overrunning clutch technology, design phase [AD-A008395] H75-24698 [AD-A007815] H75-23562 SAHDIICB STBDCTDBES Besearch on helicopter rotor noise Impact fracture of composite sandwich structures [AD-A007261] H75-23608 [AIAA PAPEB 75-748] A75-32673 The development of experimental techniques for the SEALS (STOPPEBS) study of helicopter rotor noise Current seal designs and future requirements for [HAS»-CB-137684] N75-23611 turbine engine seals and bearings Summary of BIT research on dynamic stall and 475-34123 blade-vortex interaction, 1971 - 1974 SEAT BELTS [AD-J008091] H75-24689 A crashworthy armored pilot seat for helicopters [AD-A007551] 875-23541 A-28 SUBJECT IIOBZ SPACE SBOtniS SBPABATBD FLOR SHBOODS Study of a strongly asymmetric tnrbulent wake A means of dynamic control of radar reflectivity behind a profile with upper-surface separation of an antenna or other object by means of a A75-32954 gaseous plasma shroud Calculation of the separated flow at a A75-34854 thin-section wing of finite span SIGIATDBB ABALISIS A75-34262 Airborne wake vortex detection by in-flight In axisymmetnc separated and reattached flow on a radar sensing longitudinal blunt circular cylinder A75-35425 [ASHE PAPBH 75-APH-14] " A75-35101 SIHOLAIOBS SBBTICB LIFE Aircraft engine nacelle fire test simulator Statistical estivation of service cracks and [AD-A007853] B75-23617 •aintenance cost for aircraft structures SIBGBIABITI (HAIHBBATICS) [AIAA PAPEH 75-767] A75-32657 The supersonic doublet-lattice method - A Design of fabricated static structures for long comparison of two approaches based on kernel cyclic life functions A75-34142 [AIAA PAPEB 75-760] A75-32691 Turbine airfoil life prediction by nission analysis SKID PBICTIOB A75-311H3 Unsteady boundary layers over rotating blades SBAFTS (BiCHIHB BLBBBITS) [ASHE PAPEB 75-GT-64] A75-34617 KAflex drive shaft coupling for BB-1 helicopter. SLBBDBB BODIES Design refinement Side forces on unyawed slender inclined [AD-A008365] H75-24731 aerodynamic bodies SHARP LBADISG 8DGBS A75-33435 Aerodynamic heating in gaps in the presence of Image system solution for store aerodynamics with protuberances and shock wave impingement interference. I [AIAA PAPEB 75-670) A75-32907 A75-33436 SHEAR STBAIB Aerodynamic characteristics of an axisymmetric Account of shearing strain during the calculation body undergoing a uniform pitching motion of the oscillations of low aspect-ratio wing by [AIAA PAPEB 75-838] A75-33933 the method of polynomials Integral eguations for the calculation of the flow [AD-A007397] B75-23518 about accelerated slender bodies for 8 greater, SBBAB STBESS equal, or less than 1 Design and fabrication of Bene 41 advanced A75-35204 structural panels their performance under Problem of supersonic flow past a slender pointed axial compression, shear, and bending loads body with tall [NASA-CB-132646] H75-24032 A75-35706 SHIP BOLLS Analysis of transonic flow about lifting wing-body Studies and research on marine hulls working with configurations natural ground effect [NASA-TB-B-440] N75-24681 H75-23475 SLESDBB RIBGS SHOCK RAVE IHTBBACTIOB Applications of a quadratic extended interior General analysis of the diffraction pattern for a penalty function for structural optimization plane acoustic wave at a wedge moving at [AIAA PAPEB 75-764] A75-32654 supersonic speed Analysis of transonic flow about lifting wing-body A75-34272 configurations Two-dimensional transonic calculations with [HASA-TB-B-440] H75-24681 boundary layers SBALL PEBIOBBATIOB FLOB A75-35819 A perturbation method for transonic flows about Unsteady behavior of transonic flows shock oscillating airfoils induced oscillation [AIAA PAPEB 75-877] A75-35171 [HPIS-HITT-59] H75-23516 Aerodynamics of lifting and propulsive systems in Interaction of shock wave with wedge, which moves a periodically functioning regime - Optimization at supersonic speed of their performance [AD-A007302] H75-23519 A75-35815 SBOCK RAVE PBOFAGATI01 SOBIC BOOHS The problem of diffraction of a strong Vibration responses of test structure no. 1 during magnetogasdynanc shock wave by a wedge the Edwards Air Force Base phase of the national A75-32518 sonic boom program P-104, B-58, and XB-70 Aerodynamic heating in gaps in the presence of sonic boom exposures protuberances and shock wave impingement [NASA-TB-I-72706] B75-24744 [AIAA PAPEB 75-670] A75-32907 SOOID FIELDS SBOCK RJVES Experiments concerning the response of supersonic Transonic potential flow calculations using nozzles to fluctuating inlet conditions conservation form for shock-free airfoils noise measurement A75-34193 [ASBE PAPEB 75-GT-40] A75-34597 SBOBT HAUL AIBCBAPT SOUHD HAVES The An-2 aircraft /4th revised and enlarged edition/ Random vortex shedding noise of airfoils Bussian book A75-32430 A75-35350 Sound radiation from a bounded thin inhoaogeneous SBOBT TAKEOFF JIBCB4FT plate reinforced with N ribs and driven by Maximum lift of upper surface blowing STOL boundary-layer pressure fluctuations aircraft with swept wings A75-33417 [AIAA PAPBS 75-868] A75-33955 General analysis of the diffraction pattern for a Rind shear effects on landing touchdown point plane acoustic wave at a wedge moving at A75-35420 supersonic speed Calculation of static longitudinal aerodynamic A75-34272 characteristics of STOI aircraft with upper SPACE BBVIBOBHEBT SIHDLATIOB surface blown flaps Shuttle spacelab simulation using a tear jet [HASA-CB-137646] 1175-23483 aircraft: Hission no. 3 (ASSESS program) A Kalman filter for the Stoland system [NASA-TB-X-62410] B75-24760 [HASA-CB-137668] S75-23543 SPACE LABOBATOBIBS A formal structure for advanced automatic Shuttle spacelab simulation using a Lear jet flight-control systeas aircraft: Mission no. 3 (ASSESS program) [NASA-TH-D-7940] B75-23606 [NASA-TB-X-62410] B75-24760 Low speed wind tunnel tests on a one-seventh scale SPACB SHUTTLES model of the H.126 jet flap aircraft Shuttle spacelab simulation using a Lear jet [BASA-TH-X-62433] 1175-24722 aircraft: Mission no. 3 (ASSESS program) [HASA-TB-I-62410] S75-24760 A-29 SPACBCBAPT COBFIGOBATIOIS SDBJgCT IIDBX SPACECBAFT COIFIGOBHIOBS SIBBABLIBIBG Computational procedare for three-dimensional Challenge to aviation: Batching a leaner pterosaner boundary layers on aircraft and aerospace vehicles improving commercial aircraft design for A75-34190 greater fuel efficiency SPACBCBAFT DBSIGB [BASA-TB-I-71744] B75-25298 Korolev: A chronicle a biography of Sergey STBBSS COBCEBIBATIOB Pavlovich Korolev Influence of mistuning on rotor-blade vibrations [HASA-TT-F-16278] H75-24654 ' A75-33K83 SPECTBAL BBISSIOI Blade vibration - Some key elements in design Elternal fins and ejector action for reducing the verification infrared emssion of engine ezhanst ducting A75-34132 [HASA-TH-X-3242] H75-25094 Fracture failure lodes in lightweight bearings SPECTEOB ABALTSIS A75-34140 Diagnostics of jet aero-engines by means of stress concentration in an expanded plate with spectral analysis of lubricating oil opening reinforced by central belt A75-32470 [AD-A007672] B75-24044 SPIH TESTS STRESS COBBOSIOB CBACKIBG Stone Spin Shorthand, including: Spin Data Card Fracture failure lodes in lightweight bearings and sample Criteria Spin Set for testing 475-34140 out-of-control flight STBBSS CYCLES A75-33618 Low-cycle fatigue and creep analysis of gas SPOILEBS turbine engine components Effectiveness of spoilers on the GA(W)-1 airfoil 475-34139 vlth a high perforaance Fouler flap STBOCTOBAL AiALISIS [NASA-CB-2538] 1175-23484 Analytical displacements and vibrations of SPBIBGS (ELASTIC) cantilevered nnsynmetric fiber composite laminates The influence of short springs on longitudinal [AIAA PAPBB 75-757] A75-32688 static stability Crack growth under spectrum loading: A crack [CBABFIELD-AEBO-29] H75-23607 closure nodel STABILITY [NASA-TH-X-72708] 1175-25221 Development of high stability fuel STBOCTOBAL DESIGB [AD-A007574] S75-23604 Bechanics of composite materials Book STALLIHG A75-32463 Review of hammershcck pressures in aircraft inlets Stochastic model for fatigue crack size and cost A75-3U115 effective design decisions for aerospace STATIC TESTS structures Development and testing under static conditions of [AI44 PAPEB 75-766] A75-32656 a B-A1 load transfer element New Air Force requirements for structural safety, [AIAA PAPEB 75-788] A75-32675 durability and life management The 727 airplane target thrust reverser static [AIAA PAPEB 75-781] A75-32668 performance model test for refanned JT8D engines Vibration analysis of multi-synmetric structures [BASA-CR-134652] N7S-24737 [AIAA PAPBB 75-808] 475-32706 STATIC THBUST Propulsion system structural integration and Improvement of propeller static thrust estimation engine integrity; Proceedings of the Symposium, [HASA-CB-132680] S75-23567 D.S. Naval Postgraduate School, Honterey, STATISTICAL ABALYSIS Calif., September 3-6, 1974 Statistical analysis of the functioning quality of A75-34112 regulators vith random parameter scatter Propulsion system and airframe structural 475-32471 integration program Statistical estimation of service cracks and 475-34118 maintenance cost for aircraft structures Turbine Engine Structural Integrity Program /EBSIP/ [AIAA PAPEB 75-767] 475-32657 475-34137 Botor burst protection program - Statistics on Design of composite structure with respect to aircraft gas turbine engine rotor failures that avoid crack propagation occurred in U.S. commercial aviation during 1973 H75-23709 [ASBE PAPEB 75-GT-12] 475-34575 STBOCTOBAL FAILOBB STATISTICAL DECISIOS TBEOBY A method to determine a distribution function of Stochastic model for fatigue crack size and cost main structure failures in an aircraft effective design decisions for aerospace 475-32468 structures STBOCTOBAL BBLIABILITY [AIAA PAPEB 75-766] A75-32656 Hew Air Force reguirements for structural safety, STATOB BLADES durability and life management Control of gas turbine stator blade vibrations by [AIAA PAPEB 75-781] 475-32668 means of enamel coatings Structural integrity for propulsion systems 475-34116 475-34113 Design and analysis of a ceramic stator vane Turbine Engine Structural Integrity Program /EHSIP/ [ASME PAPEB 75-G1-100] A75-34642 475-34137 STEADY FLOS Systematic development testing for engine Ose of numerically generated body-fitted structural integrity assurance coordinate systems for solution of the 475-34147 Navier-Stokes equations STBOCTOBAL STABILITY A75-34186 Crippling/column buckling analysis and test of Extension of the parabolic method for the graphite/epoxy-stiffened panels transonic flow. I - steady flow. II - Unsteady [AI44 PAPEB 75-753] A75-32684 flow Formation of flexibility matrices of a structure 475-35215 based on known yields at arbitrary points The drag and oscillating transverse force on A75-32995 vibrating cylinders due to steady fluid flow STBOCTOBAL VIBBATIOB 475-35765 The random decrement technique applied to the STIFFBESS HATBIX YF-16 flight flutter tests Formation of flexibility matrices of a structure [AIAA PAPEB 75-776] A75-32663 based on known yields at arbitrary points YF16 active-control-system/structural dynamics 475-32995 interaction instability STOCBASTIC PBOCESSBS [AIAA PAPEB 75-823] 475-32695 Stochastic model for fatigue crack size and cost System identification of a complex structure effective design decisions for aerospace helicopter gearbox dynamics from shake test data structures [4IAA PAPEB 75-809] 475-32705 [AIAA PAPEB 75-766] 475-32656 Vibration analysis of multi-symmetric structures [AIAA PAPEB 75-808] 475-32706 4-30 SUBJECT IBDEI SOPBBSOBIC BOZZLBS Sound radiation frcm a bounded thin inhomogeneous SOPEBSOHIC AIBCBAFT plate reinforced with H ribs and driven by Hitsubishi's mentor - Supersonics from Hagoy^ boundary-layer pressure fluctuations T-2 close support fighter and trainer 475-33117 A75-33118 Influence of mistnning on rotor-blade vibrations An air intake control system for a supersonic 475-331183 fighter aircraft Dynamic response of viscous-damped nulti-shaft jet 875-23589 engines Effects of asymmetry on the dynamic stability of 475-31128 aircraft Philosophy, design, and evaluation of soft-nounted [HASA-CB-112857] S75-21756 engine rotor systems SUPERSONIC 4ISPOILS 475-3*130 Oscillatory supersonic lifting surface theory Advances in fan and compressor blade flutter using a finite element doublet representation analysis and predictions [AIAA PAPEB 75-761] 475-32692 475-31131 General analysis of the diffraction pattern for a Blade vibration - Sooe key elements in design plane acoustic wave at a wedge moving at verification supersonic speed 475-31132 475-31272 Vibration responses of test structure no. 1 during Structural response of fiber composite fan blades the Edwards Air Force Base phase of the national [ASHE P4PEB 75-GT-78] 475-31627 sonic boom program F-101, B-58, and XB-70 SOPEBSOHIC BOOHD4BY L4IEBS sonic boon exposures Study of the interaction and three-dimensional [HAS4-TH-X-72706 ] N75-21711 separation effects of a boundary layer in a STBDCTDBAL HEIGHT supersonic laminar regime French book Computer program to assess impact of fatigue and 475-35150 fracture criteria on weight and cost of SOPEBSOHIC CORBOSTIOH BAHJET EHGIHES transport aircraft Subscale, hydrogen-burning, [NASA-CH-132618] N75-2U718 airframe-integrated-scramjet: Experimental and SOBCBITICiL FLOi theoretical evaluation of a water cooled strut Calculation of transonic flows using an extended airframe-integrated-scramjet: Experimental integral equation method leading edge [AIAA PAPEB 75-876] 475-33961 [H4S4-TB-X-72682] 875-23885 SOBSOBIC AIRCB4PT SOPBBSOHIC FLIGBT Effect of simulated forward flight on subsonic jet Computation of nonequilibriam three-dimensional exhaust noise inviscid flow over blunt-nosed bodies flying at [AIAA PAPEB 75-869] 475-33956 supersonic speeds SDBS08IC FLOW [AIAA PAPEB 75-835] 475-33931 A calculation method for unsteady subsonic flpw Design and analysis of a supersonic about harmonically oscillating wing-body penetration/maneuvering fighter configurations [NASA-CB-132633] 875-23558 [AIAA PAPEB 75-861] A75-33951 SOPEBSOHIC FLOI A finite-element method for lifting surfaces in The supersonic doublet-lattice method - A steady incompressible subsonic flow comparison of two approaches based on kernel [NASA-CB-112811] N75-23177 functions Subsonic base and boattaxl drag, an analytical [AIAA PAPEB 75-760] A75-32691 approach Experimental investigation of friction on a plate N75-23192 in the flow of a rarefied gas SDBSOHIC PLDTTBB A75-33316 Subsonic transient lifting surface aerodynamics Computer simulation of transonic flow past [AIAA PAPEB 75-758] 475-32689 airfoils with boundary layer correction SOBSOSIC SPEED 475-34196 Subsonic and supersonic indicial aerodynamics and Spatial supersonic flow through annular cascades aerodynamic transfer function for coaplex [ASHE PAPEB 75-GT-113] 475-31650 configurations aerodynamic configurations Problem of supersonic flow past a slender pointed for subsonic and supersonic speeds using the body with tail finite elenent method 475-35706 [N4S4-CB-112818] H75-23178 Calculations of three-dimensional flows in a The subsonic base drag of cylindrical twin-jet and linearized supersonic regime single-jet afterbodies A75-35813 B75-23198 An experimental investigation of the component Effect of wing planform and canard location and drag composition of a two-dimensional inlet at geometry on the longitudinal aerodynamic transonic and supersonic speeds characteristics of a close-coupled canard wing B75-23189 model at subsonic speeds Interaction of shock wave w,ith wedge, which moves [SASA-TH-D-7910] H75-23511 at supersonic speed An investigation of the flow field of the 4-7D [AD-4007302] M75-23519 aircraft with several external store loadings at Experimental study of heat transfer during flow Bach numbers 0.70 and 0.95 around uncambered delta wings with blunted edges [4D-4008176] H75-21688 [AD-4007316] H75-23521 SDBSOBIC SIBD TUBBELS SOPEBSOSIC FLOTTEB Study on the establishment of flow in a wind Integrated potential formulation of unsteady tunnel functioning by Induction supersonic aerodynamics for interacting wings A75-35811 [4144 P4PEB 75-762] 475-32693 SDPEBCBITICAL FLO1 Aeroelastic panel optimization with aerodynamic Calculation of transonic flows using an extended damping integral equation method A75-33188 [4IAA PAPEB 75-876] 475-33961 Advances in fan and compressor blade flutter A fast semidirect method for computing transonic analysis and predictions aerodynamic flows 475-31131 475-31191 SDPEBSOHIC IHLETS SUPERCRITICAL BIHGS Transonic off-design drag and performance of three Supercritical airfoil flowfield measurements mixed-compression axisymmetric inlets [AIAA PAPEB 75-880] 475-33961 [HASA-TH-X-3215] 875-23602 Supercritical wing sections II: A handbook —— SOP1BSOHIC HOZZLES numerical computations Experiments concerning the response of supersonic A75-31975 nozzles to fluctuating inlet conditions noise measurement [4SHB MPEB 75-GT-10] 475-31597 4-31 SDPBBSOHICS SUBJECT IHDEX Effect of external conditions on the functioning Propulsion system and airframe structural of a dual flow supersonic nozzle designing integration program propulsion system of military aircraft A75-31118 B75-23191 International and U.S. design proposals for a SOPERSONICS microwave landing system Subsonic and supersonic indicial aerodynamics and A75-31536 aerodynamic transfer function for complex Involving the expert and aviation community in the configurations aerodynamic configurations decision making structure of the O.S. MLS program for subsonic and supersonic speeds using the Microwave Landing System finite element method A75-31537 [BASA-CB-112818] N75-23178 Parachute systems of the DFVLB for stabilization SUPPORT'SYSTBBS and salvage of flight vehicles Plight test results of an automatic support system [DGLB PAPEB 71-013] A75-31661 on board a YF-12A airplane for ]et engine An overview and assessment of plans and programs inlet air control for the development of the upgraded third A75-35272 generation air traffic control system SDBFiCE FIBISBIHG [AD-A008910] B75-23531 Surface finishing particularly for use in The use of digital control for complex power plant smoothing irregularities on aluminum aircraft management vings B75-23596 [ NASA-CASE-HSC-12631-1] N75-23176 SDBFiCE BODGHHESS Determination of surface roughness of materials A75-33331 t TAIL SDBFACBS Influences of manufacturing tolerances and surface The flutter analysis of T-tails roughness of blades on the performance of turbines [AIAA PAPEB 75-759] A75-32690 [ASHE PAPEB 75-G1-35] A75-31592 T-2 AIBCBAFT SDBFACE TBHPBBATOHB Mitsubishi's mentor - Supersonics from tiagoya Observing cold-night temperatures of agricultural T-2 close support fighter and trainer landscapes with an airplane-mounted radiation A75-33118 thermometer T-33 AIBCBAFT A75-33103 Analysis of wake vortex flight test data behind a SOBFACES T-33 aircraft A finite-element method for lifting surfaces in [BASA-CB-137669] B75-23182 steady incompressible subsonic flow TAIL ASSBBBLIBS [NASA-CB-112811] N75-23177 Hinimum weight design of the F-15 empennage for SDBGES flutter YF-16 air induction system design loads associated [AIAA PAPEB 75-777] A75-32661 with engine surge The flutter analysis of T-tails A75-31111 [AIAA PAPEB 75-759] A75-32690 S1EPT SISGS Subsonic base and boattail drag, an analytical Variable geometry today latest swing wing approach aircraft B75-23192 A75-33117 TAKBOFF BDBS The annals of the polymorph - A short history of Aeronautical requirements and procedure for variable geometry. II variable swept wings low-level turbulence and wind shear reporting A75-33119 A75-35111 Haximum lift of upper surface blowing STOL TECHBOLOGICAL FOBECASTIBG aircraft with swept wings Cargo aircraft - A look toward the future [AIAA PAPEB 75-868] A75-3395S A75-35290 Velocity and rolling-moment measurements in the Analysis of technology requirements and potential wake of a swept-wing model in the 10 by 80 foot demand for general aviation avionics systems in wind tunnel the 1980's technology assessment and C 8ASA-TB-X-62111 ] H75-23181 technological forecasting of the aircraft industry SiEPTBACK BIHGS [BASA-CB-137629] B75-21735 Some wind tunnel measurement of the trailing TECHNOLOGY ASSESSHEBT vortex development behind a sweptback wing - Chemical milling review Induced rolling moments on intercepting wings A75-32810 [AIAA PAPER 75-881] A75-33966 Recent advances in in-flight simulator technology Calculation of loads and deformations of sweptback A75-33187 wing with the aid of mechanical analog instruments The annals of the polymorph - A short history of [AD-A007308] N75-23525 variable geometry. Ill variable wing aircraft An experimental investigation on the transonic A75-33150 flutter characteristics of the cantilever Bell Belicopter/NASA/Army X7-15 status report swept-back wing with aerofoil section, and A75-33617 comparison with the thin cantilever svept-back Bigh-speed rotor dynamics - In assessment of wing current technology for small turboshaft engines [HAE-J.IB-THABS-1838] H75-21680 A75-31127 STREETS! Engineering titanium alloys Russian book Vibration analysis of multi-symmetric structures A75-35519 [AIAA PAPEB 75-808] A75-32706 Analysis of technology reguirements and potential SYSTEB EFPECTT.VEHBSS demand for general aviation avionics systems in Air traffic controllers' operative effectiveness the 1980's technology assessment and under HAS environments technological forecasting of the aircraft industry A75-31539 [BASA-CB-137629] S75-21735 SYSTEBS AHALYSIS TECHNOLOGY DTILIZATIOB Identification of systems by means of adaptive model Loran-C compared with other navigation aids in application to jet engines neeting future Canadian needs A75-32173 475-35796 SYSTBHS EBGIBEBBISG Analysis of technology reguirements and potential Propulsion system structural integration and demand for general aviation avionics systems in engine integrity; Proceedings of the Symposium, the 1980's technology assessment and D.S. Naval Postgraduate School, Bonterey, technological forecasting of the aircraft industry Calif., Septenber 3-6, 1971 [BASA-CB-137629] H75-21735 A75-31112 TBBPEBATBRE EFFECTS YF-16 air induction system design loads associated Jet-induced thermal effects for VTOL aircraft with engine surge [ASBE PAPER 75-GT-96] A75-31638 A75-31111 i-32 SOBJECT IBDBI TILTIIG BOTOIS Exhaust plane temperature effects an nozzle IBIB BUGS afterbody performance over the transonic Bach A three-dimensional solution of flo*« over clogs number range with leading-edge vortex sepacatio* H7 5-23504 [AIM PAPEB 75-866] 175-33953 TBHPBBMUBE BEASDBIIG IHSTBOBEBTS Calculation of the separated flow at • Temperature measurement for advanced gas tarbine thin-section wing of finite span controls 175-34262 875-23597 TBBEB DIHBISIOI1L BODID1BI L1IBB TEBSILB TESTS Computational procedure for three-dimensional Directionally solidified lamellar eutectic boundary layers on aircraft and aerospace vehicles sdperalloys by edge-defined, fill-fed groHth A75-39190 including tensile tests TBBBB DIBEHSIOHAL FLOS [SASA-CB-131808] B75-24897 Computation of nonequilibrinm three-dimensional TEST FACILITIES inviscid flow over blunt-nosed bodies flying at Laboratory testing of controls for aircraft supersonic speeds turbine engines [AIAA PAPEB 75-835] A75-33931 [»SBE PiPEB 75-GT-101] A75-31643 A three-dimensional solution of flows over wings TEST PILOTS with leading-edge vortex separation YF-16 - A rare opportunity flight test program [AIAA PAPEB 75-866] A75-33953 A75-33615 Three dimensional characteristics of turbulent TEST STABDS wakes behind rotors of axial flow turbomachinery Automated test facility for aircraft hydraalic [ASBE PAPEB 75-GT-1] A75-31566 pumps and motors Concurrent mixing and diffusion in three dimensions A75-32397 ejector performance THEBBAL BOOBDABT LAIBB [AIAA PAPEB 75-873) A75-35170 Unsteady boundary layers over rotating blades Study of the interaction and three-dimensional [ASHE PAPEB 75-GT-61] A75-31617 separation effects of a boundary layer in a THBBBAL BAPPIHG supersonic laminar regime French book Passive infrared inaging systems A75-35150 A75-31881 Calculations of three-dimensional flows in a TBBBBil POILOTIOS linearized supersonic regime Besponse of a light aircraft to a thermal exhaust A75-35813 plume TBBOTTLIBG A75-35103 S-3A stall testing and auto-throttle TBEBHOBLASTICITT. development/testing Design and analysis of a ceramic stator vane A75-33613 [»SHE PAPEB 75-GT-100] A75-31642 TBBOST ADGBBBIATIOB TBBBBOBETEBS Beversed cowl flap inlet thrust augoentor with Observing cold-night temperatures of agricultural adjustable airfoil landscapes with an airplane-mounted radiation [BASA-CASE-ARC-10751-1] H75-21736 thermometer •"HBUST BEABIBGS A7S-33103 Design and development of low-cost, self-contained TBICKHESS BATIO bearing lubrication systems for turbine engines Method of the optimization of the load-carrying A75-31121 structure of King on rigidity during variation TEBOSr HBASCBEBEBT by the distribution of thickness ratio Interaction of jets of GE CF6-50 reactors with the [AD-A007317] N75-23521 wing cellules of the airbus during cruise - An investigation on the effect of second-order Rind-tunnel simulation additional thickness distributions to the upper A75-35808 surface of an NACA 61 sub 1-212 airfoil TBBOST BEVBBSAL using flow equations and a CDC 7600 digital Ground vortex - Limit to engine/reverser operation computer for high bypass ratio engine [NASi-CB-137701] N75-2167U [ASBE PAPEB 75-GT-3] A75-31567 An investigation on the effect of second-order Research about effects of external flow and additional thickness distributions to the upper aircraft installation conditions on thrust surface of an HACA 61-206 airfoil using flow reversers performances equations and a CDC 7600 digital computer N75-23195 [N1SA-CB-137702] »75-2a675 Reverse thrust experience on the Concorde Theoretical effect of modifications to the upper H75-23II96 surface of two NACA airfoils using smooth Aerodynamic aspects and optimisation of thrust polynomial additional thickness distributions reverser systems which emphasize leading edge profile and which H75-23513 vary guadratically at the trailing edge The 727 airplane target thrust reverser static using flow equations and a CDC 7600 computer performance model test for refanned JT8D engines [HASA-CB-137703] N75-21676 [HASA-CB-131652] 1175-21737 TBIB AIBFOILS Effect on fan flow characteristics of length and Random vortex shedding noise of airfoils axial location of a cascade thrust reverser A75-32H30 [NASA-TB-X-3217] N75-21715 A perturbation method for transonic flows about TBBDST-IEIGBT BATIO oscillating airfcils A design study of a fan augmented ramjet [AIAA PAPEB 75-877] A75-35171 [ASHE PAPEB 75-GT-97] A75-31639 TBIH PILBS TBDBDEBSTOBBS Application of thin-layer chromatography for Aircraft turbulence encounters during commercial determining the wearing capacity of additives operations in the vicinity of thunderstorms contained in petroleum-based aviation oils A75-35118 A75-35300 TILT BOTOB BBSBABCB AIBCBAFT PBOGBAB TBIB PLATES Bell Helicopter/HASA/Army XV-15 status report Experimental investigation of friction on a plate A75-33617 in the flow of a rarefied gas NASA/Army XV-15 tilt rotor research aircraft A7 5- 33 34 6 familiarization document Sound radiation from a bounded thin inhomogeneous [NASA-TB-X-62107] B75-21720 plate reinforced with N ribs and driven by TILT IIBG AIBCBAFT boundary-layer pressure fluctuations Bell Helicopter/NASA/Army XV-15 status report A75-33117 A75-33617 TBIB BALLS TILTIBG BOTOBS Fabrication of one-piece-forged thin-walled parts Bell Belicopter/HASA/Army XV-15 status report having variable cross section Russian book A75-33617 A75-33150 A-33 TITHIOR ALLOYS SUBJECT IHDEI TITABIUH ALLOTS TBABSOBIC FLOW Titaniui casting - Industrial development - A modern look at confornal mapping, including Economic aspects doubly connected regions for computerized A75-351S9 design of airfoil Engineering titanium alloys Russian book [AIAA PAPEB 75-842] A75-33936 A75-35519 Finite element analysis of unsteady transonic flov Evaluation of the reliability and sensitivity of [AIAA PAPEB 75-875] A75-33960 DDT methods for titaniun alloys, Volume 2 Calculation of transonic flovs using an extended [AD-AOO 16011] B75-24923 integral eguation method TOLBBAHCES (HECHABICS) [AIAA PAPEB 75-876] A75-33961 Influences of manufacturing tolerances and surface Transonic flow about a thick circular-arc airfoil roughness of blades on the performance of turbines [AIAA PAPEB 75-878] A75-33962 [iSHE PAPER 75-GT-35] A75-3U592 Supercritical airfoil flowfield measurements TOBSIOBAL VIBRiTIOH [AIAA PAPEB 75-880] A75-33961 Influence of structural damping, preconing offsets Transonic potential flow calculations using and large deflection on the flap-lag-torsional conservation forn for shock-free airfoils stability of a cantilevered rotor blade A75-34193 [AIAA PAPEB 75-780] A75-32667 A fast semidirect method for computing transonic TODCBDOIH aerodynamic flows Wind shear effects on landing touchdown point A75-34194 A75-35420 Transonic airfoil analysis and design using TRADEOFFS Cartesian coordinates B-1 airborne strategic deterrent A75-34195 A75-33550 Computer simulation of transonic flow past TBAILIHG EDGES airfoils with boundary layer correction Active flutter suppression using trailing-edge and A75-34196 tab control surfaces Integral eguations for the calculation of the flow [AIAA PAPEB 75-822] A75-32697 about accelerated slender bodies for H greater, Some wind tunnel measurement of the trailing egual, or less than 1 vortex development behind a sveptback ving - A75-35204 Induced rolling moments on intercepting wings Extension of the parabolic method for the [AIAA PAPEB 75-881] A75-33966 transonic flow. I - Steady flow. II - Unsteady Trailing edge flows over turbomachine blades and flow the Kutta-Joukowsky condition A75-35215 [ASHE PAPEB 75-61-94] A75-3U636 Two-dimensional transonic calculations with Theoretical effect of modifications to the upper boundary layers surface of two NACA airfoils using smooth A75-35819 polynomial additional thickness distributions The measurement of the transonic spillage drag of which emphasize leading edge profile and which a supersonic intake vary quadratically at the trailing edge H75-23488 using flow eguations and a CDC 7600 computer An experimental investigation of the component [NASA-CB-137703] B75-24676 drag composition of a two-dimensional inlet at TBAILIHG-BDGB FLAPS transonic and supersonic speeds Experimental study of the effect of span loading 875-23489 on aircraft wakes Dnsteady behavior of transonic flows shock [AIAA PAPEB 75-885] A75-33967 induced oscillation Influence of a plain flap with a blunt, notched [HPIS-HITT-59] B75-23516 trailing edge on the lift of a rectangular wing Analysis of transonic flow about lifting wing-body [ESBO-TT-117] B75-21685 configurations TBAIBIHG AIBCBAFT [NASA-TB-B-140] B75-24681 Hitsubishi's mentor - Supersonics from Bagoya TBABSOBIC FLDTTEB T-2 close support fighter and trainer A perturbation method for transonic flows about A75-33148 oscillating airfoils TBAIBIBG SIBDLATOBS [AIAA PAPEB 75-877] A75-35171 Becent advances in in-flight simulator technology An experimental investigation on the transonic A75-33187 flutter characteristics of the cantilever TBAJECTOBY ANALYSIS swept-back wing with aerofoil section, and Analysis of various descent trajectories for a comparison with the thin cantilever swept-back hypersonic-cruise, cold-wall research airplane wing [BASA-TN-D-7860] S75-21673 [BAE-LIB-TBANS-1838] N75-24680 TBABSFOBHATIOBS (HiTBEHATICS) TBABSOBIC SPEED A modern look at conformal mapping, including Low speed injection effects on the aerodynamic doubly connected regions for computerized performance at transonic speed design of airfoil B75-23494 [AIAA PAPEB 75-812] A75-33936 Effect of canard position and wing leading-edge TBABSIBBT OSCILLATIONS flap deflection on wing buffet at transonic speeds Surge and rotating stall in axial flow [BASA-TB-X-72681] N75-23559 compressors. I - Theoretical compression system Transonic off-design drag and performance of three model mixed-compression axisymmetric inlets [ASHE PAPEB 75-GT-9] A75-31573 [NASA-TH-X-3215] N75-23602 TBABSIEBT BESPOBSE 1BAHSOHIC WIHD TDBHELS Subsonic transient lifting surface aerodynamics Study on the establishment of flow in a wind [AIAA PAPEB 75-758] A75-32689 tunnel functioning by induction YF-16 air induction system design loads associated A75-35811 with engine surge TBABSPOBT AIBCBAFT A75-34111 Lift-fan characteristics selection for 1980-85 TBABSITIOB FLOW V/STOL carrier onboard delivery aircraft Inviscid to turbulent transition of trailing [ASHE PAPEB 75-GT-98] A75-34610 vortices High-capacity transport planes as modern air [AIAA PAPEB 75-883] A75-33965 freight systems TBABSONIC FLIGHT [NASA-TT-F-16396] B75-23533 On some problems encountered in a theoretical Computer program to assess impact of fatigue and study of the external flow over a nozzle fracture criteria on weight and cost of configuration in transonic flight transport aircraft S75-23199 [NASA-CB-132648] B75-21718 Flight service evaluation of PBD-19/epoxy composite panels in wide-bodied commercial transport aircraft [BASA-CB-132647] B75-24719 A-31 SUBJECT IBDEI D.S.S.B. SPICE PBOGBAH TBAHS7EBSE OSCILliTIOB IOBBOJET EBGIBES The drag and oscillating transverse force on The multi-mission Birage F vibrating cylinders doe to steady fluid flow 475-33832 i75-35765 An application of modern control theory to jet TDHIHG propulsion systems considering onboard Influence of distuning on rotor-blade vibrations computer A7S-33483 [BASA-TB-X-71726] H75-23573 TOBBIHE BLADES Development of impact resistant boron/aluminum Influences of manufacturing tolerances and surface composites for turbojet engine fan blades roughness at blades on the performance of turbines [HASA-CB-134770] 875-24747 [ASBE PAPEH 75-GT-35] A75-3U592 TDBBOB1CBIHB BLADES Missile firing tests at stationary targets in A method for calculating flows through plane support of blade containaent design for airfoil lattices aircraft engines A75-34245 [ASBE PAPER 75-GT-47] A75-34604 Trailing edge flows over turbomachine blades and Structural response of fiber composite fan blades the Kutta-Joukowsky condition [ASHE PAPEB 75-GT-78] 475-34627 [ASBE PAPER 75-GT-94] A75-34636 A fracture mechanics approach to turbine airfoil TDBBOHACHIHBBT design Contribution of flight simulation tests to the [ASBE PAPEB 75-GT-79] 475-34628 study of turbomachine control Development of impact resistant boron/aluminum B75-23577 composites for turbojet engine fan blades TDBBOPBOP BBGIBES [SASA-CH-134770] N75-24747 Transmissivity of light - One of the quantities Process evaluation of directionally solidified usable in the diagnostics of oil in a motor SI3Cb reinforced eutectics in turbine blade forn A75-32472 [AD-A0081435] H75-24926 Preliminary study of advanced turboprops for low TOBBIHE EHGIBES energy consumption Review of hamnershock pressures in aircraft inlets [8AS4-TB-X-71740] H75-24739 475-34115 TDBBOSBAFTS High-speed rotor dynamics - An assessment of High-speed rotor dynamics - An assessment of current technology for small turboshaft engines current technology for small turboshaft engines 475-31127 A75-34127 Philosophy, design, and evaluation of soft-mounted Performance development of the Gem turboshaft engine engine rotor systems for helicopter application A75-31130 [ASBE PAPEB 75-GT-28] A75-34586 Turbine Engine Structural Integrity Program /ENSIP/ TOBBDLEBCB EFFECTS A75-3U137 High altitude turbulence encountered by the Experimental results of full scale air-cooled supersonic YF-12A airplane turbine tests A75-35409 [ASBE PAPEB 75-G1-116] A75-34653 Aircraft turbulence encounters during commercial Turbine design and application, volume 3 operations in the vicinity of thunderstorms [HASA-SP-290-VOL-3] B75-24741 475-35418 IOBBIHE WHEELS TORBOLEHT BODHDABY LAYEB Philosophy, design, and evaluation of soft-mounted Random vortex shedding noise of airfoils engine rotor systems 475-32430 475-34130 Sound radiation from a bounded thin inhomogeneous Dynamic simulator for advanced gas turbine engine plate reinforced with N ribs and driven by component tests boundary-layer pressure fluctuations 475-34146 A75-33417 Three dimensional characteristics of turbulent TDHBDLEHT BAKES wakes behind rotors of axial flow turbomachinery Search for the final period of decay of the [ASBE PAPEB 75-G1-1] A75-34566 axisymmetric turbulent wake Rotor burst protection program - Statistics on A75-32439 aircraft gas turbine engine rotor failures that Study of a strongly asymmetric turbulent wake occurred in 0.S. commercial aviation during 1973 behind a profile with upper-surface separation [ASBE PAPEB 75-G1-12] A75-3U575 A75-32954 TOBBOCOBPBESSORS Inviscid to turbulent transition of trailing Surge and rotating stall in axial flow vortices compressors. I - Theoretical compression system [AI4A PAPEB 75-883] A75-33965 model Three dimensional characteristics of turbulent [ASBE PAPEB 75-GT-9] A75-34573 wakes behind rotors of axial flow turbomachinery Study on the mechanism of stall margin improvement [ASBE PAPEB 75-GT-1] 475-34566 of casing treatment of low speed axial flow The drag and oscillating transverse force on compressors vibrating cylinders due to steady fluid flow [ASBE PAPEB 75-GT-13] 475-31576 475-35765 Propagating stall in compressors with porous walls Aerodynamics of rotors *- Rake equilibration [ASBE P4PEB 75-61-59] 475-31612 475-35814 A study of casing treatment stall margin Experimental study of the effect on span loading improvement phenomena for axial compressor on aircraft wakes rotor blade tips [HASA-TB-X-62431 ] H75-23479 [ASBE PAPEB 75-GT-60] 475-34613 Turbulent wake behind a self-propelled body TOBBOFAB EBGIHES [AD-4008417] B75-24690 Begenerative turbofans - A comparison with TWO DIBBBSIOBAL FLOB nonregenerative units aircraft engine Use of numerically generated body-fitted performance coordinate systems for solution of the 475-33438 Bavier-Stokes equations P100 fan stall flutter problem review and solution 475-34186 475-31134 Two-diaensional transonic calculations with Development of a high-heat-release combustor for boundary layers the F100 gas turbine 475-35819 [ASBE PAPEB 75-GT-86] 475-34631 B4S4 refan program status for noise reduction of JT8D turbofan engine u [8ASA-TB-I-71705] B75-23570 D.S.S.B. SPACE PBOGBAB tOBBOJEI E16IHE COBTBOI Korolev: 4 chronicle a biography of Sergey Identification of systems by leans of adaptive model Pavlovich Korolev application to jet engines [BASA-TI-F-16278] H75-24654 A75-32473 A-35 ULTBASOHIC TESTS SUBJECT IHDEI ULTRASOHIC TESTS VABIABLE SHEEP IIHGS The effect of water path variations on ultrasonic Variable geometry today latest swing wing through-transmission sensitivity for aircraft adhesively bonded aircraft honeycomb structures A75-33117 A75-34203 The annals of the polymorph - A short history of Evaluation of the reliability and sensitivity of variable geometry. II variable swept wings NOT methods for titanium alloys. Volume 2 A75-33449 [AD-A001604] N75-24923 The annals of the polymorph - A short history of DSCABBBBBD SIHG5 variable geometry. Ill variable wing aircraft Experimental study of heat transfer during flow A75-33450 around uncambered delta wings with blunted edges VELOCITY DISTBIBDTIOB [AD-A007316] H75-2352t Integrated potential formulation of unsteady OHSTEADY FLOI supersonic aerodynamics for interacting wings A rigorous solution of the Ravier-Stokes eguations [AIAA PAPEB 75-762] A75-32693 for unsteady viscous flow at high Reynolds VELOCITY HEiSDBEBEBT numbers around oscillating airfoils Wind tunnel measurements of forward speed effects [AIAA PAPER 75-863] A75-33950 on jet noise from suppressor nozzles and A calculation method for unsteady subsonic flow comparison with flight test data about harmonically oscillating wing-body [AIAA PAPEB 75-870] A75-33957 configurations VERTICAL TAKEOFF AIBCBAFT [AIAA PAPEB 75-861] A75-33951 Jet-induced thermal effects for VIOL aircraft Finite element analysis of unsteady transonic flow [ASHE PAPER 75-GT-96] A75-34638 [AIAA PAPEB 75-875] A75-33960 Ground effects for jet lift VIOL Calculation of the separated flow at a [NASA-TT-F-16359] H75-23480 thin-section wing of finite span VIBBATIOB OAHPIHG A75-34262 The random decrement technique applied to the Extension of the parabolic method for the YF-16 flight flutter tests transonic flow. I - Steady flow. II - Unsteady IAIAA PAPER 75-776] A75-32663 flow Influence of structural damping, preconing offsets A75-35215 and large deflection on the flap-lag-torsional DSUB BAHDALS (COHPOTEB PROGRAMS) stability of a cantilevered rotor blade Computer program to assess impact of fatigue and [AIAA PAPEB 75-780] A75-32667 fracture criteria on weight and cost of YF16 active-control-system/structural dynamics transport aircraft interaction instability [NASA-CR-132618] N75-24718 [AIAA PAPEH 75-823] A75-32695 Airport noise reduction forecast. Volume 2: NEF Active flutter suppression using trailing-edge and computer program description and user's manual tab control surfaces [PB-239388/2] N75-2U772 [AIAA PAPEB 75-822] A75-32697 OSBB BBQDIBEHENTS System identification of a complex structure Autotest user needs at a base shop helicopter gearbox dynamics from shake test data computerized Automatic Test Equipment for [AIAA PAPER 75-809] A75-32705 military avionics Aeroelastic panel optimization with aerodynamic A75-35253 damping Loran-C compared with other navigation aids in A75-33488 meeting future Canadian needs Control of gas turbine stator blade vibrations by A75-35796 means of enamel coatings A75-34116 VIBBATIOB HEASDBBHEHT Natural oscillations of liquid in a horizontal 7/STOL AIBCB1FT container with symmetric double-connected cross Becent advances in in-flight simulator technology section 475-33187 [AD-A007312] B75-23906 Lift-fan characteristics selection for 1980-85 VIBRATIOH BODE V/STOL carrier onboard delivery aircraft Vibration analysis of multi-symmetric structures [ASME PAPER 75-G1-98] A75-3<46<10 [AIAA PAPEB 75-808] A75-32706 Correlation of low speed wind tunnel and flight Rapid verification of engine rotor and case test data for V/STOL aircraft flexibilities by a modal comparison algorithm [NASA-TH-X-621123] N75-23557 A75-3H119 Dynamic and aeroelastic problems of stop-rotors VISCODS DAHPIHG and their analytical treatment. Part 2: Dynamic response of viscous-damped multi-shaft jet Analytical equations and solutions V/STOL engines aircraft A75-34128 [ESBO-TT-145-PT-2] N75-24683 VISCOUS FLOB NASA/Army XV-15 tilt rotor research aircraft A rigorous solution of the Navier-Stokes eguations familiarization document for unsteady viscous flow at high Reynolds [SASA-TH-I-62107} B75-21720 numbers around oscillating airfoils TIDES [AIAA PAPEB 75-863] A75-33950 Design and analysis of a ceramic stator vane VISOBS [ASHE PAPEB 75-6T-100] A75-31642 A holographic visor helmet-mounted display system ViPOB DEPOSITIOS A75-35283 Ion vapor deposited aluminum improves structure VISDAL OBSEBVATIOH durability airframe corrosion protective A radar and direct visual study of the hazard to coatings aircraft from bird migrations in the southwest [AIAA PAPEH 75-807] A75-32680 [AD-A008198] N75-24699 VAPOBIZIHG VOLTBBBA BQOATIOHS Experimental investigation of a new concept of Problem of supersonic flow past a slender pointed fuel prevaporization for aircraft engine low body with tail emission conbustors A75-35706 [ASSE PAPEB 75-6T-6] A75-34570 TOBTEX BRBAKDOWH VARIABLE GEOMETRY STBDCTDBES Random vortex shedding noise of airfoils The annals of the polymorph - A short history of A75-32430 variable geometry. II variable swept wings Inviscid to turbulent transition of trailing A75-33449 vortices The annals of the polymorph - A short history of [AIAA PAPEB 75-883] A75-33965 variable geometry. Ill variable wing aircraft Experimental study of the effect of span loading A75-33450 on aircraft wakes [AIAA PAPEB 75-885] A75-33967 Vortex development and breakdown [AIAA PAPER 75-881] A75-35172 i-36 SUBJECT IIDBI illD TOII1L TESTS Wake vortex decay near the ground HEDGE PLOB [AIAA PAPEH 75-882] A75-35173 The problem of diffraction of a strong VOBTBX SHEETS magnetogasdynamic shock wave by a wedge Theoretical study of lift-generated vortex Hakes A75-32518 designed to avoid rollap General analysis of the diffraction pattern for a 175-33185 plane acoustic wave at a wedge moving at A three-dimensional solution of flovs over vings supersonic speed Kith leading-edge vortex separation A75-34272 [AIAA PiPEH 75-866] A75-33953 BBDGBS Calculation of the separated flow at a Interaction of shock wave with wedge, which moves thin-section wing of finite span at supersonic speed A75-34262 [AD-A007302] H75-23S19 VOBTEI STBBETS HEIGHT ABALTSIS Airborne wake vortex detection by in-flight Applications of a quadratic extended interior radar sensing penalty function for structural optimization A75-35425 [AIAA PAPEB 75-764] A75-32654 VOBI1CES HEIGHT HBASOBEBEHT Some wind tunnel measurement of the trailing Flight test for the feasibility evaluation of the vortex development behind a sweptback wing - Chadwicc Electronic feighing System (CBEHS) Induced rolling moments on intercepting vings [AD-A007516] S75-23522 [AIAA PAPEB 75-884] A75-33966 HEIGHT BEDDCTIOH Ground vortex - limit to engine/reverser operation Binimnm weight design of the F-15 empennage for for high bypass ratio engine flutter [ASHE PAPEB 75-6T-3] A75-34567 [AIAA PAPEB 75-777] A75-32664 Rind-tunnel tests and computer simulations of Boron/aluminum for advanced technology aircraft buoyant wing-tap vortices cost and weight advantages A75-35422 [AIAA PAEEB 75-790] A75-33762 A predictive model of wake vortex transport Fracture failure modes in lightweight bearings A75-35423 A75-34140 The motion of wake vortices in the terminal RELDIHG environment Design of fabricated static structures for long A75-35424 cyclic life Analysis of wake vortex flight test data behind a A75-34142 T-33 aircraft HIDBBAHD COBHDHICATIOH [BASA-CB-137669] H75-23482 Small antennas fractional wavelength design Summary of HIT research on dynamic stall and for wideband applications blade-vortex interaction, 1971 - 1971 A75-35827 [AD-A008091] N75-24689 HIBD EFFECTS VOLBEBABILITT The influence of wind shear on aerodynamic Fuel tank non-nuclear vulnerability test program coefficients [AD-A008531] H75-24728 A75-35411 Aeronautical requirements and procedure for low-level turbulence and wind shear reporting w A7S-35414 IAKES Rind shear effects on landing touchdown point Velocity and rolling-moment measurements in the A75-35420 wake of a svept-wing model in the 40 by 80 foot BIHD PBOFILES wind tunnel Rind shear effects on landing touchdown point [HASA-TH-X-62414] H75-23481 A75-35420 Analysis of wake vortex flight test data behind a A predictive model of wake vortex transport T-33 aircraft A75-35423 [HASA-CB-137669] N75-23482 HIBD SBEAB RILL PLOH The influence of wind shear on aerodynamic A theoretical analysis for three dimensional ram coefficients wings in parallel walls A75-35411 A75-33427 Aeronautical reguirements and procedure for BATES FIOH low-level turbulence and wind shear reporting The effect of water path variations on ultrasonic A75-35414 through-transmission sensitivity for Rind shear effects on landing touchdown point adhesively bonded aircraft honeycomb structures A75-35420 A75-34203 The effects of atmospheric stability, turbulence, HATE DIPFRACTIOi and wind shear on aircraft wake behavior The problem of diffraction of a strong A75-35426 magnetogasdynamic shock wave by a wedge RIBD TDHBBL BODBLS A75-32518 Twin jet exhaust system test technigues 1ATB IHCIDEHCE COHTBOI integrating airframe and propulsion system for Interaction of shock wave with wedge, which moves wind tunnel models at supersonic speed N7 5-23500 [AO-A007302] H75-23519 The 727 airplane target thrust reverser static 1BAPOS SISTERS performance model test for refanned JT8D engines The multi-mission Hirage F [NASA-CB-134652] 1175-24737 A75-33832 HIBD TOHHBL STABILITY TESTS Reliability and maintainability allocation for Experimental study of the effect of span loading avxonic maintenance optimization on aircraft wakes A75-35252 [AIAA PAPEB 75-885] A75-33967 HEAR large-scale Kind-tunnel tests of three vehicles Increasing the wear resistance of aircraft parts incorporating a deployable rigid wing [SASA-TT-F-15759] N75- 24723 aircraft design of rectangular wings using BBAB IHHIBITOBS aircraft models and wind tunnel stability tests Influence of protective additions on the anti-wear [NASA-TH-X-62405] H75-24671 properties of jet fuels RIBD TOBHEL TESTS A75-35298 Search for the final period of decay of the Application of thin-layer chromatography for axisyometric turbulent wake determining the wearing capacity of additives A75-32439 contained in petroleum-based aviation oils Study of a stcongly asymmetric turbulent wake A75-35300 behind a profile with upper-surface separation A75-32954 A-37 HID TELOCITY BBASOBBBBBT SUBJECT IHDBZ gaximui lift of opper surface bloving STOL Theoretical and experimental research on the aircraft with svept wings fatigue crack propagation in stiffened panels, [AIAA PAPBB 75-868] 175-33955 an evaluation of the Paris theory Hind tnnnel measurements of forward speed effects [AD-A008079] B75-21732 on jet noise from suppressor nozzles and BIBG PLABFOBBS comparison with flight test data Effect of wing planfora and canard location and [AIAA PAPBB 75-870] A75-33957 geometry on the longitudinal aerodynamic Transonic flow about a thick circular-arc airfoil characteristics of a close-coupled canard wing [illi PAPEB 75-878] A75-33962 model at subsonic speeds Supercritical airfoil flowfield measurements [BASA-TB-D-7910] B75-23511 [AIAA PAPER 75-880] A75-33961 BIBG PROFILES Some wind tnnnel measurement of the trailing A theoretical analysis for three dimensional ram vortex development behind a sveptback wing - wings in parallel walls Induced rolling moments on intercepting wings A75-33127 [AIAA PAPER 75-881] A75-33966 Supercritical wing sections II: A handbook Rind tnnnel tests for the deternination of the numerical computations behavior of aircraft external loads which are A75-31975 dropped Rind tunnel test of a flutter suppressor on a A75-35098 straight wing Rind-tunnel tests and computer simulations of [OBERA, IP BO. 1975-31] A75-35869 buoyant wing-tip vortices RIBG SPAB A75-35122 Experimental study of the effect on span loading Comparison of flight and wind tunnel tests of an on aircraft wakes executive airplane [BASA-TB-X-62131] H75-23179 A75-35806 RIBG TIPS Interaction of jets of SB CP6-50 reactors with the Rind-tunnel tests and computer simulations of wing cellules of the airbus during cruise - buoyant wing-tip vortices Rind-tunnel simulation A75-35122 A75-35808 HIBG-FDSELAGB STOBES Rind tunnel test of a flutter suppressor on a Prediction of the optimum location of a nacelle straight wing shaped body on the wing of a wing-body [ONEBA, TP NO. 1975-31] A75-35869 configuration by inviscid flow analysis Isolating nozzle afterbody interaction parameters H75-23510 and size effects: A new approach flight and RIBGS wind tunnel tests with A 7 aircraft A calculation method for unsteady subsonic flow 1175-23503 about harmonically oscillating wing-body Reynolds number effects on boattail drag of configurations exhaust nozzles from wind tunnel and flight tests [AIAA PAPEB 75-861] A75-33951 H75-23506 Surface finishing particularly for use in Airframe: Engine interaction for engine smoothing irregularities on aluminum aircraft configurations mounted above the wing. Part 2: wings Engine jet simulation problems in wind tunnel [BASA-CASE-BSC-12631-1] B75-23176 tests Detailed experimental and theoretical analysis of 1175-23512 the aerodynamic interference between lifting Correlation of low speed wind tunnel and flight jets and the fuselage and wing test data for V/STOL aircraft H75-23509 [NASA-TB-X-62123] 1175-23557 Airframe: Engine interaction for engine BIND VELOCITY BBASOBEBBBT configurations mounted above the wing. Part 1: Surface wind speed range as a function of time Interference between wing and intake jet interval and mean wind speed N75-23511 A75-35113 Account of shearing strain during the calculation RIBG FLAPS of the oscillations of low aspect-ratio wing by Effectiveness of spoilers on the GA(R)-1 airfoil the method of polynomials with a high performance Fowler flap [AD-A007397] B75-23518 [HASA-CB-2538] H75-23481 Hethod of the optimization of the load-carrying RIBG LOADIBG structure of wing on rigidity during variation £ three-dimensional solution of flows over wings by the distribution of thickness ratio with leading-edge vortex separation [AD-A007317] 1175-23521 [AIAA PAPER 75-866] A75-33953 Ring longitudinal stability criteria Experimental study of the effect of span loading [AD-A007130] 875-23527 on aircraft wakes Computer-augmented design of aircraft wing [AIAA PAPER 75-865] A75-33967 structures Interaction of jets of GE CF6-50 reactors with the 1175-23551 wing cellules of the airbus during cruise - Hind-tunnel simulation A75-35808 Experimental study of the effect on span loading X BAT ABALISIS on aircraft wakes Development of real time high energy X-ray imaging [NASA-TH-X-62131 ] 1175-23179 system for use in dynamic fluoroscopy of aero RIBG OSCILLATIOBS gas turbines Drag effects on wing flutter [ASBE PAPEB 75-GT-117] A75-31651 [AIAA PAPER 75-775] A75-32662 1-5 AIBCBAFT Oscillatory supersonic lifting surface theory The annals of the polymorph - A short history of using a finite element doublet representation variable geometry. II variable swept wings [AIAA PAPER 75-761] A75-32692 A75-33119 A perturbation method for transonic flows about oscillating airfoils [AIAA PAPER 75-877] A75-35171 RIBG PABBLS TAR Hypersonic wing test structure design, analysis, Side forces on unyawed slender inclined and fabrication aerodynamic bodies [AIAA PAPER 75-785] A75-32670 A75-33435 Evaluation of bead-stiffened metal panels for TF-12 AIBCBAFT hypersonic aircraft and space systems design High altitude turbulence encountered by the [AIAA PAPER 75-815] A75-32701 supersonic TF-12A airplane Design and fabrication of Rene 11 advanced A75-35109 structural panels their performance under YIELD STBBBGTB axial compression, shear, and bending loads Formation of flexibility matrices of a structure [HASA-CB-132616] 1175-21032 based on known yields at arbitrary points A75-32995 A-38 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING /A Special Bibliography (Suppl 61) SEPTEMBER 1975 Typical Personal Author Index Listing PERSONAL AUTHOR CIVIBSKAS. K. A comparison of optimuu JP and LH2 turbofan ABHOLDI, B. A. engines designed for tvo subsonic transport Advances in fan and compressor blade flutter it missions analysis and predictions [NASA-TB-X-71622] N75-109U5 A75-31131 &BIHOBS, T. D. I Interaction between control augmentation system I and airframe dynamics on the YF-17 TITLE REPORT [AIAA PAPEB 75-821] A75-3269U NUMBER &SATUBIAH, A. SB. A method for calculating flows through plane airfoil lattices A75-3U2U5 Listings in this index are arranged alphabetically by personal author The title ASHLEY, H. of the document provides the user with a brief description of the subject matter Drag effects on wing flutter The report number helps to indicate the type of document cited (eg NASA [AIAA PAPE8 75-775] A75-32662 report translation NASA contractor report} The accession number is located ATENCIO, A., JB. Wind tunnel measurements of forward speed effects beneath and to the right of the title eg N75-10945 Under any one author s on jet noise from suppressor nozzles and name the accession numbers are arranged in sequence with the IAA accession comparison with flight test data numbers appearing first [AIAA PAPER 75-870] A75-33957 ATKET, E. H. The 727 airplane target thrust reverser static performance model test for refanned JT8D engines [NASA-CR-131652] N75-21737 AABHES, H. H. ATTBI, 8. S. Propulsion system and airframe structural Test and performance criteria for airplane integration program antiskid systems 475-31118 [AD-A008536] N75-21730 AAS, H. G. iOLEHLA, F. Nondestructive holographic techniques for Reynolds number effects on fore- and aftbody structures inspection pressure drag [AD-A007850] H75-23946 S75-23197 ABBETT, H. J. 4ZATIAB, L. D. Computational procedure for three-dimensional The problem of diffraction of a strong boundary layers on aircraft and aerospace vehicles magnetogasdynamic shock wave by a wedge A75-31190 A75-32518 SBDiLLA, K. L. AZOBA, A. NASA refan program status Local momentum theory and its application to the [NASA-TH-X-71705] S75-23570 rotary wing AHMED, S. B. [AIAA PAPEB 75-865] A75-33952 Prediction of the optimum location of a nacelle shaped body on the wing of a King-body configuration by inviscid flow analysis B N75-23510 BABKIH, V. S. AKIN, J. t. Determination of surface roughness of materials Rapid verification of engine rotor and case A75-33331 flexibilities by a modal comparison algorithm BADGLEY, B. B. A75-3»119 Dynamic simulator for advanced gas turbine engine AKSO, H. component tests A rigorous solution of the Navier-Stokes eguations A75-3U1U6 for unsteady viscous flow at high Reynolds BAILEY, H. E. numbers around oscillating airfoils Computation of noneqnilibrium three-dimensional [AIAA PAPEB 75-863] 475-33950 iDviscad flow over blunt-nosed bodies flying at ALBAHO, B. D. supersonic speeds A perturbation method for transonic flows about [AIAA PAPEB 75-835] A75-33931 oscillating airfoils BAKEB, J. B. [AIAA PAPER 75-877] A75-35171 Laboratory testing of co'ntrols for aircraft ALEKSEBVA, B. P. turbine engines Changes in the properties of hydrogenated fuels [ASBE PAPEB 75-GT-101] A75-346<43 during prolonged storing BALABIS, C. A. A75-35299 Analysis and design of aircraft antennas AHDEBSOH, B. B. [NASA-CH-1U29«5] H75-25057 Implications of equipping a DC-8-61 fleet with BALL, i. H. BHAV/two-segment approach avionics Accounting of aerodynamic forces on [HASA-CB-137680] B75-2351U airfraoe/propulsion systems 10TAGI, K. H75-23507 Baxiinn lift of upper surface blowing STOL BALLBSBEBGBB. •. B. aircraft with swept wings On the way to tactical aircraft robotics [AIAA PAPEB 75-868] A75-33955 A75-32Q52 APPA, K. BALLBABH, 3. Integrated potential formulation of unsteady Integral equations for the calculation of the flow supersonic aerodynamics for interacting wings about accelerated slender bodies for B greater, [AIAA PAPEB 75-762] A75-32693 equal, or less than 1 A75-3520Q B-1 B4HHEBT, R. PEBSOHAL AOTHOB IHDEX BAHHBBT, K. BEHDEB, H. A. Influences of manufacturing tolerances and surface Digital flight control systems for tactical roughness of blades on the performance of turbines fighters. Volume 3. Digital flight control [ASHE PAPER 75-GT-35] A75-34592 system design consideration BAHDETTINI, A. [AD-A002687] H75-2t754 Supercritical airfoil flowfield measurements Digital flight control system for tactical fighters [AIAA PAPEB 75-880] A75-33964 [AD-A002686] N75-21757 BABBIEB, A. BEHHEKEBS, B. Titanium casting - Industrial development - A calculation method for unsteady subsonic flow Economic aspects about harmonically oscillating wing-body A75-35159 configurations BABCLAT, P. A. [AIAA PAPEB 75-864] A75-33951 Aircraft turbulence encounters during commercial BEHTZ, C. S. operations in the vicinity of thunderstorms The role of computers in future propulsion controls A75-351H8 N75-23582 BABLOi, G. C. BBBHAH, A. Development of a high-heat-release combustor for System identification of a complex structure the F100 gas turbine [AIAA PAPEB 75-809] A75-32705 [ASHE PAPEB 75-GT-86] A75-34631 BEBBY, B. A. BARHBBLI, B. R. The flutter analysis of T-tails Analysis of transonic flow about lifting wing-body [AIAA PAPEB 75-759] A75-32690 configurations BESIGK, G. [NASA-TB-R-440] N75-21681 Reynolds number effects on fore- and aftbody BABONTI, P. pressure drag Besponse of a light aircraft to a thermal exhaust H75-23497 plume BIL1ISGSLEY, J. C. A75-35403 Droplet diameter and size distribution of JP-4 BABBOH, R. A. fuel injected into a subsonic airstream Jet-induced thermal effects for VTOL aircraft [AD-A007687] N75-24192 [ASME PAPEB 75-GT-96] A75-3U638 BLAHCBABD, B. BABTEL, C. Automated test facility for aircraft hydraulic Airport noise reduction forecast. Volume 1: pumps and motors Summary report for 23 airports A75-32397 [PB-239387/1] N75-2H771 BLICKEHSTAFF, J. Airport noise reduction forecast. Volume 2: NEF Fuel tank non-nuclear vulnerability test program computer program description and user's manual [AD-A008531] B75-24728 [PB-239388/2] N75-2U772 BOGBAHI, A. B. BAOEB, F. Dynamic heave-pitch analysis of air cushion Computer simulation of transonic flow past landing systems airfoils with boundary layer correction [HASA-CB-2530] H75-24721 A75-31196 BOBOH, B. L. Supercritical wing sections II: A handbook Evaluation of bead-stiffened metal panels A75-31975 [AIAA PAPEB 75-815] A75-32701 BADEBFEIHD, K. BOLLIHGEB, R. PRAC: A new aero gas turbine engine control concept Flight test for the feasibility evaluation of the N75-2358U Chadwick Electronic Weighing System (CHEHS) BAYNE, B. 1. [AD-A007516] N75-23522 Performance development of the Gem turboshaft engine BOHBETT, R. S. [ASME PAPEB 75-GT-28] A75-31586 Computational procedure for three-dimensional BAZABHOVA, H. H. boundary layers on aircraft and aerospace vehicles Experimental investigation of friction on a plate A75-3U190 in the flow of a rarefied gas BOBGEB, R. D. A75-33346 Practical stability of a reluctance synchronous BEACH, H. L. machine Subscale, hydrogen-burning, [AD-A007659] 1175-23605 airframe-integrated-scramjet: Experimental and BODSQOET, J. theoretical evaluation of a water cooled strut Two-dimensional transonic calculations with airframe-integrated-scramjet: Experimental boundary layers leading edge A75-35819 [HASA-TH-X-72682] N75-23885 BOREB, G. H. BF.AHS, E. R. Cargo aircraft - A look toward the future A design study of a fan augmented ramjet A75-35290 [ASHE PAPEB 75-G1-97] A75-3M639 BBACE, B. L. BBASLBY, 8. D. HOD - An important new aid to the L.S.O Low-speed aerodynamic characteristics of a A75-33620 13-percent thick airfoil section designed for BBADLEY, B. general aviation applications High temperature tests of a JP-5 type fuel [NASA-TH-X-72697 ] H75-2<4678 [AD-A007662] H75-23603 BBASOB, B. C. BBASBEABS, H. B. A radar and direct visual study of the hazard to Finite element analysis of unsteady transonic flow aircraft from bird migrations in the southwest [AIAA PAPEB 75-875] A75-33960 [AD-A008198] 875-21699 A predictive model of wake vortex transport BEATTY, I. D. A75-35M23 An inverse method for the design of multielement BBASS, J. high-lift systems Besponse of aircraft structural compartments to [AIAA PAPEB 75-879] A75-33963 blast pressures and fragments from high BEADLIEO, R. D. explosive projectiles Beview of hammershock pressures in aircraft inlets [AIAA PAPEB 75-751] A75-32652 A75-3U115 BBATABOR, T. BEBBEBT, B. A rigorous solution of the Havier-Stokes equations Ground effects for Jet lift VTOl for unsteady viscous flow at high Beynolds [HASA-TT-F-16359] H75-23U80 numbers around oscillating airfoils BELOTSEBKOVSKII, S. H. [AIAA PAPEB 75-863] A75-33950 Calculation of the separated flow at a BBATBBOOK, B. H. thin-section wing of finite span Variable geometry today A75-34262 A75-33447 B-2 PBBSOBAL ADIHOB IBDBI CLABK, J. C. BHAZIBB, H. E. CABBAH, 3. B., JB. Accounting of aerodynamic forces on An investigation of the flow field of the A-7D airframe/propulsion systems aircraft with several external store loadings at B75-23507 Bach numbers 0.70 and 0.95 BBIGHAC, B. J. [AD-A008476] H75-21688 The random decrement technique applied to the CABBB, J. P. Y?-16 flight flatter tests Research about effects of external flow and [AIAA PiPEB 75-776] A75-32663 aircraft installation conditions on thrust BBIHOLE. J. H. reversers perfornances A holographic visor helmet-mounted display systea B75-23495 A75-35283 CASTES, B. C. BROCK, B. 3. The measurement of the transonic spillage drag of The supersonic doublet-lattice method - A a supersonic intake comparison of two approaches B75-23088 [AIAA PAPEB 75-760] A75-32691 CARTBRIGHT, E. 0. BBOOK, B. B. Safezone escape alert system development program. A stndy of self-siHilarity in boundary layer Phase 1: Systea development turbulence and its relevance to aircraft design [AD-A008561] B75-21733 and operation CAYAGB, B. I. A75-35419 Lift-fan characteristics selection for 1980-85 BBOiB, D. E. V/ST01 carrier onboard delivery aircraft Reliability and maintainability allocation for [ASHE PAPER 75-GT-98] A75-316UO avion1C maintenance optimization CBABBEBLIH, B. A75-35252 Beynolds number effects on boattail drag of BHOBB, G. S. exhaust nozzles from wind tunnel and flight tests A three-dimensional solution of flows over vings B75-23506 with leading-edge vortex separation CBAHIS, C. C. [AIAA PAPER 75-866] A75-33953 Analytical displacements and vibrations of BBOHSCHB, K. cantilevered unsymmetric fiber composite laminates Design of composite structure with respect to [AIAA PAPEB 75-757] A75-32688 avoid crack propagation Structural response of fiber composite fan blades H75-23709 [ASBE PAPEB 75-GT-78] A75-3«627 BBOSSE, J. CBAH, S. T. K. Improvement of propeller static thrust estimation Finite element analysis of unsteady transonic flow [NASA-CR-132680] N75-23567 [AIAA PAPEB 75-875] A75-33960 BUCH, A. CHAHG, J. B. Fatigue properties of aircraft lugs with Analytical prediction of fatigue crack growth at interference fit cold-worked fastener holes [TAE-213] H75-2U031 [AIAA PAPEB 75-805] A75-33763 BOCHBR, I. CHATTOT, J. J. High temperature tests of a JP-5 type fuel Theory of mixing flow of a perfect fluid around an [AD-A007662] N75-23603 afterbody and a propulsive jet BDHKOV, V. G. N75-23493 Account of shearing strain during the calculation CBAQKIB, J. a. of the oscillations of low aspect-ratio wing by Safety-related engineering and development the method of polynomials activities of the Federal Aviation Administration [AD-A007397] H75-23518 [AD-A008395] H75-2<4698 BOBKHiRT, T. B. CBBBG, D. T. Subsonic transient lifting surface aerodynamics Beversed cowl flap inlet thrust augmentor [AIAA PAPEB 75-758] A75-32689 [NASA-CASE-ABC-1075U-1] N75-24736 BORT, J. B., JR. CBEBBOVA, K. S. An experimental investigation of the aerodynamic Application of thin-layer chromatography for characteristics of several nose mounted canard determining the wearing capacity of additives configurations at supersonic Bach numbers contained in petroleum-based aviation oils [AD-A007793] N75-23526 A75-35300 BORBOOD-SHITH, A. CHILD, B. D. Materials for gas turbines Design and analysis of a supersonic A75-32839 penetration/maneuvering fighter [HASA-CB-132633] B75-23558 CHBTB, G. I. A method for calculating flows through plane CABOT, L. airfoil lattices Some problems posed by the aerodynamics of the A75-312U5 dirigible balloon CHOBT, D. A. A75-35810 Transonic off-design drag and performance of three CALLABAB, C. J. mixed-compression axisymmetric inlets An experimental investigation of the component [HASA-TH-X-3215] N75-23602 drag composition of a two-dimensional inlet at CHOI, C. I. P. transonic and supersonic speeds The 727 airplane target thrust reverser static N75-23*89 performance model test for refanned JT8D engines CAHBON, C. B. [NASA-CR-13U652] H75-21737 Control of gas turbine stator blade vibrations by CHOBSHDKOT, E. S. means of enamel coatings Influence of protective additions on the anti-wear 475-31116 properties of jet fuels CAPTAIB, K. B. A75-35298 Dynamic heave-pitch analysis of air cushion CICOLAHI, I. landing systems A formal structure for advanced automatic [NASA-CB-2530] N75-21721 flight-control systems CABDBB, B. K. [NASA-TB-D-79UO] B75-23606 Light aircraft lift, drag, and moment prediction: CIFFONE, D. L. A review and analysis Experimental study of the effect of span loading [NASA-CR-2523] N75-21677 on aircraft wakes CABLSOH, L. A. [AIAA PAPEB 75-885] A75-33967 Transonic airfoil analysis and design using Experimental study of the effect on span loading Cartesian coordinates on aircraft wakes A75-3t195 [NASA-Tn-Jt-621131] B75-23179 CLABK, J. C. Fracture failure modes in lightweight bearings A75-31110 B-3 CLBT1IGBB. 8. B., JB. PBBSOHAL AUTHOB I8DEI CLBTB1SBB, B. B., JB. COilE, 8. D. The dynamics of atmospheric dust particles in Turbine Engine Structural Integrity Program /EMSIP/ aircraft auxiliary power radial inflow turbines A75-34137 [AIAA PAPEB 75-844] A75-33938 CBAIE, J. F. I. CLBTBBSO*. S. A. The subsonic base drag of cylindrical twin-jet and A study of helicopter interior noise redaction single-jet afterbodies [NASA-TB-I-72655] H75-23556 875-23498 COCKSHOTT, B. P. COSPSTI, B. A. Bquilibrian performance analysis of gas turbine Excess noise from gas turbine exhausts engines using influence coefficient techniques [ASHE PAPEB 75-GT-61] A75-34614 H75-23592 CDBDIFF, B. A. COFFIH, B. D. Dynamic simulator for advanced gas turbine engine Hew Air Force requirements for structural safety, component tests durability and life management A75-34146 [AHA PAPEB 75-781] A75-32668 COBBAB, P. H. COBS, D. B. Process evaluation of directionally solidified Analysis of technology requirements and potential HI3Cb reinforced eutectics in turbine blade forn demand for general aviation avionics systems in [AD-A008435] N75.-24926 the 1980's CIGNOB, J. B. [NASA-CR-137629] H75-24735 Advanced engine mounted fuel pump technology COLEBABK, J. H. H7 5-23601 Automatic test equipment for S-3A support A75-35279 COLES, A, Design of fabricated static structures for long DAHFORTH, C. B. cyclic life Blade vibration - Some key elements in design A75-34142 verification COLVIH, e. L. A75-34132 Bell Belicopter/NASi/Army XV-15 status report DABLIBGTOB, C. B. A75-33617 Droplet diameter and size distribution of JP-4 COHPTOH, H. A. fuel injected into a subsonic airstream Temperature measurement for advanced gas turbine [AD-A007687] B75-24192 controls DAVIDSOH, B. E. N75-23597 Rind-tunnel tests and computer simulations of COHPTOB, ». B., Ill buoyant wing-tip vortices An experimental study of jet exhaust simulation A75-35422 N75-23501 DAVIDOVA, B. A. COOK, I. L. Experimental study of heat transfer during flow Correlation of low speed wind tunnel and flight around uncambered delta wings with blunted edges test data for V/STOL aircraft [AD-A007316] N75-23524 [NASA-TH-X-62423] H75-23557 DBIBBBT, G. S. COOHBBS, T. D. Transonic flow about a thick circular-arc airfoil A model technique for exhaust system performance [AIAA PAPER 75-878] A75-33962 testing DBLEBI, J. N75-23502 Effect of external conditions on the functioning COOHBS, C. K. of a dual flow supersonic nozzle Design of fabricated static structures for long N75-23491 cyclic life DELDCIA, B. A. A75-34142 Rotor burst protection program - Statistics on COBSIGLIA, V. B. aircraft gas turbine engine rotor failures that Experimental study of the effect of span loading occurred in U.S. commercial aviation during 1973 on aircraft wakes [ASBE PAPEB 75-GT-12] A75-34575 [AIAA PAPEB 75-885] A75-33967 DBBICBEHOHT, G. Experimental study of the effect on span loading Effect of external conditions on the functioning on aircraft wakes of a dual flow supersonic nozzle [NASA-TM-X-62431] H75-23479 H75-23491 Velocity and rolling-moment measurements in the DESIDYHDEK, B. wake of a swept-wing model in the 40 by 80 foot Wind tunnel test of a flutter suppressor on a wind tunnel straight wing [NASA-TH-X-62414 ] N75-23481 [ONEBA, IP NO. 1975-31] A75-35869 COSEL, B. H. DBYAB, L. PAA lightning protection study: Lightning An estimate of the effect of multiple ejection protection requirements for AIL type 55 K rack flexibility on six degree of freedom store instrument landing system ejection conditions [AD-A008931] N75-23530 [AD-A008329] N75-24734 COSTBH, B. C. DIEEBERGEE, J. Wind-tunnel tests and computer simulations of A fracture mechanics approach to turbine airfoil buoyant wing-tip vortices design A75-35422 [ASHE PAPEB 75-GT-79] A75-34628 COTTIHGTOH, B. V. DIETBICB, D. A. Total powerplant simulation Effect on fan flow characteristics of length and N75-23594 axial location of a cascade thrust reverser CODGHLIB, C. [NASA-TM-X-3247] S75-24745 Airport noise reduction forecast. Volume 2: NEF DIHI, 0. computer program description and user's manual Fluidic sensors for turbojet engines [PB-239388/2] N75-24772 H75-23598 CODIHY, G. DINI, J. i. Aerodynamics of lifting and propulsive systems in Chemical milling a periodically functioning regime - Optimization A75-32840 of their performance DOHEBB, K.-F. A75-35815 Parachute systems of the DFVLR for stabilization CODLDBIS, G. J. and salvage of flight vehicles Air traffic controllers' operative effectiveness [DGL8 PAPEB 74-043] A75-34661 under HAS environments DBEES, B. H. A75-34539 The development of experimental techniques for the CODBJABEI, B. study of helicopter rotor noise Aerodynamics of rotors - Hake eguilibration [NASA-CS-137684] H75-23611 A75-35814 B-4 PEBSOBSL iOTBOB IHDEX PBOST, 8. DOBBIBSKII, V. P. The An-2 aircraft /1th revised and enlarged edition/ A75-35350 DOFFT, 1. E. FABHIB, E. B. Temperature measurement for advanced gas turbine Ion vapor deposited aluminum improves structure controls durability H75-23597 [AIAA PAPEB 75-807] A75-32680 FiSHIBG, A. E. Twin jet exhaust system test techniques 1175-23500 EJB1, D. G. PiBTIBO, B. E. Some wind tunnel measurement of the trailing Effects of asymmetry on the dynamic stability of vortex development behind a sweptback wing - aircraft Induced rolling moments on intercepting wings [NASA-CB-1U2857] B75-21756 [AIAA PAPEH 75-880] A75-33966 FABQOHAB, B. R. EATOH, B. H. The refracting inlet - A new concept for aircraft Loran-C compared with other navigation aids in inlet noise suppression meeting future Canadian needs [ASBE PAPEB 75-GT-21] A75-3<4580 A75-35796 FABB, J. I., JB. EBEBSOLT, H. A perturbation method for transonic flows about Studies and research on marine hulls working with oscillating airfoils natural ground effect [AIAA PAPEB 75-877] A75-35171 B75-23175 PEHLEB, A. EDBOBD, B. J. Experimental investigation of a new concept of Analysis of distress air cases in relation to fuel prevaporization crash position and intended track. 1968 - 1973 [ASBE PAPEB 75-GT-6] A75-31570 [AD-A007129] B75-23510 FEHBE8KAHP, L. G. EGOLP, T. A. Surface finishing Prediction of rotor wake induced flow along the [BASA-CASE-BSC-12631-1 ] B75-23176 rocket trajectories of an Army AH-1G helicopter FEISTEL, T. I. [AD-A007878] H75-23528 Large-scale wind-tunnel tests of three vehicles EHBBBBBBGEB, L. J. incorporating a deployable rigid wing High altitude turbulence encountered by the [BASA-TB-X-62105] N75-21671 supersonic IF-12ft airplane FEEHEBBEBG, A. J. A75-35109 Fuel tank non-nuclear vulnerability test program EL-BAYOOHY, L. E. [AD-A008531] N75-21728 Influence of mistuning on rotor-blade vibrations FIHDLBY, D. S. A75-33183 Vibration responses of test structure no. 1 during EL-HATAH, B. T. A. the Edwards Air Force Ease phase of the national Statistical analysis of the functioning quality of sonic boom program regulators with random parameter scatter [BASA-TH-X-72706] 875-21711 A75-32171 FLICK, E. A. BL-BABLY, Z. A means of dynamic control of radar reflectivity Some wind tunnel measurement of the trailing of an antenna or other object by means of a vortex developnent behind a sweptback wing - gaseous plasma shroud Induced rolling moments on intercepting wings A75-31851 [AIAA PAPEB 75-881] A75-33966 FOEBSCHISG, B. ELBEB, 1. Dynamic and aeroelastic problems of stop-rotors Crack growth under spectrum loading: A crack and their analytical treatment. Part 2: closure model Analytical equations and solutions [NASA-TH-X-72708 ] H75-25221 [ESBO-TT-115-PT-2] B75-21683 BBGLIH, B. A. FOBSHAB, S. E. Changes in the properties of hydrogenated fuels CF5D aircraft cockpit-noise reduction during prolonged storing [DCIEH-7U-B-1018] B75-2356U A75-35299 FBEDIABI, A. EBF, B. K. Theoretical and experimental research on the Nondestructive holographic techniques for fatigue crack propagation in stiffened panels, structures inspection an evaluation of the Paris theory [AD-A007850] H75-23916 [AD-A008079] B75-21732 EBICKSOB. J. D. FBEICB, B. F. Aircraft dynamics - Bhat pilots never ask Systematic development testing for engine A75-31299 structural integrity assurance EBICKSOB, J. S. A75-31117 Process evaluation of directionally solidified FBEYBOTB, F. BI3Cb reinforced eutectics in turbine blade form Search for the final period of decay of the [AD-A008135] N75-24926 axisymmetric turbulent wake ESHBLBT, B. E. A75-32139 The influence of short springs on longitudinal FBICK, J. K. D. static stability Velocity and rolling-moment measurements in the [CHAHFIEID-AEBO-29] N75-23607 wake of a swept-wing model in the 10 by 80 foot EViBS, P. J. wind tunnel 7F-16 air induction system design loads associated [NASA-TS-X-62111] H75-23181 with engine surge FBIDHAN, J. D. A75-31111 Airborne wake vortex detection BVBBSEB, D. A. A75-35125 Vibration analysis of multi-symmetric structures FBIEDHA8B, P. [AIAA PAPEH 75-808] A75-32706 Influence of structural damping, preconing offsets BBALD, B. and large deflection on the flap-lag-torsional Airfrane: Engine interaction for engine stability of a cantilevered rotor blade configurations mounted above the wing. Pact 2: [AIAA PAPEB 75-780] A75-32667 Engine jet simulation problems in vind tunnel FBOLOV, V. H. tests Hethod of the optimization of the load-carrying H75-23512 structure of wing on rigidity during variation ElBEEG, D. K. by the distribution of thickness ratio Air transportation of radioactive materials [AD-A007317] B75-23521 475-33568 FBOST, B. The influence of wind shear on aerodynamic coefficients A75-35111 B-5 FHUEHAUF, B. H. PEBSOB1L AOTHOB ISDEX FBOEBAOF, B. B. GOODALL, B. G. Spatial supersonic flow through annular cascades Conceptual design study of advanced acoustic [ASHE PAPER 75-GT-113] 475-31650 composite nacelle [NASA-CR-132649] N75-23568 GOODBASSOB, L. I. Cargo aircraft - A look toward the future GAABO, B. J. A75-35290 Digital flight control systems for tactical GOODilH, F. K. fighters. Volume 3. Digital flight control Calculation of static longitudinal aerodynamic system design consideration characteristics of STOL aircraft with upper [AD-A002687] N75-24754 surface blown flaps Digital flight control system for tactical fighters [NASA-CB-137616] N75-23483 [AD-A002686] N75-24757 GORLA, B. S. B. GABDE, A. E. Unsteady boundary layers over rotating blades Hypersonic research engine project. Phase 2: [ASBE PAPEB 75-GT-61] A75-31617 Some combustor test results of HASA GOSTELOB, J. pf aerothermodynamic integration model Trailing edge flows over turbomachine blades and [NASA-CR-132525] N75-24738 the Kutta-Joukowsky condition GAGOSZ, B. B. [ASBE PAPEB 75-GT-91] A75-34636 Nondestructive holographic technigues for GHABKEHFELD, J. B. structures inspection Development of high stability fuel [AD-A007850] N75-23946 [AD-A007574] N75-23604 GALLAGHER, J. T. GBASSI, 8. Interaction between control augmentation system Theoretical and experimental research on the and airframe dynamics on the YF-17 fatigue crack propagation in stiffened panels, [AIAA PAPER 75-821] A75-32691 an evaluation of the Paris theory GABABEDIAH, P. [AD-A008079] H75-21732 Supercritical wing sections II: A handbook GBEEBB, B. B. A75-31975 Evaluation of bead-stiffened metal panels GABELIK, I. S. [AIAA PAPEB 75-815] A75-32701 Determination of surface roughness of materials Design and fabrication of Rene 41 advanced A75-33331 structural panels GEOKGE, A. B. [NASA-CB-132616] M75-21032 Research on helicopter rotor noise GBEITZER, E. H. [AD-A007261] N75-23608 Surge and rotating stall in axial flow GEBSTLE, J. B. compressors. I - Theoretical compression system Analysis of rotor fragment impact on ballistic model fabric engine burst containment shields [ASBE PAPER 75-GT-9] A75-34573 A75-31141 GRIFFIB, J. A., JB. GIAHEI, A. F. The supersonic doublet-lattice method - A Process evaluation of directionally solidified comparison of two approaches NI3Cb reinforced eutectics in turbine blade form [AIAA PAPER 75-760] A75-32691 [AD-A008135] N75-21926 GRIFFITHS, D. H. GIESIBG, J. P. The use of digital control for complex power plant Oscillatory supersonic lifting surface theory management using a finite element doublet representation B75-23596 [AIAA PAPEB 75-761] A75-32692 GHISBIH, V. I. GILLOB, G. Stress concentration in an expanded plate with Theory of mixing flow of a perfect fluid around an opening reinforced by central belt afterbody and a propulsive jet [AD-A007672] H75-21041 N75-23193 GDEBTBER, B. GLADKIKH, V. A. Development and testing under static conditions of Changes in the properties of hydrogenated fuels a B-A1 load transfer element during prolonged storing [AIAA PAPER 75-788] A75-32675 A75-35299 GDI, B. H. GLASSBAH, 1. J. Subscale, hydrogen-burning, Turbine design and application, volume 3 airframe-integrated-scramjet: Experimental and [HASA-SP-290-VOL-3] H75-21711 theoretical evaluation of a water cooled strut GLAZOHOV, S. G. airfrane-integrated-scramjet: Experimental Engineering titanium alloys leading edge A75-35519 [NASA-TB-I-72682] N75-23885 GLBHH, D. B. Analysis of technology reguirements and potential demand for general aviation avionics systems in H the 1980's HAFTKA, S. I. [SASA-CR-137629] H75-21735 Applications of a quadratic extended interior GLBBNY, B. J. B. penalty function for structural optimization Materials for gas turbines [AIAA PAPER 75-761] A75-32651 A75-32839 HAGDE, D. S. GLIDBIBLL, B. J. An investigation on the effect of second-order Twin jet exhanst system test technigues additional thickness distributions to the upper N75-23500 surface of an NACA 64 sub 1-212 airfoil GLOSS, B. B. [NASA-CB-137701] 875-24674 Effect of wing planforn and canard location and An investigation on the effect of second-order geometry on the longitudinal aerodynamic additional thickness distributions to the upper characteristics of a close-coupled canard wing surface of an NACA 64-206 airfoil model at subsonic speeds [NASA-CB-137702] B75-24675 [NASA-TN-D-7910] B75-23511 Theoretical effect of modifications to the upper Effect of canard position and wing leading-edge surface of two NACA airfoils using smooth flap deflection on wing buffet at transonic speeds polynomial additional thickness distributions [NASA-TH-X-72681 ] H75-23559 which emphasize leading edge profile and which 6OATHAB, J. I. vary quadratically at the trailing edge Bissile firing tests at stationary targets in [SASA-CB-137703] N75-24676 support of blade containment design HAIGHT, H. C. [ASHE PAPEB 75-GT-17] A75-31601 An automated tuneup calibration of jet engine fuel GOLOVABOV, T. controls Korolev: A chronicle A75-35258 [HASA-TT-P-16278 ] H75-21654 B-6 PEBSOIAt iOIBOB IBDEX BOTTO, B. BUBS, T. A. HICKBI, D. B. Observing cold-night temperatures of agricultural Correlation of low speed wind tunnel and flight landscapes with an airplane-mounted radiation test data for V/STOL aircraft thermometer [BASA-TH-I-62423] 175-23557 A75-33103 BIGH, H. D. HA LI, 6. B. Exhaust ploie temperature effects on nozzle A criterion for prediction of airframe integration afterbody performance over the transonic Bach effects on inlet stability vith application to number range advanced fighter aircraft 875-23504 H75-23487 BILL, R. F. BILL, 6. W. Beavy lift helicopter; cargo handling ATC program. Becent advances in in-flight simulator technology Volume 2: Fabrication of test hardware and 475-33187 fixtures integrated test rig BALLOCK, 0. B. [AD-A007244] , H75-24724 Wake vortex decay near the ground HILVEBS, D. B. [AIAA PAPBB 75-882] A75-35173 A study of casing treatment stall margin A predictive nodel of vake vortex transport improvement phenomena A75-35423 [ASHE PAPEB 75-GT-60] A75-34613 The notion of vake vortices in the terminal BIBSCB, B. I. environment Parametric analysis of an advanced manned A75-35424 interceptor utilization Airborne vake vortex detection [AD-4007663] B75-23563 A75-35425 HOLLADAY, T. B. BAH, R. D. Development of a high-heat-release conbustor for Summary of HIT research on dynamic stall and the F100 gas turbine blade-vortex interaction, 1971 - 197<4 [ASHE PAPEB 75-GT-86] A75-34631 [AD-A008091] H75-24689 HOLZBH, B. BAHBOBG, 6. I. A new lightweight fuel control system for Design and development of low-cost, self-contained electrical inputs bearing lubrication systems for turbine engines H75-23599 A75-34121 BOHIAK, L. BABEL, P. Full scale upper surface blown flap noise Parachute systems of the DFVLB for stabilization [HASA-TH-X-71708] H75-23569 and salvage of flight vehicles HOSE, B. I. [DGLB PAPEB 74-043] A75-34661 Flight load investigation of helicopter external BAHAGOD, S. loads Stochastic model for fatigue crack size and cost [AD-A008394] H75-24727 effective design decisions BOBLOCK, J. B. [AIAi PAPEB 75-766] A75-32656 Propagating stall in compressors with porous walls HABDY, J. B. [ASHE PAPEB 75-ST-59] A75-34612 Besearch about effects of external flow and HODCK, P. D. aircraft installation conditions on thrust Guide for the design of control sticks in reversers performances vibration environments N75-23495 [AD-A008533] H75-24729 BABBIS, i. 1. HOiLBTT, G. ». The development of experimental technigoes for the A study of helicopter interior noise reduction study of helicopter rotor noise [HASA-TH-X-72655] 1175-23556 [HASA-CB-1376811] H75-23611 BO, B. B. HABTHAHB, B. FAA lightning protection study: Lightning Development and testing under static conditions of protection requirements for AIL type 55 K a B-A1 load transfer element instrument landing system [AIAA PAPEB 75-788] A75-32675 [AD-A008931] H75-23530 BABTIELL, B. HOCKEL, T. Automatic Test System for Jet Engine Accessories Vibration responses of test structure no. 1 during A75-32396 the Edwards Air Force Base phase of the national BAIES, B. I. sonic boom program An automated tuneup calibration of jet engine fuel [HASA-TH-X-72706] N75-2474U controls BOFFHAH, J. K. A75-35258 Effect of canard position and wing leading-edge BEFFEBHAH, 3. T. flap deflection on wing buffet at transonic speeds Surface finishing [NASA-TH-X-72681] H75-23559 [HASA-CASE-HSC-12631-1] N75-23476 BDLLS, L. B. HEIDELBERG, I. J. Automated test facility for aircraft hydraulic Full scale upper surface blown flap noise pumps and motors [HASA-TH-X-71708] N75-23569 A75-32397 BBLA8, B. BOHPBBEYS, J. B. The economic advantages of low and high Why so few all new General Aviation aircraft temperature anti corrosion coatings on jet A75-33619 engine parts - A case history BDHG, F. T. A75-35449 Aerodynamic heating in gaps in the presence of HEHDEHSOB, B. B. protuberances and shock wave impingement Vibration responses of test structure no. 1 during CAIAA PAPEB 75-670] A75-32907 the Edwards Air Force Base phase of the national HOBLBY, F. X. sonic boom program Supercritical airfoil flowfield measurements [HASA-TB-X-72706 ] B75-24744 [AIAA PAPEB 75-880] A75-33964 BEHDEBSOH, B. B. BOBLBI, G. F. Development of a high-heat-release combustor for Directionally solidified lamellar entectic the F100 gas turbine superalloys by edge-defined, film-fed growth [ASHE PAPEB 75-GT-86] A75-34631 [HASA-CB-134808] 1175-24897 BEHDBBSOH, B. P. HDTCBIHSOH, J. E. Effect of canard position and wing leading-edge Velocity vector - The logical solution flap deflection on wing buffet at transonic speeds A75-32110 [HASA-TH-I-72681 ] N75-23559 BOTTO, B. BIBHBB, D. B. The influence of wind shear on aerodynamic Dynamic response of viscous-damped aulti-shaft jet coefficients engines A75-35411 A75-34128 B-7 HIPHBB, I. P. PBESOHAL ADIHOB IBDEI HIPBBB. B. P. JOHES, 8. L. Analysis of distress air cases in relation to Full scale upper surface blown flap noise crash position and intended track: 1968 - 1973 [H4SA-TH-I-71708] H75-23569 [4D-4007429] N75-23540 JOBBS, 8. P. Integrated potential formulation of unsteady supersonic aerodynamics for interacting wings [AIAA PAPEB 75-762] A75-32693 I4SKBVICB, B. P. Determination of surface roughness of materials A75-33331 IBODOV, B. D. KACHOBIBA, 6. V. Ring longitudinal stability criteria Changes in the properties of hydrogenated fuels [4D-4007430] H75-23527 during prolonged storing IOGOV, 0. K. A75-35299 Hatching of aircraft and engine characteristics KA1HAB, I. P. 475-35521 Oscillatory supersonic lifting surface theory IVABOV. A. L. using a finite element doublet representation Changes in the properties of hydrogenated fuels [AIAA PAPEB 75-761] 475-32692 during prolonged storing KiHBEB, P. I. 475-35299 in airframe manufacturer's reguirements for future IVABOV, T. I. propulsion controls Calculation of the reinforced thin-walled H75-23578 construction by the method of the final element KABBKO, V. F. [AD-A007307] H75-23560 Determination of surface roughness of materials IVBBSBH, J. D. A75-33331 Inviscid to turbulent transition of trailing KAO, B. C. vortices Side forces on nnyawed slender inclined [4144 P4PEB 75-883] 475-33965 aerodynamic bodies IVES, D. C. A75-33435 4 modern look at conformal mapping, including HAPPIER, G. doubly connected regions Experimental investigation of a new concept of [4144 P4PER 75-812] 475-33936 fuel prevaporization [ASBE PAPER 75-GT-6] 475-34570 KASIAHOV, G. A. Rescue measures in the case of accidents of the JAABSHA, P. AS-12 aircraft Jet interference of a podded engine installation A75-32527 at cruise conditions KAIACHI, K. N75-23490 Local momentum theory and its application to the J4COBSEH, B. 4. rotary wing Analysis of wake vortex flight test data behind a [AIAA P4PEB 75-865] 475-33952 T-33 aircraft K4I, B. B. [BASA-CR-137669] B75-23482 Safety-related engineering and development JiCOBSOB, B. J. activities of the Federal Aviation Administration Response of aircraft structural compartments to [AD-A008395] N75-24698 blast pressures and fragments from high KAYSEB, J. B. explosive projectiles Analysis of technology reguirements and potential [A1A4 PAPER 75-751] 475-32652 demand for general aviation avionics systems in JAHBSOB, 4. the 1980's Transonic potential flov calculations using [NASA-CR-137629] S75-24735 conservation form KEBDALL, B. B. 475-31193 Computational procedure for three-dimensional Supercritical wing sections II: 4 handbook boundary layers on aircraft and aerospace vehicles 475-31975 475-34190 JBFFEBS, J. D., II KBHTFIELD, J. A. C. F100 fan stall flutter problem review and solution Regenerative turbofans - A comparison with 475-31131 nonregenerative units JEBHIHGS, B. P. A75-33438 The flutter analysis of T-tails KETTLEBOBODGH, C. F. [4IAA PAPEB 75-759] A75-32690 Improvement of propeller static thrust estimation JBHSBN, G. [BAS4-CH-132680] B75-23567 Involving the expert and aviation community in the KIKOCHI, T. decision making structure of the D.S. MLS program An experimental investigation on the transonic 475-31537 flutter characteristics of the cantilever JOHBSOB, C. L. swept-back wing with aerofoil section, and Control system reguirements dictated by comparison with the thin cantilever swept-back optimization of engine operation wing N75-23579 [RAE-LIB-TRANS-1838] B75-24680 JOHBSOB, F. 1. KIHZLBR, J. 4. A three-dimensional solution of flows over wings Surface finishing with leading-edge vortex separation [NASA-CASE-HSC-12631-1] S75-23476 [4IA4 P4PEH 75-866] 475-33953 KIRSCHET, G. JOH1STOB, I. B. Experimental investigation of a new concept of Conseguential and special damages - Tempest in the fuel prevaporization tariff [ASHE P4PER 75-GT-6] 475-34570 A75-33569 KISH, J. JOBES, D. I. G. Advanced overrunning clutch technology, design phase Control of gas turbine stator blade vibrations by [AD-4007815] N75-23562 means of enamel coatings KLBIB, V. A75-34116 On the adeguate model for aircraft parameter JOBES, B. B. estimation Mechanics of composite materials [CH4B?IELD-4EBO-28] B75-24755 475-32463 KLEPPB, K. B. JOHES, S. B. Ground effects for jet lift VIOL International and D.S. design proposals for a [NASA-TT-F-16359] B75-23480 microwave landing system KBIBB, T. F. 475-34536 Advanced gallium phosphide L.E.D. displays 475-35284 B-8 PEBSOBAL ADTBOB ISDBX LOWEB, K. KOEHIG, D. G. LAKSBHI8ABAYAHA, B. Hagimum lift of upper surface blowing STOL Three dimensional characteristics of turbulent aircraft vitb swept wings wakes behind rotors of axial flow tnrbomachinery tAIAA PAPEB 75-868] A7S-339S5 [ASHE PAPEB 75-GT-1] A75-31566 KOLIB, I. 7. LAB, C. L. Natural oscillations of liquid in a horizontal Design and analysis of a ceramic stator vane container with symmetric double-connected cross [ASBE PAPEB 75-GT-100] A75-34612 section LAHDGBBBB, A. J. [AD-A007312] H75-23906 Prediction of rotor wake induced flow along the KOSAE, A. F. rocket trajectories of an Army AH-1G helicopter Digital flight control system for tactical fighters [AD-A007878] H75-23528 [AD-A002686] H75-24757 LUG, J. D. KOBB, D. A model for the dynamics of a separation bubble Computer simulation of transonic flow past used to analyze control-surface buzz and dynamic airfoils with boundary layer correction stall A75-34196 CAIAA PAPEB 75-867] A75-3395 B-9 LOVE, J. E. PEESOHiL ADTHOS IHDEX LOTS, J. E. BARBIBBET, i. Flight test results of an automatic support system Flight test for the feasibility evaluation of the on board a TP-12A airplane Chadwick Electronic weighing System (CHEUS) A75-35272 [AD-A007516] 1175-23522 LU, P. HAZELSKT, B. A three-dinensional solution of flows over wings A crashworthy armored pilot seat for helicopters with leading-edge vortex separation [AD-A007551] H75-235M1 [AIAA PAPER 75-866] A75-33953 HCCAFFBEI, B. B. LOEBS, J. K. Response of a light aircraft to a thermal exhaust Wind shear effects on landing touchdown point plume A75-35420 A75-35403 LDKIC, S. BCCABTI, J. I. Formation of flexibility matrices of a structure The effect of chine tires on nose gear water-spray based on known yields at arbitrary points characteristics of a twin engine airplane A75-32995 [BASA-TB-X-72695] H75-23555 LOO, I. S. BCCOSBICK, B. i. Aerodynamics of lifting and propulsive systems in Response of a light aircraft to a thermal exhaust a periodically functioning regime - Optimization plume of their performance A75-35403 A75-35815 flCCOT, H. L. The B-1 CITS system A75-35277 M BCDEVITT, J. B. B6ESTBATI, J. Transonic flow about a thick circular-arc airfoil Comparison of flight and wind tunnel tests of an [AIAA PAPER 75-878] A75-33962 executive airplane BCGHBB, B. J. A75-35806 Low-speed aerodynamic characteristics of a HiGGE, B. 13-percent thick airfoil section designed for Philosophy, design, and evaluation of soft-mounted general aviation applications engine rotor systems [HASA-TB-X-72697] 875-21678 A75-34130 HCKEBZIE, A. B. BAJOBDAB, S. Performance development of the Gem turboshaft engine Low-cycle fatigue and creep analysis of gas [ASBE PAPER 75-GT-28] A75-34586 turbine engine components HEECE, C. B., JB. A75-31139 FIDO fan stall flutter problem review and solution HAKI, B. L. A75-34134 Large-scale wind-tunnel tests of three vehicles BEER, S. A. incorporating a deployable rigid wing International and D.S. design proposals for a [BASA-TH-X-62U05 ] B75-24671 microwave landing system MALAVAED, L. A75-34536 Aerodynamics of lifting and propulsive systems in BEIEB, G. E. A. a periodically functioning regime - Optimization Unsteady behavior of transonic flows of their performance [MPIS-HITT-59] B75-23516 ' A75-35815 BELEASON, B. T. BALLOT, A. B. Transonic off-design drag and performance of three Corrosion control in naval aircraft nixed-compression axisymmetric inlets A75-32830 [BASA-TB-X-3215] B75-23602 BASGASO, G. J. BELNYK, t. Rotor burst protection program - Statistics on Development of impact resistant boron/aluminum aircraft gas turbine engine rotor failures that composites for turbojet engine fan blades occurred in U.S. commercial aviation during 1973 [BASA-CB-134770] [175-24747 [ASHE PAPER 75-GT-12] A75-3U575 BEHDESHALL, B. B. BARKS, A. S. Calculation of static longitudinal aerodynaaic Theoretical downwash velocities about the AH-1G characteristics of STOL aircraft with upper helicopter at hover and 140 knots surface blown flaps [AD-A008339] B75-24693 [BASA-CB-137646] H75-23483 BABBOL, B. A. BERKULOV, B. L. Rapid verification of engine rotor and case Calculation of loads and deformations of sweptback flexibilities by a modal comparison algorithm wing with the aid of mechanical analog instruments A75-34119 [AD-A007308] B75-23525 BABTIH, A. B. BERRIED, P. B-1 - The road to first flight Titanium casting - Industrial development - A75-32455 Economic aspects BABTIB, E. D. A75-35159 A fast sefflidirect method for computing transonic SEBEILL, R. C. aerodynamic flows An application of modern control theory to jet A75-3 B-10 PBBSOIAL ADTBOB IBDBX IISSIB, B. BBT1BS, L. B. HOOLDBB, T. B. The B-1 CITS system On soie probleis encountered in a theoretical A75-35277 study of the external flow over a nozzle BIGBOSI, &. configuration in transonic flight Study on the establishment of flow in a wind B75-23499 tunnel functioning by induction BOTBB, T. D. 475-35811 Design and development of low-cost, self-contained BIKBEICBBV, P. i. bearing lubrication systems for turbine engines Application of thin-layer chromatography for A75-3U121 determining the wearing capacity of additives HDLABZ, S. J. contained in petroleum-based aviation oils Flow characteristics of various swirl-can module A75-35300 designs HIEBITABOf, B. A. [BASA-tB-X-3236] H75-24740 Soand radiation froa a bounded thin inhomogeneoas Bxhaast pollatant emissions from swirl-can plate reinforced with H ribs and driven by combustor module arrays at parametric test boundary-layer pressure fluctuations conditions A75-33U17 [8ASA-TB-X-3237] H75-2U7U6 BIKOLAJCZAK, A. A. BDHDBll, A. B. 6. Advances in fan and conpressor blade flatter The subsonic base drag of cylindrical twin-jet and analysis and predictions single-jet afterbodies A75-34131 H75-23198 BUBS, A. T. BUBBIKSBA, B. Puiping system design related to fuel systen Jet interference of a podded engine installation specifications at cruise conditions 875-23600 S75-23U90 BILLIGiB, H. D. BOSGBOVE, B. D. Preliminary results from pilot aviation weather Advanced beaded and tabular structural panels. self-briefing experiments Volume 2: Fabrication A75-35428 [BASA-CB-132H82] B75-2U717 BIBABI, K. A theoretical analysis for three dimensional ran wings in parallel walls A75-33H27 BAGATO, K. BIHICH, B. B. Preliminary study of low emission gas turbine Analytical displacements and vibrations of combustor with airblast fuel atomizer cantilevered unsymmetric fiber composite laminates [ASBE PAPEH 75-61-31] A75-31588 [AliA PAPEB 75-757] A75-32688 BAKAI, B. Structural response of fiber composite fan blades An experimental investigation on the transonic [ASBE PAPEB 75-GT-78] A75-31627 flutter characteristics of the cantilever BIODDSBEVSKII, P. V. swept-back wing with aerofoil section, and Reproduction of the interaction of aerodynamic comparison with the thin cantilever swept-back loads and structural distortions during strength wing tests [BAB-LIB-TBAHS-1838] H75-2U680 [AD-A007661] H75-23520 BAK1TABI, B. BIIAI, T. A theoretical analysis for three dimensional ram A theoretical analysis for three dimensional ran wings in parallel walls wings in parallel Halls A75-33127 A75-33127 H18COO, B. B. HODIG, C. Aeronautical reguirements and procedure for Civil aviation studies and interagency low-level turbulence and wind shear reporting coordinating organizations, volume 1 A75-35U14 [PB-2393UU/5] B75-2t186 BABDO, C. I. Civil aviation studies and interagency Computational procedure for three-dimensional coordinating organizations, volume 2: Appendices boundary layers on aircraft and aerospace vehicles [PB-239315/2] N75-24187 A75-34190 BOISEBV, V. H. BABDOBB, V. Engineering titanium alloys Contribution of flight simulation tests to the A75-35519 study of turbomachine control BOBAB, J. M75-23577 Airport noise reduction forecast. Volume 2: NEF BABBAHOBE, J. C. computer program description and user's manual An inverse method for the design of multielement [PB-239388/2] 875-21772 high-lift systems BOBIHO, L. [AIAA PAPEB 75-879] A75-33963 A finite-element method for lifting surfaces in BEEL, C. B. steady incompressible subsonic flow Shuttle spacelab simulation using a Lear jet [NASA-CF-102811] H75-23H77 aircraft: Mission no. 3 (ASSESS program) Subsonic and supersonic indicial aerodynamics and [BASA-TM-I-62I»10] H75-2U760 aerodynamic transfer function for complex HESS, B. B. configurations The random decrement technigue applied to the [HASA-CB-142818] 875-23178 IF-16 flight flutter tests BOBITA, I. [AIAA PAPEB 75-776] A75-32663 An experimental investigation on the transonic BG, K. 8. flatter characteristics of the cantilever Effect of simulated forward flight on subsonic jet swept-back wing «ith aerofoil section, and exhaust noise comparison with the thin cantilever swept-back [AIAA PAPEB 75-869] A75-33956 wing BISBIBDBA, B. [BAE-LIB-TBANS-1838] H75-2U680 Experimental results of full scale air-cooled BOBHILI, D. E. turbine tests Automatic test equipment for S-3A support [ASBE PAPEB 75-GT-116] A75-3W653 A75-35279 BISBT, B. I. BOSS, F. E. Calculation of the separated flow at a Challenge to aviation: Batching a leaner pterosauer thin-section wing of finite span [KASA-TB-X-71741 ] 1175-25298 A75-31262 BOSTIPiB. V. K. BISSIB, B. Determination of surface roughness of materials Active flutter suppression using trailing-edge and A75-33331 tab control surfaces BOTTCKA, D. L. [AIAA PAPEB 75-822] A75-32697 Ground vortex - Lint to engine/reverser operation [ASBE PAPEB 75-GT-3J A75-31567 B-11 nioi, D. PBBSOBAL iDTBOB IBDBX •IXOI, D. PALHBB, C. J. Calculation of transonic flows using an extended The effect of water path variations on ultrasonic integral equation aethod through-transmission sensitivity [AIAA PAPEB 75-876] A75-33961 "A75-31203 •HOI, P. B. PAIASBHKO, A. V. Observing cold-night temperatures of agricultural General analysis of the diffraction pattern for a landscapes with an airplane-mounted radiation plane acoustic wave at a wedge moving at thermometer supersonic speed A75-33103 A75-34272 BOBTHBOP. B. F. PABK, C. Design and fabrication of Rene 41 advanced Computation of noneguilibrini three-dimensional structural panels inviscid flow over blunt-nosed bodies flying at [NASA-CB-132646] H75-24032 supersonic speeds Advanced beaded and tabular structural panels. [AIAA PAPEB 75-835] A75-33931 Volume 2: fabrication PABBAB, P. B. [BASA-CB-132482] H75-24717 Bypersonic research engine project. Phase 2A: MOBTH100D, J. B. Instrumentation program Materials for gas turbines [NASA-CB-132593] 875-24743 ' A75-32839 PABSOHS, B. K. BOBTOI, P. S. Effects of asymmetry on the dynamic stability of S-3A stall testing and auto-throttle aircraft development/testing [NASA-CB-142857] H75-24756 A75-33613 PECSVABADI, T. BOOSE, B. Four-dimensional guidance algorithms for aircraft Experimental results of full scale air-cooled in an air traffic control environment turbine tests [NASA-TN-D-7829] B75-23549 [ASBE PAPEB 75-GT-116] A75-31653 PEIKEBI, J. NOXEB, B. I. An air intake control system for a supersonic Problems of federal and state court jurisdiction fighter aircraft and venue in products liability litigation - B75-23589 Defendants viewpoint PELODBET, B. P.. JB. A75-33565 YF16 active-control-system/structural dynamics BDBH, B. B. interaction instability Aerodynamic characteristics of an axisymmetric [AIAA PAPBB 75-823] A75-32695 body undergoing a uniform pitching motion PEBKIB, S. C., JB. [AIAA PAPEB 75-838] A75-33933 Calculation of static longitudinal aerodynamic HTE, S. characteristics of STOL aircraft with upper Use of simulation in the design, development and surface blown flaps testing of pover plant control systems [NASA-CB-137646] B75-23483 H75-23595 PEBKS, H. P. BTLBB, 8. B. Helicopter engine control: The past 20 years and The-out of service guest pilot evaluation of the the next two-segment noise abatement approach in the N75-23585 Boeing B727-200 PE1BB, A. [NASA-CR-137625] N75-24696 Drag effects on wing flutter [AIAA PAPEB 75-775] A75-32662 PICO, L. C. The age of the BPV data bus or the data bus comes OEHHEB, K. H. of age Extension of the parabolic method for the A75-35261 transonic flow. I - Steady flow. II - Unsteady PIEBSOB, B. L. flow Aeroelastic panel optimization with aerodynamic A75-35215 damping OESTBICBEB, P. F, A75-33488 YF-16 - A rare opportunity PIBCKHEI, S. Z. 475-33615 Subscale, hydrogen-burning, OLSBH, S. i. airframe-integrated-scramjet: Experimental and CF5D aircraft cockpit-noise reduction theoretical evaluation of a water cooled strut [DCIEH-74-B-1048 ] N75-23564 airframe-integrated-scramjet: Experimental OHAH, B. B. leading edge Computer program to assess impact of fatigue and [HASA-TH-X-72682] H75-23885 fracture criteria on weight and cost of PIVA, B. transport aircraft Low speed injection effects on the aerodynamic [NASA-CH-132648] N75-24718 performance at transonic speed ONEI1L, B. C. B75-23494 Analysis of distress air cases in relation to PLABK, P. P. crash position and intended track: 1968 - 1973 Hypersonic wing test structure design, analysis, [AD-A007429] N75-23540 and fabrication OTA, T. [AIAA PAPEB 75-785] A75-32670 An axisymmetric separated and reattached flow on a POPOV, 0. V. longitudinal blunt circular cylinder Fabrication of one-piece-forged thin-walled parts [ASME PAPEB 75-APM-14] A75-35101 having variable cross section A75-33150 POPP, B. G. Design of fabricated static structures for long PACKHiB, A. B. cyclic life Effect of simulated forward flight on subsonic ]et A75-34142 exhaust noise POVINELLI, V. P., JB. [AIAA PAPEB 75-869] A75-33956 Current seal designs and future requirements for PAIHTEB, G. V. turbine engine seals and bearings Conceptual design study of advanced acoustic A75-34123 composite nacelle PORBLL, J. D. [NASA-CB-132649] 875-23568 Effects of asymmetry on the dynamic stability of PALCZA, J. L. aircraft Jet-induced thermal effects for VTOL aircraft [NASA-CB-142857] N75-24756 [ASHE PAPEB 75-GT-96] A75-34638 POBELL, B. D. The use of digital control for complex power plant management N75-23596 B-12 PEBSOBiL AUTHOR IBDEI BOZBK07, I. V. PBIBCB, D. C., JB. BIPOLL, J. C. A study of casing treatnent stall margin Contribution of flight siaulation tests to the improvement phenomena study of tnrbomachine control [ASHE PAPER 75-GT-60) A75-31613 H75-23577 BOBEBTSOB, A. B. Boron/aluminum for advanced technology aircraft [AIAA PAPEB 75-790] A75-33762 QOEBABD, C. HOBIBSOB, C. E. Study on the establishment of flow in a wind Exhaust plume temperature effects on nozzle tunnel functioning by induction afterbody performance over the transonic Bach A75-35811 number range QUEBHAHB, J. K. B75-23501 Subsonic base and noattail drag, an analytical BOBIBSOB, K. approach Afterburning regulation concepts N75-23192 H75-23587 QUIBB. B. BOEKBOJOTO, B. Concurrent mixing and diffusion in three dimensions Ground effects for jet lift VIOL [AIAA PAPBB 75-873] A75-35170 [NASA-TT-F-16359] 1175-23180 BOGEBS, G. 1. Rind-tunnel tests and computer simulations of buoyant wing-tip vortices B4JT, J. A75-35122 Vortex development and breakdown BOGEBS, B. C. [AIAA PAPEB 75-881] A75-35172 Subscale, hydrogen-burning, HADCHEBKO, I. V. airframe-integrated-scram]et: Experimental and The An-2 aircraft /1th revised and enlarged edition/ theoretical evaluation of a water cooled strut A75-35350 airfraue-integrated-scramjet: Experimental BAHAIB, T. J. leading edge Design and analysis of a ceramic stator vane [HASA-TB-X-72682] B75-23885 [ASHE PAPEB 75-GT-100] A75-31612 BOHLIBG, 8. J. t BAIHBIBD, i. J. The influence of nacelle afterbody shape on Some wind tunnel measurement of the trailing airplane drag vortex development behind a sweptback wing - H75-23505 Induced rolling noments on intercepting wings aoat, D. A. [AIAA P4PEB 75-881] A75-33966 Temperature measurement for advanced gas turbine BAJ, B. controls Three dimensional characteristics of turbulent N75-23597 wakes behind rotors of axial flow turbomachinery BOBABOV, A. B. [ASBE PAPEB 75-GT-1] A75-31566 Changes in the properties of hydrogenated fuels RAKICH, J. V. during prolonged storing Computation of nonequilibrium three-dimensional A75-35299 inviscid flow ever blunt-nosed bodies flying at BOOS, F. I. supersonic speeds Supercritical airfoil flowfield measurements [AIAA PAPEB 75-835] A75-33931 [AIAA PAPEB 75-880] A75-33961 BEDDECLIF?, J. BOOS, B. Dynamic simulator for advanced gas turbine engine A calculation method for unsteady subsonic flow component tests about harmonically oscillating wing-body A75-31116 configurations BEDHAB, fi. C. [AIAA PAPEB 75-861] A75-33951 Prediction of unsteady aerodynamic loadings caused BOSSI, F. by leading edge and trailing edge control Theoretical and experimental research on the surface motions in subsonic compressible flow: fatigue crack propagation in stiffened panels, Computer program description an evaluation of the Paris theory [HASA-CB-132631] N75-21672 [AD-A008079] 1175-21732 BEEVES, J. B. BOSSOB, V. J. Hind shear effects on landing touchdown point Theoretical study of lift-generated vortex wakes A75-35120 designed to avoid rollup BEID, J. A75-33185 The subsonic base drag of cylindrical twin-jet and Experimental study of the effect of span loading single-Jet afterbodies on aircraft wakes 1175-23198 [AIAA PAPEB 75-885] A75-33967 BEIBE, C. B. Experimental study of the effect on span loading Botor Systems Besearch Aircraft /BSEA/ on aircraft wakes A75-33621 [NASA-TB-X-62131] B75-23179 BELLEB, J. O., JB. Velocity and rolling-moment measurements in the Shuttle spacelab simulation using a Lear jet wake of a swept-wing model in the 10 by 80 foot aircraft: Bission no. 3 (ASSESS program) wind tunnel [HASA-TB-X-62110] 1175-21760 [HASA-TH-X-62111] B75-23181 BEVAI, A. I., JB. BOOT*, I. ?AA lightning protection study: Lightning Autotest user needs at a base shop protection reguirements for AIL type 55 R A75-35253 instrument landing system BORE, G. L. [AD-A008931] H75-23530 Autotest user needs at a base shop BEZHICBEHKO, ID. 1. A75-35253 Determination of surface roughness of materials B08B, 8. S. A75-33331 Prediction of unsteady aerodynamic loadings caused BHODES, fl. D. by leading edge and trailing edge control Inpact fracture of composite sandwich structures surface motions in subsonic compressible flow: [AIAA PAPEB 75-718] A75-32673 Computer program description BICBBT. G. K. [HASA-CB-132631] 1175-21672 Airframe/propnlsion system flow field interference BOIAL, A. C. and the effect on air intake and exhaust nozzle High-speed rotor dynamics - An assessment of performance current technology for small turboshaft engines H75-23508 A75-31127 BICBTBB, J. J. BOZHKOV, I. V. Passive infrared imaging systems Influence of protective additions on the anti-wear A75-31881 properties of jet fuels A75-35298 B-13 BDBBEBT, P. E. PESSOB4L ADTHOH IIOEX EDBBEBT, P. S. SCHSIBD, B. G. A three-dimensional solution of flows over vings Velocity and rolling-moment measurements in the with leading-edge vortex separation wake of a swept-wing model in the 40 by 80 foot [AIAA PAPER 75-866] A75-33953 wind tunnel [HASA-TB-X-62414] B75-23481 SCOTLAHD, B. L. Reverse thrust experience on the Concorde SABLIHA, Z. A. H75-23496 Influence of protective additions on the anti-wear SCOTTOLIBB, C. A. properties of jet fuels Aerodynamic heating in gaps in the presence of A75-35298 protuberances and shock wave impingement SAGBH, D. [AIAA PAPER 75-670] A75-32907 Simulator evaluation of manually flown curved BIS SEKIGAIA, E. approaches Bitsubishi's mentor - Supersonics from Nagoya A75-34535 A75-33448 SAIHIO, ». C. SELIVAHOV, 0. 0. Hypersonic research engine project. Phase 2: Hatching of aircraft and engine characteristics Some combustor test results of NASA A75-35521 aerothermodynamic integration model SELLEBS, J. [NASA-CR-132525] 875-24738 Generalized dynamic engine simulation techniques Hypersonic research engine project, phase 2. for the digital computers Preliminary report on the performance of the H75-23593 HSE/AIH at Bach 6 SEIKO, G. H. [NASA-CR-132538] N75-24742 Analysis of technology requirements and potential SAIZ, B. demand for general aviation avionics systems in Interaction of jets of GE CF6-50 reactors with the the 1980's wing cellules of the airbus during cruise - [NASA-CR-137629] 875-24735 Wind-tunnel simulation SEBEGIH, E. P. A75-35808 Changes in the properties of hydrogenated fuels SAKHHOV, V. A. during prolonged storing Determination of surface roughness of materials A75-35299 A75-33331 SEBGBEV, V. L. SALABA, J. Free-molecular interference of cylinders with Identification of systems by means of adaptive model oblique ray reflection A7S-32473 A75-33339 SALLBT, D. I. SHANKS, S. P. The drag and oscillating transverse force on Dse of numerically generated body-fitted vibrating cylinders due to steady fluid flow coordinate systems for solution of the A75-35765 Navier-Stokes equations SAIVBTTI, A. A75-34186 Theoretical and experimental research on the SBBFBIH, J. fatigue crack propagation in stiffened panels, Heavy lift helicopter; cargo handling ATC program. an evaluation of the Paris theory Volume 2: Fabrication of test hardware and [AD-A008079] 875-24732 fixtures integrated test rig SAHIB ABDELSALAB, B. [AD-A007244] B75-24724 A method to determine a distribution function of SHELTOH, 3. D. main structure failures in an aircraft Hinimum weight design of the F-15 empennage ror A75-32468 flutter SASDAY, S. C. [AIAA PAPEB 75-777] A75-32664 Design and analysis of a ceramic stator vane SHEBESHKOV, G. B. [ASBE PAPEB 75-GT-100] A75-34642 Bescue measures in the case of accidents of the SABDSTEDE, B. AB-12 aircraft Influences of manufacturing tolerances and surface A75-32527 roughness of blades on the performance of turbines SBBVBLL, B. S. [ASBE PAPER 75-GT-35] A75-34592 Effects of asymmetry on the dynamic stability of SABLOEESZO, E. A. aircraft Response of a light aircraft to a thermal exhaust [HASA-CB-142857] 875-24756 plume SHIDELBB, J. L. A75-35403 Evaluation of bead-stiffened metal panels SAHTOCHI, B. [AIAA PAPEB 75-815] A75-32701 Fluidic sensors for turbojet engines SIDDIQEE, I. 875-23598 Air traffic controllers' operative effectiveness S40BDEBS, G. B. under MAS environments Image system solution for store aerodynamics with A75-34539 interference. I SIBOBIS, E. A. A75-33436 Helicopter engine control: The past 20 years and SCHEIB, P. the next Calculations of three-dimensional flows in a H75-23585 linearized supersonic regime SIHPSOB, L. A75-35813 Airport noise reduction forecast. Volume 1: SCBHIDT, D. K. Summary report for 23 airports Air traffic controllers' operative effectiveness [PB-239387/4] 875-24771 under HAS environments SIBHETT, J. B. A75-34539 Advanced maneuverability options for future fighters SCBBIDT, S. F. [AD-A008497] 875-24725 A Kalman filter for the Stoland system SKOVOHODIB, G. B. [HASA-CB-137668] 1175-23543 Influence of protective additions on the anti-wear SCHOLMBISTEB, L. F. properties of jet fuels Process evaluation of directionally solidified A75-35298 HI3Cb reinforced entectics in turbine blade fora SIOAH, 0. [AD-A008435] 875-24926 The refracting inlet - A new concept for aircraft SCBDLZ, 6. inlet noise suppression Detailed experinental and theoretical analysis of [ASBE PAPEB 75-GT-21] A75-34580 the aerodynamic interference between lifting SHBTA8A, F. O. jets and the fuselage and wing Light aircraft lift, drag, and moment prediction: H75-23509 A review and analysis SCBDTZ [BASA-CB-2523] N75-24677 Total airfraie fatigue test F 104 G [AD-A007938] H75-24726 B-11 PBBSOBAL AOIHOH IBDEX SOBKOTA, B. B. SBITB, C. 0. STABIKOV, B. B. Image system solution for store aerodynamics with Experimental investigation of friction on a plate interference. I in the flow of a rarefied gas A75-33436 A75-333»6 SHITH, t. 1. STABKE, P. Digital flight control systems for tactical System concept and key problems concerning fighters. Volume 3. Digital flight control pilotless, reaotely-controlled combat aircraft DBF system design consideration [DGLB PAPEB 74-076A] A75-34725 [AD-A002687] B75-24754 STABBBS, J. B., JB. Digital flight control systea for tactical fighters Applications of a guadratic extended interior [AD-A002686] B75-24757 penalty function for structural optimization SBITB, 1. B. [AIAA PAPEB 75-764] A75-32654 Aerodynamic characteristics of an axisymmetric STBCEBECK, ?. J. body undergoing a uniform pitching notion Preliminary results from pilot aviation weather [AIAA PAPEB 75-838] A75-33933 self-briefing experiments SBITH, t. B. A75-35428 The random decrement technigae applied to the STETSOH, E. A. YF-16 flight flutter tests Nondestructive holographic technigues for [AIAA PAPEB 75-776] A75-32663 structures inspection SBITH, B. S. [AD-A007850] B75-23946 Light aircraft lift, drag, and nonent prediction: SIEOBB, K. B. A review and analysis Ion vapor deposited aluminum improves structure [HASA-CR-2523] H75-24677 durability SBITB, B. [AIAA PAPEB 75-807] A75-32680 Design and development of lov-cost, self-contained STBBABT, A. E. bearing lubrication systems for turbine engines Development of real time high energy X-ray imaging A75-34121 system for use in dynamic fluoroscopy of aero SHTDEB, L. E. gas turbines Advances in fan and compressor blade flutter [ASBE PAPEB 75-GT-117] A75-34654 analysis and predictions STEBABT, B. B. A75-34131 Missile firing tests at stationary targets in SOK0107A, 0. B. support of blade containment design Calculation of the separated flow at a [ASBE PAPEB 75-GT-47] A75-34604 thin-section wing of finite span SIITEBS, L. S., JB. A75-3<1262 Supercritical airfoil flowfield measurements SOBEBS, D. B. [AIAA PAPEB 75-880] A75-33964 Low-speed aerodynamic characteristics of a STOHE, B. B. 13-percent thick airfoil section designed for Stone Spin Shorthand, including: Spin Data Card general aviation applications and sample Criteria Spin Set [NASA-TB-X-72697] H75-24678 A75-33618 SPAID, F. i. STBACK, I. Supercritical airfoil flowfield measurements Preliminary study of advanced turboprops for low [4IAA PAPEB 75-880] A75-33964 energy consumption SPABGLEB, S. B. [NASA-TB-I-71740] 875-24739 Calculation of static longitudinal aerodynamic STBADB, B. B. characteristics of STOL aircraft with upper Test and performance criteria for airplane surface blown flaps antiskid systems [HASA-CB-137646] B75-23483 [AD-A008536] H75-24730 SPEAB, E. B. STBEET, P. 6. Systematic development testing for engine Thrust/drag analysis for a front fan nacelle structural integrity assurance having two separate co-axial exhaust streams A75-34147 [ABC-CP-1311] H75-23574 SPBHEBT, T. STOBBS, S. B. A rigorous solution of the Navier-Stokes equations The effect of chine tires on nose gear water-spray for unsteady viscous flow at high Beynolds characteristics of a twin engine airplane numbers around oscillating airfoils [SASA-Tn-X-72695] H75-23555 [AIAA PAPEB 75-863] A75-33950 SOBE, H. B. SPIEB, E. E. Theory of mixing flow of a perfect fluid around an Crippling/column buckling analysis and test of afterbody and a propulsive jet graphite/epoxy-stiffened panels B75-23493 [AIAA PAPEB 75-753] A75-32684 SDCIO, E. SPIBTZTK, J. A finite-element method for lifting surfaces in System concept and key problems concerning steady incompressible subsonic flow pilotless, remotely-controlled combat aircraft UKF [HASA-CB-142811] H75-23477 [DGLB PAPEB 74-076AJ A75-34725 SOBBEI, D. C. SPITZEB, E. A. Light aircraft lift, drag, and moment prediction: The motion of wake vortices in the terminal A review and analysis environment [HASA-CB-2523] 1175-24677 A75-35424 SOB, I. B. SPBIBG, D. J. Hypersonic research engine project. Phase 2: On some problems encountered in a theoretical Some combustor test results of NASA study of the external flow over a nozzle aerothermodynamic integration model configuration in transonic flight [NASA-CB-132525] N75-24738 H75-23199 Hypersonic research engine project, phase 2. SPBIHGEB, B. J. Preliminary report on the performance of the Aircraft engine nacelle fire test simulator 8BE/AIB at Bach 6 [AD-A007853] H75-23617 [NASA-CB-132538] S75-24742 SBIBIVASAR, A. V. SDBBBH, L. B. Influence of mistnning on rotor-blade vibrations Airfcame/propulsion system flow field interference A75-33483 and the effect on air intake and exhaust nozzle SBIBIVASAB, P. performance Study of the interaction and three-dimensional H75-23508 separation effects of a boundary layer in a SDHKOVA, B. B. supersonic laminar regime Problem of supersonic flow past a slender pointed A75-35450 body with tail STABGABDTEB, H. A75-35706 Advances in fan and compressor blade flutter analysis and predictions A75-34131 B-15 SOTHBBLAiD. I. C. PEBSOHAL AOTHOB IHDBX SOTHEBIAHD, L. C. IOTH, I. J. Airport noise redaction forecast. Volute 1: Developoent of impact resistant boron/aluminum Sumiary report for 23 airports composites for turbojet engine fan blades [PB-239387/1] H75-21771 [NASA-CS-13*770] B75-21717 TBACI, B. H. A perturbation method for transonic flows about oscillating airfoils TABAKOFP. 8. [AIAA PAPEB 75-877] A75-35171 The dynamics of atmospheric dust particles in TBIBGALI, J. B. aircraft auxiliary power radial inflow turbines Control design considerations for variable [AIAA PAPEB 75-811] A75-33938 geometry engines TAKAHABA, K. B75-23583 Experimental results of full scale air-cooled TBOAI, P. P. turbine tests YF-16 air induction system design loads associated [ASBE PiPEE 75-GT-116] A75-31653 with engine surge TAKATA, H. A75-31111 Study on the mechanise of stall margin improvement TSEH, L. F. of casing treatment Study of a strongly asymmetric turbulent wake [ASBE PAPEE 75-GT-13] A75-31576 behind a profile with upper-surface separation TABHEB, C. J. A75-32951 Computer progran to assess impact of fatigue and TSOKODA, I. fracture criteria on weight and cost of Study on the mechanism of stall margin improvement transport aircraft of casing treatment CHASA-CB-132618] H75-21718 [ASBE PAPEE 75-GT-13] A75-31576 TABHEB. H. TDCKBB, P. B. Influence of a plain flap with a blunt, notched Binimum weight design of the F-15 empennage for trailing edge on the lift of a rectangular wing flutter [ESBO-TT-117] N75- 21685 [AIAA PAPEE 75-777] A75-32661 TATTELSAH, P. TDGAZAKOV, B. I. Surface wind speed range as a function of time Interaction of shock wave with wedge, which moves interval and mean wind speed at supersonic speed A75-35U13 [AD-A007302] H75-23519 TAYLOB. B. F. Development of high stability fuel u [AD-A007571] N75-23604 TBIPEL, I. UKBAIHTSBV, G. V. Extension of the parabolic method for the Bethod of the optimization of the load-carrying transonic flow. I - Steady flow. II - Unsteady structure of wing on rigidity during variation flow by the distribution of thickness ratio A75-35215 [AD-A007317] H75-23521 TEBEB, F. DJTEBSTELLEB, L. P. Generalized dynamic engine simulation techniques Studies and research on marine hulls working with for the digital computers natural ground effect N75-23593 S75-23175 TEBVO, S. K. OPPALOBI, B. Control design considerations for variable Stochastic model for fatigue crack size and cost geometry engines effective design decisions N75-23583 [AIAA PAPEE 75-766] A75-32656 THAHES, F. C. Dse of numerically generated body-fitted coordinate systems for solution of the Havier-Stokes eguations VACEK, P. A75-31186 Diagnostics of jet aero-engines by means of TBOBPSOH, D. S. spectral analysis of lubricating oil Program to improve the fracture toughness and A75-32170 fatigue resistance of aluminum sheet and plate VAKHHIAHIHA, B. B. for aircraft applications, volume 2 Application of thin-layer chromatography for [AD-A003417] N75-23775 determining the wearing capacity of additives TBOBPSOH, E. B. contained in petroleum-based aviation oils Exhaust plume temperature effects on nozzle A75-35300 afterbody performance over the transonic Bach VAH HOYSBH, B. S. number range Design and development of low-cost, self-contained H75-23501 bearing lubrication systems for turbine engines THOBPSOH, J. F. A75-31121 Dse of numerically generated body-fitted VAHCE, J. B. coordinate systems for solution of the High-speed rotor dynamics - An assessment of Navier-Stokes equations current technology for small turboshaft engines A75-34186 A75-31127 THOBHLET, S. A. H. VAHFOSSBH, G. J., JR. The measurement of the transonic spillage drag of External fins and ejector action for reducing the a supersonic intake infrared emission of engine exhaust ducting H75-23188 [HASA-TB-X-3212] B75-25094 TIESTBAHON, P. 7EBBOLECZ, P. R. Computer-augmented design of aircraft wing Exhaust pollutant emissions from swirl-can structures combustor module arrays at parametric test N75-2355U conditions TIFFABY, C. F. [HASA-TB-X-3237] H75-21716 New Air Force reguirements for structural safety, VICKESS, B. J. durability and life management Dse of simulation in the design, development and [AIAA PAPEB 75-781] A75-32668 testing of power plant control systems TOBBACH, I. -> B75-23595 The effects of atmospheric stability, turbulence, VIEHBBGBB, G. and wind shear on aircraft wake behavior Detailed experimental and theoretical analysis of A75-35126 the aerodynamic interference between lifting TOBISAKI, T. jets and the fuselage and wing Experimental results of full scale air-cooled H75-23509 turbine tests VIETS, H. [ASBE PAPEB 75-GT-116] A75-31653 Concurrent mixing and diffusion in three dimensions [AIAA PAPEB 75-873] A75-35170 B-16 PEBSOBAJ. AOTHOB IHDEX ZAHOLi, 6. H. BIHHEB, B. H. w A holographic visor helmet-mounted display system A75-35283 BAGSEB, L. 0. BIRTH, C. J. Software management and the compiler KAflex drive shaft coupling for DH-1 helicopter. A75-35264 Design refinement BiLKEB, S. C. [AD-A008365] B75-24731 Isolating nozzle afterbody interaction parameters BISLEB, D. C. and size effects: A new approach A study of casing treatment stall margin 875-23503 improvement phenomena BiLKEB, H. J. [AS8E PAPEB 75-GT-60] A75-34613 Propulsion system structural integration and BOLF, J. 0. engine integrity; Proceedings of the Symposium, Digital flight control system for tactical fighters U.S. Baval Postgraduate School, Honterey, [AD-A002686] B75-24757 Calif., September 3-6, 1974 IOOD, I. D. A75-34112 The motion of wake vortices in the terminal BALKLET, K. B. environment Image system solution for store aerodynamics with A75-35424 interference. II BOOLBY, J. B. A75-33U37 Flight service evaluation of PRD-19/epoxy BASSOB, B. A., JE. composite panels in wide-bodied commercial Droplet diameter and size distribution of JP-4 transport aircraft fuel injected into a subsonic airstream [NASA-CR-132647] H75-24719 [AD-A007687] B75-24192 BOOLLETT, B. B. BATEBS, J. H. Transonic off-design drag and performance of three A digital controller applied to the limitation of mixed-compression axisymmetric inlets reheat combustion roughness [NASA-TH-X-3215] B75-23602 N75-23586 ROBHLET, 0. H. •ATEBS, J. P. Dynamic heave-pitch analysis of air cushion Nondestructive holographic techniques for landing systems structures inspection [SASA-CR-2530] N75-24721 [AD-A007850] N75-23946 10, J. H. HATKIBS, I. On some problems encountered in a theoretical Airport noise reduction forecast. Volume 2: BEF study of the external flow over a nozzle computer program description and user's manual configuration in transonic flight [PB-239388/2] B75-24772 1175-23499 HEAB, J. 0. Exhaust pollutant emissions from swirl-can combustor module arrays at parametric test conditions YAGER, T. J. [NASA-TB-X-3237] N75-24746 The effect of chine tires on nose gear water-spray HEBER, 0. A. characteristics of a twin engine airplane A three-dimensional solution of flows over wings [NASA-TB-X-72695] H75-23555 with leading-edge vortex separation rABABOTO, A. [AIAA PAPEB 75-866] A75-33953 Experimental results of full scale air-cooled iEISS, B. I. turbine tests High-capacity transport planes as modern air [ASHE PAPER 75-GT-116] A75-34653 freight systems YAHAHAKA, K. [HASA-TT-F-16396] 1175-23533 Preliminary study of low emission gas turbine BEBTZ, B. H., JR. combustor with airblast fuel atomizer Effectiveness of spoilers on the GA(H)-1 airfoil [ASHE PAPER 75-GT-31] A75-34588 with a high performance Fowler flap YABABE, J. B. [BASA-CR-2538] B75-2348U Response of aircraft structural compartments to BHEBLBB, H. A. blast pressures and fragments from high Small antennas explosive projectiles A75-35827 [AIAA PAPER 75-751] A75-32652 •BITE, C. G. YABG, J.-H. Reliability specification for gas turbine control Statistical estimation of service cracks and systems maintenance cost for aircraft structures B75-23581 [AIAA PAPEB 75-767] A75-32657 SHITE, 0. 1. IOSHIDA, T. Propulsion system and airframe structural Experimental results of full scale air-cooled integration program turbine tests A75-34118 [ASBE PAPER 75-GT-116] A75-34653 BICHHAHH, K. YODHG, L. C. Bind tunnel tests for the determination of the Review of hammershock pressures in aircraft inlets behavior of aircraft external loads which are A75-34115 dropped YOBCZYK, B. F. A75-35098 Test and performance criteria for airplane BIDHALL, S. B. antiskid systems The development of experimental techniques for the [AD-A008536] B75-24730 study of helicopter rotor noise YDSHIH, A. I. [N&S&-CR-137684] 1175-23611 Experimental study of heat transfer during flow BIGGIHS, J. B. around uncambered delta wings with blunted edges Sound and vibration measurements for Concorde [AD-A007316] N75-23524 supersonic transport and subsonic jet aircraft YOSKA, J. A. [PB-238748/8] N75-24436 HASA refan program status BILCOI, F. A. [HASA-TH-X-71705] B75-23570 Reynolds number effects on boattail drag of exhaust nozzles from wind tunnel and flight tests H75-23506 BILLHBE, A. C. ZABOLA, G. I. Reverse thrust experience on the Concorde Reproduction of the interaction of aerodynamic B75-23496 loads and structural distortions during strength BILSOH, D. B. tests The S-3A carrier suitability demonstration [AD-A007661] B75-23520 A75-3361U B-17 ZIHKHiB, B. E. PEBSOBiL AUTEOB IBOEZ ZIHKBAfl, B. E. Program to improve the fracture toughness and fatigue resistance of aluminum sheet and plate for aircraft applications, volume 2 [AD-A003U17] H75-23775 ZOLLIHGEB, J. B. Structural integrity for propulsion systems A75-34113 ZOKOSKI, E. B. Experiments concerning the response of supersonic nozzles to fluctuating inlet conditions [ASHE PAPEB 75-Gl-llO] A75-3M597 ZfAiS, B. J. A calculation method for unsteady subsonic flow about harmonically oscillating King-body configurations [AIAA PAPEB 75-86»] A75-33951 B-18 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING /A Special Bibliography (Suppl 61) SEPTEMBER 1975 Typical Contract Number Index Listing HAS2-768U H75-23611 505-10-21 B75-24722 HAS2-7888 875-24735 505-11-21 B7 5-24671 HAS2-8135 S75-23534 505-11-21- 02 B75-23514 KiSK-2183 H75-10036 HAS2-8268 H75-23483 B7 5-23559 HAS2-8503 H75-23543 505-11-31- 02 B75-24673 HAS2-8599 H75-24674 51«-52-01 B75-23479 1175-24675 514-54 B75-23557 B75-24676 744-01-01 B75-24720 BAS3-15707 A75-34613 760-60-01- 0900 HAS3-17763 B75-24747 B75-24677 Listings in this index are arranged alphanumencally by contract number HAS3-17842 H75-24737 975-50-01-10 H75-24760 Under each contract number the accession numbers denoting documents HAS3-17855 A75-34566 BAS3-18909 H75-24897 that have been produced as a result of research done under that contract BAS4-1845 A75-32670 are arranged m ascending order with the IAA accession numbers appearing BAS8-26600 A75-35420 first The accession number denotes the number by which the citation is BAS8-27387 A75-35411 identified m either the lAAot STAR section BAS8-30617 A75-32656 SG1-22-009-640 A75-34535 AF PROJ. 1369 DOT-F170HA-2MU8 BGR-05-007-1414 B75-24730 H75-23531 A75-32667 AF PROJ. 1987 N75-2a698 NGR-05-020-663 B7S-24754 DOT-FA72HAI-356 1175-24756 B75-24757 S75-23530 BGR-11-002-169 AF PROJ. 30148 DOT-OS-20088 H75-21771 A75-32656 H75-23603 H75-2I4772 UGH-17-002-072 875-23617 DOT-OS-a0121 N75-211D36 B75-23484 B75-24728 DRHE-70/1i(5 A75-35U50 HGB-22-004-030 AP PROJ. 3115 DRME-71/319/2 1175-23477 N75-23605 A75-3295K B75-23478 AP PROJ. 718U DHflE-122/t A75-35i(50 BGR-25-001-055 B75-24725 EPA-68-01-2229 A75-34186 AF PROJ. 7351 N75-21186 BGB-33-016-167 H75-23775 117 5-21187 A75-30193 875-23946 F33615-71-C-1871 A75-34196 B75-24923 K75-239f6 A75-34975 AF PROJECT 735106 F33615-72-C-10t5 BGH-33-016-201 A75-34116 A75-32652 A75-34193 AF TASK 7351 A75-3I4116 F33615-72-C-1058 A75-34975 AF-AFOSR-72-2167 N75-24751 NGR-34-002-179 B75-23494 H75-21757 B75-24677 AF-AFOSR-74-2712 F33615-72-C-1203 BGB-36-010-024 A75-32662 H75-2U923 B75-23573 AT(11-1)-3077 F33615-72-CT1801 BG8-44-001-011 A75-34193 A75-3i)1«6 B75-23567 A75-30 196 F33615-73-C-0173 SGB-114-00 1-157 A7S-34975 N75-21I728 A75-34195 DA PROJ. 1F2-62203-AH-86 F33615-73-C-3017 BG8-49-001-049 N75-24727 N75-2I1730 B75-25057 DA PROJ. 1H2-62303-A-214 F33615-73-C-311I) BGB-50-007-001 H75-23526 A75-33960 A75-33950 B75-24693 F3361S-73-C-'4110 BGB-52-012-008 DA-31-l24-ABO(D)-247 A75-35283 A75-32654 N75-24689 F33615-71-C-2035 BHC A-7799 A75-33966 DAAA21-74-C-0195 N75-23617 NSF GK-35004 A75-32662 N75-23528 F33615-714-C-3084 BSG-1099 A75-32657 DAAH01-74-C-0183 A75-35172 NSG-7072 A75-32697 N75-23499 F33615-7II-C-309U N00014-74-C-0373-P0001 DAAH03-74-C-0405 A75-35171 A75-34186 1175-23526 F3361S-71-C-UOU1 H00019-72-C-0187 DAAJ01-71-C-0840 N7 5-21 729 A75-34131 B75-24724 F33615-7»-C-5060 N00019-74-C-0194 DAAJ01-72-C-0381 N75-23775 B75-24926 A75-34130 F33615-7I4-C-5151 B00029-73-C-0021 DAAJ01-72-C-0900 A75-33762 A75-34628 S75-24731 MASS-2U81 S75-23H80 S00140-7II-C-0618 DAAJ02-68-C-0002 NASS-2U83 N75-23533 B75-23604 A75-34130 NASW-2185 K75-21723 S62269-74-C-0523 DAAJ02-71-C-0050 NAS1-6666 H75-2U738 B75-24733 A75-34130 1175-24 712 PROJ. FEDD B75-24678 DAAJ02-7I4-C-0016 H75-24713 501-03-11 N75-23549 H75-21727 HAS1-107M9 875-24032 H75-23606 DAAJ02-74-C-0028 H75-2U717 504-09-21-01 B75-23556 B75-23562 UAS1-11621 N75-24719 505-02-31-01 B75-25221 DAAJ02-7U-C-0039 HAS1-12020 M75-24672 505-03 M75-24740 A75-32705 NAS1-12185 A75-33953 505-03-12-05 B75-24744 DAHC014-72-C-0029 HAS1-12403 S75-24721 505-04 875-23602 H75-21690 HAS1-12424 A75-34190 875-24746 DAHCOa-7«-C-0001 NAS1-12506 N75-24718 B75-25094 1175-23608 HAS1-12709 A75-32693 505-05 B75-24745 DAJA37-73-C-2881 NAS1-13233 075-23568 505-06-11-02 875-24681 N75-21732 NAS1-13496 S75-23558 505-06-22 B75-23481 DGBST-69-01-723 HAS2-6973 S75-23U82 505-06-31-02 «75-24678 N75-23K75 BAS2-7208 1175-24696 505-08-31-01 875-23555 NAS2-7475 B75-23544 505-10-11-03 B75-23484 C-1 NASA-Langley, 1975 1 Report No 2 Government Accession No 3 Recipient's Catalog No NASA SP-7037 (61) 4 Title and Subtitle 5 Report Oa'e AERONAUTICAL ENGINEERING September 1975 A Special Bibliography (Supplement 61) 6 Performing Organization Code 7 Author(s) 8 Performing Organization Report No 10 Work Unit No 9 Performing Organization Name and Address National Aeronautics and Space Administration 1 1 Contract or Grant No 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 1 6 Abstract Th s bibliography lists ^18 reports, articles, and other documents intro- duced into the NASA scientific and technical information system in August 1975. 17 Key Words (Suggested by Author(s) ) 18 Distribution Statement Aerodynamics Aeronautical Engineering Aeronaut ics Unclassified - Unlimited Bibl iographies 19 Security Qassif (of this report) 20 Security Classif (of this page) 21 No of Pages 22 Price" Unclass if ied Unclassified ^2k $^.00 HC For sale by the National Technical Information Service, Springfield, Virginia 22161 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 sen/ices as reference assistance, mterhbrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention CALIFORNIA MASSACHUSETTS University of California. 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