NASA SP-7G37(67) •c -4 3- -J AERONAUTICAL ENGINEERING & V* A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplements? FEBRUARY 1976 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION https://ntrs.nasa.gov/search.jsp?R=19760012974 2020-03-22T17:00:26+00:00Z ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges: STAR(N-10000 Series) N 76-10001 N 7 6 - 1 1 9 9 2 IAA (A-10000 Series) A 76-10001 A 76-12754 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 (67) AERONAUTICAL ENGINEERING A Special Bibliography Supplement 67 A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in January 1 976 in • Scientific and Technical Aerospace Reports (STARI • International Aerospace Abstracts (IAA) Si leiinju and Technu al Information Office FE BRUARY 1976 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION \Va\hnifiitii O C This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161, for $4 00 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 341 reports, journal articles, and other documents originally announced in January 1976 in Scientijic and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts eo) M Abejon Adamez lAA/lngenieria AeronSuttca y Astronautica, vol 27, Aug Sept 1975, p 7-20 42 refs In Spanish The system concept is examined along with a number of aspects of systems engineering The large social, technical, and economic systems and organizations of contemporary life are considered An investigation is conducted concerning questions of systems engi- neering in the field of transportation and a description is given of the characteristics of air transport from the point of view of systems engineering The character of the airport as an interphase between air transport and land transoortation is discussed and the technological, economical, and organizational problems of transport integration are studied G R A76-12156 ft The safety of flight operations (Seguridad de las operaciones en vuelo) R Fernandez lAA/lngenierfa Aeronautica y Astronautica, vol 27, Aug-Sept 1975, p 57-72 In Spanish Aircraft accidents and their causes are examined and typical operational problems are investigated Approach and landing opera- tions are considered, taking into account the ultimate operational phase, approach procedures designed to reduce noise, details of landing procedures, wind effects, and effects produced by water, snow, ice, mud, and residue of oil on the runway Other types of accidents are related to different forms of turbulence in connection with thunderstorms, air currents near mountains, clear-air turbu- lence, and flow effects in the wake of a preceding aircraft Collision-related accidents are also discussed and attention is given to cases in which the human factor must be held responsible for the accident G R A76-12159 Airline profit pinch clouds harvest of gams W H Gregory Aviation Week and Space Technology, vol 103, Nov 10, 1975, p 32-34,39,41 It is pointed out that enough new technology is at hand or clearly on the horizon to build a more economic, lower fuel consumption commercial transport However, because of economic factors partly related to inflation it is uncertain whether and when such a transport will be developed It is found that airlines and transport aircraft manufacturers are more sensitive to violent inflation than other industries Attention is given to new technologi- cal developments and the prospects for the incorporation of these developments in the next-generation aircraft G R A76-12160 Builders vie for short/medium market D E Fink Aviation Week and Space Technology, vol 103, Nov 10,1975, p 43-45,51, 52 American aerospace companies agree that there is a need for a 180-200 passenger aircraft with operating economics which meet the 15 A76-12161 requirements of the 1980s However, the design approach concerning such an aircraft differs for each company The merits of the various approaches are discussed, taking into account questions of fuel economy and flight characteristics Attention is given to tunnel tests, aspects of ramp compatibility, and noise requirements G R A76-12161 Short-haul designs include trade-offs. B M Elson Aviation Week and Space Technology, vol 103, Nov 10, 1975, p 73, 75, 77, 78 Research is conducted to develop the technological options that wtl\ permit a wide range of trade-offs among cost, performance, traffic, and environmental factors in the design of short-haul transports for the 1980s and beyond The work involves a combina- tion of analysis, simulation, wind tunnel tests, and flight tests The characteristics of research aircraft for the investigations are discussed Attention is given to developments concerning the design of aircraft propellers, fuel-saving measures, and active controls programs G R A76-12285 # Optimum design of axial flow fans with cambered blades of constant thickness M Blaho (Budapesti Muszaki Egyetem, Budapest, Hungary) Penodica Polytechnica, Mechanical Engineering, vol 19, no 2, 1975, p 79-89 An investigation is conducted o1 the losses of cascades in conjunction with the outlet losses Particular attention is given to cambered blades, which are most frequently employed in fans Questions of optimum camber design are examined and the correlation between optimum lift to drag ratio and cascade density is considered The variation of the optimum lift to drag ratio as a function of the approach angle is also discussed along with the tosses in axial flow fans A description of the calculation of force factors in cascades is provided in an appendix G R A76-12300 Towards hypersomcs Flight International, vol 108, Oct 30, 1975, p 657, 658 Continuing NASA and USAF research on flight at M4 to Ml 2, is reviewed Operational hypersonic vehicles might appear in a leap fragging advance over their supersonic counterparts The blended- wmg X-24C air-launched lifting body is useful as a versatile flying tdst bed Turboramjets and supersonic combustion ramjets (scramjets) are considered as MS powerplants (two set of power- plants, at best structurally integrated, will be required for practical !operation) Hypersonic aerokmetic heating and ways of designing against it (refractory skin, ablative heat-sink insulation, active cooling with cryogenic fuels) are discussed R D V A76-12399 ff Some general questions concerning the vibra- tions of launch vehicles III - High-frequency vibrations (Quelques questions generates concernant les vibrations des lanceurs III - Vibrations A haute frequence) J Lacaze (Agence Spatiale Europe- enne, Division Ariane, Paris, France) ESA Scientific and Technical Review, vol 1,no 1,1975, p 36-66 20 refs In French The response of a wall exposed to a random acoustic field is examined as a function o1 the level, the spectrum, and spatial correlation of the noise The transmission of vibrations between various media, acoustic volumes, and walls is studied by using the Statistical Energy Analysis (SEA) method These studies yield conclusions regarding the behavior of launcher and satellite equip- ments P T H A76-12486 # Simulation study of aircraft handling during engine failure (Issledovanie pilotirovamia samoleta pri otkaze dvi- gatelia na modeliruiushchem stende) A V Polukhm, A M Fal', and V A Bimbas (Kievskn Institut Inzhenerov Grazhdanskoi Aviatsn, Kiev, Ukrainian SSR) In Ergonomic dynamic control systems Kiev, Izdatel'stvo Naukova Dumka, 1975, p 150-154 5 refs In Russian The effect of a failure of one of the turboprop engines of the IL-18 aircraft on its handling characteristics is studied Some criteria are introduced which allow estimation of handling criteria when an outer engine has failed Simulation results are given which show the effect of the time taken by the pilot to detect the engine failure on the process of parrying the dangerous angular variations of the aircraft P T H A76-12487 ff Universal system for loading the control ele- ments of flight simulators (Universal'naia sistema zagruzhi organov upravlenna dha imitatorov poleta) V A Vasilenko and V lu Dmitnev (Kievskn Institut Inzhenerov Grazhdanskoi Aviatsn, Kiev, Ukrainian SSR) In Ergonomic dynamic control systems Kiev, lidatel'stvo Naukova Dumka, 1975, p 154-156 In Russian The paper describes briefly a setup for loading the control elements of flight simulators and trainers in order to reproduce the forces on the control elements, the displacement range of the control elements of the simulated aircraft, the effect of trimming, and nonlmeanty in the aircraft control system The chief unit in the loading system is an asynchronous motor with hollow rotor The system is applicable for simulating aircraft with direct, reversible power-assisted, or irreversible power-assisted control P T H A76-12498 The asset management approach to spares support M D Basch (Federal Express Corp, Memphis, Tenn ) Logistics Spectrum, vol 9, Fall 1975, p 37-39,42 A program of asset management applicable to commercial aircraft spare parts support is discussed which achieves required service levels at reduced costs through integration of inventory, transportation, and warehousing The program involves implementa- tion of centralized back up support, objective forecasting and planning, and a positive inventory control system A practical model for determining the least costs sparing levels on a national or local basis is presented C K D A76-12500 The airship - Phoenix or Dodo F J Regan (U S Navy, Naval Surface Weapons Center, Silver Spring, Md ) Machine Design, vol 47, Nov 13,1975, p 20-22. 24 A new lease on life for airships, in the form of hybrids with fixed-wing and rotary-wing heavier-than-air craft, is considered in terms of engineering feasibility and economic competitiveness Drone aerostats for nonmilitary monitoring and surveillance, 1000-T heavy- lift balloon-helicopter cranes, fixed-wing four-jet dirigibles, aerostat- helicopter hybrids, heavy-duty hybrids might compete with jumbo- jet freighters and supertankers in transporting large indivisible loads Techniques not available in the 30s that could render such concepts workable include computer stress analysis, vectored thrust and high lift, high-strength composites, computer flight control and trim adjustment, variable and tillable control surfaces R D V A76-12516 The present outlook for aerostatic techniques (Perspectives actuelles des techniques aerostatiques) P Contensou (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France) Sciences et Techniques, Oct 15, 1975, p 21-24 In French A historical overview of the relative advances and lags in the development, use, and acceptance of aerostats and various types of aerodynes (gliders, fixed-wing aircraft, rotary-wing aircraft) focuses on the coefficient of friction (of the vehicle against the supporting, buoyant, or resisting medium) and on various extra-technical factors (cost, congestion, noise, total energy and fuel consumption, energy and fuel consumption per unit payload, public attitudes toward technical progress) that might offer aerostatic vehicles a change at a comeback Conveying heavy and cumbersome bulk freight, where short travel time and fast speed are not essential factors, is seen as promising for economic use of aerostats, while control and maneu- verability in docking and cruise are viewed as the major problems, given recent advances in materials science and design computation techniques R D V 16 N76-10010 STAR ENTRIES was developed for future applications m which predicted airloads would be incorporated in an acoustics analysis to attempt to predict and analyze impulsive noise (blade slap) The analysis was applied to a hovering full scale rotor for which impulsive noise was recorded in the presence of ambient wind The predicted tip vortex coordinates are in reasonable agreement with the test data and the blade airload solutions converged to a periodic behavior for an imposed steady ambient wind conditions Author N76-10002*# Massachusetts Inst of Tech Cambridge ,Measurement Systems Lab A PASSIVE GUST ALLEVIATION SYSTEM FOR A LIGHT AIRCRAFT Final Report Phillippe Roesch and Raymond 8 Harlan Washington NASA Oct 1975 136 p refs (Grant NGR-22-009-782) (NASA-CR-2605 RE-90) Avail NTIS HC $5 75 CSCL01C A passive aeromechamcal gust alleviation system was examined for application to a Cessna 172 The system employs small auxiliary wings to sense changes in angle of attack and to drive the wing flaps to compensate the resulting incremental lift The flaps also can be spring loaded to neutralize the effects of variations in dynamic pressure Conditions for gust alleviation are developed and shown to introduce marginal stability if both vertical and horizontal gusts are compensated Satisfactory behavior is realized if only vertical gusts are absorbed however elevator control is effectively negated by the system Techniques to couple the elevator and flaps are demonstrated to restore full controllability without sacrifice of gust alleviation Author N76-10006*# National Aeronautics and Space Administration Langley Research Center Langley Station Va EFFECTS OF JET EXHAUST GAS PROPERTIES ON EXHAUST SIMULATION AND AFTERBODY DRAG William B Compton III Washington Oct 1975 128 p refs (NASA-TR-R-444 L-10183) Avail NTIS HC $5 75 CSCL 01A The effect of varying the jet exhaust s ratio of specific heats gas constant and temperature on airplane afterbody drag was investigated Jet exhaust simulation parameters were evaluated also Subsonic and transonic tests were made using a single nacelle model with afterbodies having boattail angles of 10 deg and 20 deg Besides air three other jet exhaust gases were investigated The ratios of specific heats gas constants and total temperatures of the four exhaust gases ranged from 1 40 to 126 287 to 376 J/kg-K and 300 to 1013 K respectively For steep boattail angles and transonic speeds and typical turbojet pressure ratios the current data indicate that the use of air to simulate a dry turbojet exhaust can result in an overprediction of afterbody drag as high as 17 percent of the dry turbojet value Author N76 10004*$ National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio POPPET VALVE CONTROL OF THROAT STABILITY BYPASS TO INCREASE STABLE AIRFLOW RANGE OF A MACH 2 5 INLET WITH 60 PERCENT INTERNAL CONTRACTION Glenn A Mitchell and Bobby W Sanders Washington Oct 1975 49 p refs (NASA-TM-X-3297 E-8382) Avail NTIS HC S3 75 CSCL 200 The throat of a Mach 2 5 inlet with a coldpipe termination was fitted with a stability-bypass system System variations included several stability bypass entrance configurations Poppet valves controlled the bypass airflow The inlet stable airflow range achieved with each configuration was determined for both steady state conditions.and internal pulse transients Results are compared with those obtained without a stability bypass system Transient results were also obtained for the inlet with a choke point at the diffuser exit and for the inlet with large and small stability bypass plenum volumes Poppet valves at the stability bypass exit provided the inlet with a stable airflow range of 20 percent or greater at all static and transient conditions Author N76-10005*# United Technologies Research Center East Hartford Conn TRANSIENT A IRLOAD COMPUTER ANALYSIS FOR SIMULATING WIND INDUCED IMPULSIVE NOISE CONDI- TIONS OF A HOVERING HELICOPTER ROTOR Gerald F Hall Oct 1975 48 p refs Sponsored in part by Army Air Mobility R and D Lab Moffett Field Calif (Contract NAS2-7025) (NASA-CR-137772) Avail NTIS HC S3 75 CSCL 01A A numerical analysis was developed to determine the airloads on helicopter rotors operating under near-hovering flight conditions capable of producing impulsive noise A computer program was written in which the solutions for the rotor tip vortex geometry inflow aeroelastic response and airloads are solved in a coupled manner at sequential time steps with or without the influence of an imposed steady ambient wind or transient gust The program N76-10007*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC ANALYSES REQUIRING A D V A N C E D COMPUTERS. PART 1 Washington 1975 710 p refs Conf held at Hampton Va 4-6 Mar 1975 (NASA-SP-347-PM) Avail NTIS H C S 1 7 2 5 CSCL 098 Papers are presented which deal with results of theoretical research on aerodynamic flow problems requiring the use of advanced computers Topics discussed include viscous flows boundary layer equations turbulence modeling and Navier-Stokes equations and internal flows N76-10010* Douglas Aircraft Co Inc El Segundo Calif CALCULATION OF THREE-DIMENSIONAL COMPRESSIBLE LAMINAR AND TURBULENT B O U N D A R Y LAYERS CALCULATION OF THREE-DIMENSIONAL COMPRESSIBLE BOUNDARY LAYERS ON ARBITRARY WINGS Tuncer Cebeci Kalle Kaups Judy Ramsey and Alfred Moser In NASA Langley Res Center Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 41-76 refs CSCL 01A A very general method for calculating compressible three- dimensional laminar and turbulent boundary layers on arbitrary wings is described The method utilizes a nonorthogonal coordinate system for the boundary-layer calculations and includes a geometry package that represents the wing analytically In the calculations all the geometric parameters of the coordinate system are accounted for The Reynolds shear-stress terms are modeled by an eddy-viscosity formulation developed by Cebeci The governing equations are solved by a very efficient two-point finite-difference method used earlier by Keller and Cebeci for two-dimensional flows and later by Cebeci for three-dimensional flows Author 17 N76-10015 N76-10015* Grumman Aerospace Corp Bethpage. NY ASYMPTOTIC THEORY OF TWO-DIMENSIONAL TRAILING EDGE FLOWS R E Melnik and R Chow In NASA Langley Res Center Aerodynamic Analysis Requiring Advanced Computers, Pt 1 1975 p 177-249 refs (Contract NAS1-12426) CSCL 20D Problems of laminar and turbulent viscous interaction near trailing edges of streamlined bodies are considered Asymptotic expansions of the Navier-Stokes equations in the limit of large Reynolds numbers are used to describe the local solution near the trailing edge of cusped or nearly cusped airfoils at small angles of attack in compressible flow A complicated inverse iterative procedure, involving finite-difference solutions of the triple-deck equations coupled with asymptotic solutions of the boundary values, is used to accurately solve the viscous interaction problem Results are given for the correction to the boundary-layer solution for drag of a finite flat plate at zero angle of attack and for the viscous correction to the lift of an airfoil at incidence A rational asymptotic theory is developed for treating turbulent interactions near trailing edges and is shown to lead to a multilayer structure of turbulent boundary layers The flow over most of the boundary layer is described by a Lighthill model of inviscid rotational flow The main features of the model are discussed and a sample solution for the skin friction is obtained and compared with the data of Schubauer and Klebanoff for a turbulent flow in a moderately large adverse pressure gradient Author N76-10021* National Aeronautics and Space Administration Ames Research Center Moffett Field Calif SIMULATION OF TURBULENT TRANSONIC SEPARATED FLOW OVER AN AIRFOIL George S Deiwert John B McDevitt and Lionel L Levy Jr In its Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 419-436 refs 01-02) CSCL 20D A code developed for simulating high Reynolds number transonic flow fields of arbitrary configuration is described This code in conjunction with laboratory experiments is used to devise and test turbulence transport models which may be suitable in the prediction of such flow fields, with particular emphasis on regions of flow separation The solutions describe the flow field including both the shock-induced and traihng-edge separation regions in sufficient detail to provide the profile and friction drag Author N76-10023* Mississippi State Univ. Mississippi State NUMERICAL SOLUTION OF THE NAVIER-STOKES EQUA- TIONS FOR ARBITRARY TWO-DIMENSIONAL AIRFOILS Frank C Thames Joe F Thompson and C Wayne Mastm In NASA Langley Res Center Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 469-530 refs (Grant NGR-25-001-055) CSCL 20D A method for numerical solution of the Navier-Stokes equations for the flow about arbitrary airfoils or other bodies is presented This method utilizes a numerically generated curvilinear coordinate system having a coordinate line coincident with the body contour Streamlines velocity profiles and pressure and force coefficients for several airfoils and an arbitrary rock are given Potential flow solutions are also presented The procedure capable of treating multiple-element airfoils and potential flow results are presented Author N76-10026* Massachusetts Inst of Tech Cambridge COMPUTATIONAL ASPECTS OF THE PREDICTION OF MULTIDIMENSIONAL TRANSONIC FLOWS IN TURBOMA- CHINERY David A Oliver and Panagiotis Spans In NASA Langley Res Center Aerodynamic Analyses Requiring Advanced Computers. Pt 1 1975 p 567-585 refs CSCL 20D The analytical prediction and description of transonic flow. in turbomachmery is complicated by three fundamental effects (1) the fluid equations describing the transonic regime are inherently nonlinear (2) shock waves may be present in the flow, and (3) turbomachine blading is geometrically complex possessing large amounts of curvature stagger, and twist A three-dimensional computation procedure for the study of transonic turbomachine fluid mechanics is described The fluid differential equations and corresponding difference operators are presented the boundary conditions for complex blade shapes are described and the computational implementation and mapping procedures are developed Illustrative results of a typical unthrottled transonic rotor are also presented Author N76-10O27* National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio TIME-DEPENDENT TRANSONIC FLOW SOLUTIONS FOR AXIAL TURBOMACHINERY John Erdos (Advanced Technol Labs Inc ) Edgar Alzner (Advanced Technol Labs Inc ) Paul Kalben (Advanced Technol Labs Inc) William McNally and Simon Slutsky (Polytechnic Inst of New York) In its Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 587-621 refs CSCL 200 Three-dimensional unsteady transonic flow through an axial turbomachine stage is described in terms of a pair of two- dimensional formulations pertaining to orthogonal surfaces namely a blade-to-blade surface and a hub-to-casing surface The resulting systems of nonlinear inviscid compressible equations of motion are solved by an explicit finite-difference technique The blade-to-blade program includes the periodic interaction between rotor and stator blade rows Treatment of the boundary conditions and of the blade slipstream motion by a characteristic type procedure is discussed in detail Harmonic analysis of the acoustic far field produced by the blade row interaction including an arbitrary initial transient is outlined Results from the blade-to-blade program are compared with experimental measurements of the rotating pressure field at the tip of a high-speed fan The hub-to-casing program determines circumferentially averaged flow properties on a meridional plane Blade row interactions are neglected in this formulation but the force distributions over the entire blade surface for both the rotor and stator are obtained Results from the hub-to-casing program are compared with a relaxation method solution for a subsonic rotor Results are also presented for a quiet fan stage which includes transonic flow in both the rotor and stator and a normal shock in the stator Author N76-10028* National Aeronautics and Space Administration Ames Research Center, Moffett Field Calif A COMPARISON OF A SHOCK-CAPTURING TECHNIQUE WITH EXPERIMENTAL DATA FOR THREE-DIMENSIONAL INTERNAL FLOWS Leroy L Presley In its Aerodynamic Analyses Requiring Advanced Computers, Pt 1 1975 p 623-642 refs CSCL 20D Shock-capturing solutions for an axisymmetnc supersonic inlet at small angles of attack are obtained Good overall agreement between the shock-capturing solutions and experimental data is shown except in regions of strong viscous effects or boundary-layer removal Although the results indicate a strong potential for the use of shock-capturing or finite-difference solutions for internal flows, improvement in the ability to handle the reflection of strong Shockwaves having downstream Mach numbers near 1 is needed Author 18 N76-10036 N7S-10029* National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif INTERNAL AND EXTERNAL AXIAL CORNER FLOWS Paul Kutler Vijaya Shankar (Iowa State Umv of Sci and Technol), Dale A Anderson (Iowa State Umv of Sci and Technol) and Reese L Sorenson In its Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 643-658 refs CSCL 20D The mviscid, internal and external axial corner flows generated by two intersecting wedges traveling supersonically are obtained by use of a second-order shock-capturing finite-difference approach The governing equations are solved iteratively in conical coordinates to yield the complicated wave structure of the internal corner and the simple peripheral shock of the external corner The numerical results for the internal flows compare favorably with existing experimental data Author N76-10030* Advanced Technology Labs Inc. Westbury NY NUMERICAL METHODS FOR THE CALCULATION OF THREE-DIMENSIONAL NOZZLE EXHAUST FLOW FIELDS Sanford M Dash and Paul D DelGuidice In NASA Langley Res Center Aerodynamic Analyses Requiring Advanced Computers Pt 1 1975 p 659-701 refs (Contract NAS1-12726) CSCL 20D Numerical codes developed for the calculation of three- dimensional nozzle exhaust flow fields associated with hypersonic airbreathing aircraft are described Both codes employ reference plane grid networks with respect to three coordinate systems Program CHAR3D is a characteristic code utilizing a new wave preserving network within the reference planes, while program BIGMAC is a finite difference code utilizing conservation variables and a one-sided difference algorithm Secondary waves are numerically captured by both codes while the underexpansion shock and plume boundary are treated discretely The exhaust gas properties consist of hydrogen-air combustion product mixtures in local chemical equilibrium Nozzle contours are treated by a newly developed geometry package based on dual cubic splines Results are presented for simple configurations demon- strating two- and three-dimensional multiple wave interactions Author pressure distributions lift moments and local boundary-layer properties on each element of an arbitrarily arranged slotted airfoil in attached flow The final viscous solution was obtained by an iterative technique for successively combining an mviscid solution with boundary-layer displacement thicknesses The surface of each airfoil element is approximated as a closed polygon with segments represented by distributed vortex singularities The ordinary boundary-layer solution is comprised of mathematical models representing state-of-the-art technology for laminar transition and turbulent boundary layers An additional boundary- layer model was incorporated to compute the characteristics of a confluent boundary layer which reflects the merging of the upper-surface boundary layer with the slot efflux This computer program was used extensively for both the design and the analysis of airfoils Summary descriptions of the general operation and capabilities of this program and a detailed description of the major improvements that were made to the program since its initial formulation are presented Author N76-1O034* National Aeronautics and Space Administration Ames Research Center Moffett Field Calif APPLICATION OF NUMERICAL OPTIMIZATION TECH- NIQUES TO AIRFOIL DESIGN Garret N VanDerPlaats Raymond N Hicks and Earll M Murman (Flow Res Inc Los Angeles) In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 749-768 refs CSCL 20D A practical procedure is presented for automated airfoil design using numerical optimization techniques The procedure uses an optimization program based on conjugate directions for locally unconstrained problems and feasible directions for locally constrained problems This program is coupled with an aerodynam- ic analysis program which uses a relaxation method to solve the partial differential equation that governs the 'nviscid small-disturbance fluid flow Basic optimization concepts and the techniques used in the optimization program are described and the procedure for automating airfoil design is outlined Design objectives which are considered include lift maximization drag minimization and pitchmg-moment minimization various aerody- namic and geometric constraints on the design are accounted for Design results are presented to demonstrate the simplicity and generality of the method Author N76-10032* National Aeronautics and Space Administration Langley Research Center. Langley Station Va COMPUTERIZED PROCEDURES FOR AIRFOIL DESIGN Raymond L Barger and Cuyler W Brooks Jr In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 703-7 12 refs CSCL QIC Several airfoil design procedures are described The first is a procedure for designing an airfoil shape to have a prescribed surface pressure distribution it is applicable to the design of supercritical as well as subcntical airfoils The second is a computerized procedure based on the Theodorsen epsilon-function design technique and is esentially mcomdessible It also permits description of the pressure distribution with the additional feature of providing simple means for controlling important airfoil parameters The remainder of the discussion is concerned with the application of various techniques based on the epsilon-function theory to specialized design problems Author N76-10033* National Aeronautics and Space Administration Langley Research Center Langley Station Va A COMPUTER PROGRAM FOR THE ANALYSIS OF MULTIELEMENT AIRFOILS IN TWO-DIMENSIONAL SUBSONIC. VISCOUS FLOW Harry L Morgan Jr In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 713-747 refs CSCL 20D A computerized analytical model which computes the performance characteristics of multielement airfoils in subsonic viscous flow was developed The model computes the viscous N76-10035* National Aeronautics and Space Administration Ames Research Center Moffett Field Calif TSFOIL A COMPUTER CODE FOR TWO-DIMENSIONAL TRANSONIC CALCULATIONS. INCLUDING WIND-TUNNEL WALL EFFECTS AND WAVE-DRAG EVALUATION Earll M Murman (Flow Res Inc . Los Angeles) Frank R Bailey and Margaret L Johnson (Computer Sci Corp ) In its Aerodynamic Analysis Requiring Advanced Computers Pt 2 1975 p 769-788 refs CSCL 20D An up-to-date computer program to solve the transonic small-disturbance equation for two-dimensional flow past lifting airfoils was written The theoretical and numerical formulation of the code is outlined and several computed examples are included The user-oriented code is capable of computing both free-air flows and various wind-tunnel wall conditions Applications and limitations of the program are discussed Author N76-10036* National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif NUMERICAL INTEGRATION OF THE SMALL- DISTURBANCE POTENTIAL AND EULER EQUATIONS FOR UNSTEADY TRANSONIC FLOW Richard M Beam and William F Ballhaus (Army Air Mobility R and D Lab) In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 789-809 refs CSCL 20D Two methods for solving unsteady nonlinear, transonic flow problems were investigated and compared One method is to solve the Euler equations by using an implicit numerical scheme 19 N76-10037 to increase the integration time step while the second method uses semi-implicit scheme to solve the low-frequency, transonic small-disturbance potential equations Although the second method is more limited (small disturbance low frequency) than the first, it offers savings in computer time and storage requirements over the first method The details of the two methods are presented, and results from the two methods and the results of linear theory are compared The two sample motions, a sinking airfoil with steady forward velocity and an airfoil with increasing thickness, were chosen to provide a simple representa- tion of the flutter-maneuver and rotor tip motions, respectively Results are presented for an NACA 0010 airfoil undergoing simultaneous angle of attack and free stream Mach number oscillations This computation is a strip theory simulation of the flowfield about an advancing helicopter rotor Author N76-10037* National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif CALCULATION OF INVISCIO SHEAR FLOW USING A RELAXATION METHOD FOR THE EULER EQUATIONS Joseph L Steger and Harvard Lomax In its Aerodynamic Analyses Requiring Advanced Computers. Pt 2 1975 p 811-838 refs CSCL 20D A fast block relaxation method was developed for the subsonic two-dimensional Euler equations The procedure is applied to the problem of computing mviscid flow about a thin airfoil in a moderately nonuniform stream (shear flow) It is demonstrated that the technique of overlapping grid regions can be used to improve the convergence rate of block relaxation methods Solutions and possible extensions are discussed Author N76-10038* National Aeronautics and Space Administration Ames Research Center Moffett Field Canf PROCESS IN APPLICATION OF DIRECT ELLIPTIC SOLVERS TO TRANSONIC FLOW COMPUTATIONS Dale Martin In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 839-870 refs CSCL 20D Progress is described in the development and extension of a semi-direct iterative computational method for the rapid finite-difference solution of transonic flow over airfoils Additions and modifications to an earlier formulation are shown to produce stability (and therefore iterative convergence) of the iteration procedure based on use of an extended direct elliptic solver for strongly suoercntical flows governed by mixed elliptic- hyperbolic equations An improved version of an extrapolation technique introduced earlier is also described Preliminary results computed by the semi-direct method for pressure distributions on a biconvex airfoil agree with solutions computed using tne improved Murman-Cole line relaxation method The preliminary time per iteration for a 39x32 mesh on a CDC 7600 computer is 0 040 sec and a strong transonic case required 23 iterations or 092 sec These results indicate a significant potential for highly efficient transonic flow computations Author N76-10039* National Aeronautics and Space Administration Ames Research Center Moffett Field, Calif RECENT DEVELOPMENTS IN PROPULSIVE-LIFT AERODY- NAMIC THEORY Richard J Margason Long P Yip and Thomas G Gainer In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 871-895 refs CSCL 01A The progress is reviewed of propulsive-lift theories from their beginning in 1956 with Spence's development of a two- dimensional jet flap to the present general three-dimensional theories that require a large computer Results of jet-flap theories are compared for high-aspect-ratio wings with full- or partial-span blowing Applications of the jet-flap theory and the more general wing-jet interaction theories under development to exterially blown flap and upper-surface blowing configurations are a so discussed The possible direction of future developments is me icated Author • N76-10040* National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif SURVEY OF COMPUTATIONAL METHODS FOR LIFT- GENERATED WAKES Vernon J Rossow In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 897-923 refs CSCL 01A A survey is made of some computational methods that are used to predict the structure and duration of lift-generated vortices and to explore mechanisms that might significantly reduce their lifetime and hazard potential Author N76-10O42* Boeing Commercial Airplane Co Seattle Wash ADVANCED PANEL-TYPE INFLUENCE COEFFICIENT METHODS APPLIED TO SUBSONIC AND SUPERSONIC FLOWS F Edward Ehlers, Forrester T Johnson and Paul E Rubbert In NASA Langley Res Center Aerodynamic Analyses Requiring AdvancedComputers.Pt 2 1975 p 939-984 refs (Contract NAS2-7729) CSCL 20D Advanced techniques are presented for solving the linear integral equations of subsonic and supersonic potential flow in three dimensions Both analysis (Neumann) and design (Dirichlet) boundary conditions are treated Influence coefficient methods were used that encompass both source and doublet panels as boundary surfaces The methods employ curved panels possessing singularity strengths which vary as polynomials These and other features were selected to produce a stable, reliable accurate and economical scheme overcoming many problems experienced with earlier methods Computational results are presented that illustrate these advantages Author N76-1O043* National Aeronautics and Space Administration Ames Research Center Moffett Field Calif SOME RECENT APPLICATIONS OF THE SUCTION ANALOGY TO VORTEX-LIFT ESTIMATES John E Lamar In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 985-1011 refs CSCL 01A A recent extension of the suction analogy for the estimation of vortex lift along the side edge of wings is reviewed and the concept of an augmented vortex lift was developed to account for the effect of the leading-edge vortex passing downstream over an aft part of the model Applications of these extensions resulted in an improved estimating capability for a wide range of isolated sharp-edge planforms and also for multiple lifting surfaces The suction analogy concept has wider applicability at both subsonic and supersonic speeds especially in the preliminary design cycle Author N76-10044* Boeing Co. Seattle, Wash A THREE-DIMENSIONAL SOLUTION OF FLOWS OVER WINGS WITH LEADING EDGE VORTEX SEPARATION James A Weber. Guenter W Brune. Forrester T Johnson Paul Lu. and Paul E Rubbert In NASA Langley Res Center Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 1013-1032 refs (Contract NAS1-12185) CSCL 20D The application of a general, potential flow computational technique to the solution of the subsonic three-dimensional flow over wings with leading edge vortex separation is presented The method is capable of predicting forces moments, and detailed surface pressures on thin sharp-edged wings of rather arbitrary planform The wing geometry is arbitrary m the sense that leading and trailing edges may be curved or kinked and may have arbitrary camber and twist distributions The method employs an mviscid flow model in which the wing the rolled-up vortex sheets and the wake are represented by piecewise continuous quadratic doublet sheet distributions The Kutta condition is imposed and satisfied along all wing edges Strengths of the doublet distribu- tions as well as shape and position of the vortex spirals are 20 N76-10062 computed in iterative fashion starting with an assumed initial sheet geometry The method is verified by numerous computed results and the extension to supersonic flow and more general configuration types is suggested Author N76-100*6* National Aeronautics and Space Administration Langley Research Center Langley Station Va AN INTEGRATED SYSTEM FOR THE AERODYNAMIC DESIGN AND ANALYSIS OF SUPERSONIC AIRCRAFT David S Miller and Wilbur D Middleton (Boeing Co) In its Aerodynamic Analyses Requiring Advanced Computers. Pt 2 1975 p 1049-1065 refs CSCL 01C An integrated system of computer programs is described The goals of the system were to develop an easily used supersonic design and analysis capability with recognition of the need for constraints on linear theory to provide physical realism and with inclusion of interactive graphics capability for increased control over the design and analysis iteration cycles Author N76-10O47* Boston Univ Mass INDICIAL COMPRESSIBLE POTENTIAL AERODYNAMICS AROUND COMPLEX AIRCRAFT CONFIGURATIONS Luigi Mormo and Lee-Tzong Chen In NASA Langley Res Center Aerodynamics Analyses Requiring Advanced Computers Pt 2 1975 p 1067-1110 refs (Grant NGR-22-004-030) CSCL 01C A general theory for indicia! potential compressible aerody- namics around complex configurations is presented The motion is assumed to consist of constant subsonic or supersonic speed for time t less than or equal to 0 (steady state) and of small perturbations around the steady state for time t greater than 0 Using the finite-element method to discretize the space problem a set of differential-delay equations was obtained in time relating the potential to its normal derivative on the surface of the body The aerodynamic transfer function was obtained by using standard methods of operational calculus The theory is embedded in a computer code SUSSA ACTS, which is briefly described Numerical results are presented for steady and unsteady subsonic and supersonic flows and indicate that the code is not only general flexible and simple to use but also accurate and fast Author N76-10050* National Aeronautics and Space Administration Langley Research Center Langley Station, Va NUMERICAL MODELING OF TUNNEL-WALL AND BODY SHAPE EFFECTS ON TRANSONIC FLOW OVER FINITE LIFTING WINGS Perry A Newman and E B Klunker In its Aerodynamics Analyses Requiring Advanced Computers Pt 2 1975 p 1189-1212 refs CSCL 20D Preliminary computational results were obtained for two problems relating to interference effects in transonic flow over finite lifting wings The first is concerned with the numerical modeling of the flow about a three-dimensional wing configura- tion within a wind tunnel and the second is concerned with calculating favorable interference effects produced by the body of a wing-body configuration For both problems the calculations were based upon a small disturbance potential equation which is solved using a relaxation technique A number of tunnel-wall boundary conditions are simulated and a comparison is made with experimental data Author N76-10052* National Aeronautics and Space Administration Langley Research Center Langley Station Va AXISYMMETRIC TRANSONIC FLOW INCLUDING WIND TUNNEL WALL EFFECTS Jerry C South Jr and James D Keller In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 1233-1367 refs CSCL 20D A method is presented for obtaining numerical solutions to the problem of transonic flow past axisymmetnc bodies in a wind tunnel Parabolic coordinates are sheared and stretched so that the flow region between the body and the tunnel wall is mapped onto a rectangular computational plane A finite-difference analog of the exact compressible potential equation is solved with a column iteration scheme which uses Jameson s rotated retarded differences in supersonic regions and central differences in subsonic regions The flow tangency condition at the surface is enforced by a dummy-point method and the wind-tunnel wall boundary condition is satisfied by a one-sided difference method Solutions were obtained for a supercritical body of revolution and compared with previous calculations by RAXBOD a program developed by South and Jameson for bodies in free air and with experiments The present results are not as accurate as the RAXBOD results for the same number of mesh points and convergence is slow on the fine mesh The method works well for two-dimensional symmetric airfoils Author N76-10O49* National Aeronautics and Space Administration Langley Research Center. Langley Station, Va COMPARISONS OF THEORETICAL AND EXPERIMENTAL PRESSURE DISTRIBUTIONS ON AN ARROW-WING CONFIGURATION AT TRANSONIC SPEED Marjone E Manro (Boeing Commercial Airplane Co) Edward N Tmoco (Boeing Commercial Airplane Co), Percy J Bobbin and John T Rogers (Boeing Commercial Airplane Co) In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 1141-1188 refs Sponsored in part by the Boeing Co (Contract NAS1-12875) CSCL 01A A wind-tunnel test of an arrow-wing-body configuration employing both a twisted and a flat wing, as well as a variety of leading- and trailmg-edge flap deflections was conducted to provide an experimental data base for comparison with theoreti- cal methods The purpose of these comparisons was to delineate conditions under which the theoretical predictions are valid for aeroelastic calculations and to explore the use of empirical methods to correct the theoretical methods where theory is deficient Test-theory comparisons of detailed pressure distribu- tions were made using current state-of-the-art linear and separated flow computer programs The results of attempting to make empirical corrections to the theoretical methods and of using two-dimensional separation criteria to predict flow separation are shown Author N76-10054* National Aeronautics and Space Administration Langley Research Center Langley Station Va APPROXIMATE METHOD FOR CALCULATING TRANSONIC FLOW ABOUT LIFTING WING BODY COMBINATIONS Richard W Barnwell In its Aerodynamic Analyses Requiring Advanced Computers Pt 2 1975 p 1281-1303 refs CSCL 01A A fast approximate method is described for calculating transonic flow about lifting configurations with swept leading edges and aspect ratios of order 1 at angles of attack of the order of the equivalent-body thickness-length ratio The method accounts for shock waves leading-edge separation and wind- tunnel wall effects and is applicable throughout the Mach number range from zero to low supersonic Author N76-10O62*# Aerophysics Research Corp, Bellevue Wash APPLICATION OF MULTIVARIABLE SEARCH TECHNIQUES TO THE OPTIMIZATION OF AIRFOILS IN A LOW SPEED NONLINEAR INVISCID FLOW FIELD Donald S Hague and Antony W Merz Jul 1975 74 p refs (Contract NAS2-8599) (NASA-CR-137760. TN-206) Avail NTIS HC $4 25 CSCL 01A Multivariable search techniques are applied to a particular 21 N76-10063 class of airfoil optimization problems These are the maximization of lift and the minimization of disturbance pressure magnitude in an inviscid nonlinear flow field A variety of multivanable search techniques contained m an existing nonlinear optimization code, AESOP are applied to this design problem These techniques include elementary single parameter perturbation methods organized search such as steepest-descent quadratic and Davidon methods randomized procedures and a generalized search acceleration technique Airfoil design variables are seven in number and define perturbations to the profile of established Multimode switch approaches and interface memory requirements are discussed Techniques are established for converting failure data into messages the pilot can immediately understand A word code technique is recommended as a means for simplifying the SOSTEL/AIMIS interface and minimizing interface memory requirements The A-7B power distribution and armament station control unit (ASCU) subsystems are used as the data base for the study GRA N76-10123*# Georgia Inst of Tech Atlanta COMBUSTION GENERATED NOISE IN GAS TURBINE COMBUSTORS W C Strahle and B N Shivashankara Aug 1974 41 p refs (Contract NAS3-17861) (NASA-CR-134843) Avail NTIS HC S3 75 CSCL21E Experiments were conducted to determine the noise power and spectra emitted from a gas turbine combustor can exhausting to the atmosphere Limited hot wire measurements were made of the cold flow turbulence level and spectra within the can The fuels used were JP-4 acetone and methyl alcohol burning with air at atmospheric pressure The experimental results show that for a fixed fuel the noise output is dominated by the airflow rate and not the fuel/air ratio The spectra are dominated by the spectra of the cold flow turbulence spectra which were invariant with airflow rate in the experiments The effect of fuel type on the noise power output was primarily through the heat of combustion and not the reactivity A theory of combustion noise based upon the flame radiating to open surroundings is able to reasonably explain the observed results A thermoacoustic efficiency for noise radiation as high as 00003 was observed in this program for JP-4 fuel Scaling rules are presented for installed configurations Author N76-10124*# Pratt and Whitney Aircraft East Hartford Conn EXPERIMENTAL CLEAN COMBUSTOR PROGRAM. PHASE 1 Final Report R Roberts A Peduzzi, and G E Vitti Oct 1975 214 p refs (Contract NAS3-16829) (NASA-CR-134736 PWA-5153) Avail NTIS HC $7 25 CSCL 12E A program of screening three low emission combustors for conventional takeoff and landing by testing and analyzing thirty-two configurations is presented Configurations were tested that met the emission goals at idle operating conditions for carbon monoxide and for unburned hydrocarbons (emission index values of 20 and 4 respectively) Configurations were also tested that met a smoke number goal of 15 at sea-level take-off conditions None of the configurations met the goal for oxides of nitrogen emissions at sea-level take-off conditions The best configurations demonstrated oxide of nitrogen emission levels that were approximately 61 percent lower than those produced by the JT9D-7 engine but these levels were still approximately 24 percent above the goal of an emission index level of 10 Additional combustor performance characteristics including lean blowout exit temperature pattern factor and radial profile pressure loss altitude stability and altitude relight characteristics were documented The results indicate the need for significant improvement in the altitude stability and relight characteristics In addition to the basic program for current aircraft engine combustors seventeen combustor configurations were evaluated for advanced supersonic technology applications The configura- tions were tested at cruise conditions and a conceptual design was evolved Author N76-10125*# General Electric Co Cincinnati Ohio DESIGN. FABRICATION AND ACOUSTIC TESTS OF A 36 INCH (0914 METER) STATORLESS TURBOTIP FAN Final Contract Report E G Smith D L Stempert and W R Uhl Washington NASA Sep 1975 184 p refs (Contract NAS2-5462) (NASA-CR-2597 R74AEG334) Avail NTIS HC 57 00 CSCL 21E The LF336/E is a 36 inch (0914 meter) diameter fan designed to operate in a rotor-alone configuration Design features required for modification of the existing LF336/A rotor-stator fan into the LF336/E statorless fan configuration are discussed Tests of the statorless fan identified an aerodynamic performance deficiency due to inaccurate accounting of the fan exit swirl during the aerodynamic design This performance deficiency related to fan exit static pressure levels produced about a 20 percent thrust loss A study was then conducted for further evaluation of the fan exit flow fields typical of statorless fan systems This study showed that through proper selection of fan design variables such as pressure ratio radius ratio and swirl distributions performance of a statorless fan configuration could be improved with levels of thrust approaching the conventional rotor-stator fan system Acoustic measurements were taken for the statorless fan system at both GE and NASA and when compared to other lift fan systems showed noise levels comparable to the quietest lift fan configuration which included rotor-stator spacing and acoustic treatment The statorless fan system was also used to determine effects of rotor leading edge serrations on noise generations A cascade test program identified the serration geometry based on minimum pressure losses wake turbulence levels and noise generations Author N76-10126*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio THRUST P E R F O R M A N C E OF ISOLATED 36-CHUTE S U P P R E S S O R PLUG NOZZLES WITH AND WITHOUT EJECTORS AT MACH NUMBERS FROM 0 TO 045 Douglas E Harrington James J Schloemer (GE Co Cincinnati) and Stanley A Skebe Washington Oct 1975 47 p refs (NASA-TM-X-3298, E-8334) Avail NTIS HC S3 75 CSCL 20A Plug nozzles with chute-type noise suppressors were tested with and without elector shrouds at free-stream Mach numbers from 0 to 0 45 and over a range of nozzle pressure ratios from 2 to 4 A 36-chute suppressor nozzle with an ejector had an efficiency of 94 6 percent at an assumed takeoff pressure ratio of 3 0 and a Mach number of 0 36 This represents only a 3 4 percent performance penalty when compared with the 98 percent efficiency obtained with a previously tested unsuppressed plug nozzle Author N76-10127*# Advanced Technology Labs Inc Westbury NY STUDY OF VARIABLE CYCLE ENGINES EQUIPPED WITH SUPERSONIC FANS Horacio Trucco Sep 1975 110 p refs (Contract NAS3-17559) (NASA-CR-134777 ATL-TR-201) Avail NTIS H C # 5 2 5 CSCL 21E Two types of variable cycle jet engines were investigated One called Variable Bypass Engine resembles a conventional bypass engine the second is called Bleed-Burn Engine and is characterized by remote supersonic fan units These engines are characterized by the utilization of a supersonic fan to energize their bypassed flow Performance calculations show that both engines exhibit substantial reduction in fuel consumption in comparison to contemporary variable cycle engines In addition these engines are smaller and of lighter installed weight Mission range for the case of a supersonic transport with 236 passenger cruising at Mach 2 70 were calculate) for these new engines The Variable Bypass Engine displays the best performance with relative reduction in takeoff gross weight of the order of 90720 kg (200000 Ib) for the basic 7408 km (4000 N Mi) mission when compared to a conventional Duct Heating Turbofan Engine For the case of the Bleed-Burn Engine the same mission can be achieved with about 45360 kg (100000 Ib) takeoff gross weight reduction These potentials warrant a more detailed anrj >• "*~ analysis of these engines which should assign first priority to the design and test of an applicable supersonic fan Author 27 N76-10128 N76-10128*# Pratt and Whitney Aircraft East Hartford Conn NOISE ADDENDUM EXPERIMENTAL CLEAN COMBUSTOR PROGRAM. PHASE 1 Final Report. Dec 1973 - Jul 1974 T G Sofnn and D A Ross Oct 1975 120 p refs (Contract NAS3-16829) (NASA-CR-134820 PWA-5252) Avail NTIS HC $5 25 CSCL, 21E The development of advanced CTOL aircraft engines with reduced exhaust emissions is discussed Combustor noise information provided during the basic emissions program and used to advantage in securing reduced levels of combustion noise is included Results are presented of internal pressure transducer measurements made during the scheduled emissions test program on ten configurations involving variations of three basic combustor designs Author N76-10129*# General Electric Co Cincinnati, Ohio Aircraft Engine Group DEMONSTRATION OF SHORT-HAUL A IRCRAFT AFT NOISE REDUCTION TECHNIQUES ON A TWENTY INCH (508 cm) DIAMETER FAN. VOLUME 1 An Early Domestic Dissemination Report D U Stimpert and R A McFalls Apr 1975 121 p refs 3 Vol (Proj FEDD. Contract NAS3-18021) (NASA-CR-134849 R75AEG252-Vol-1) Avail NASA Regional Dissemination Centers only to US Requesters HC S525/MF $225 CSCL 21 E Scale models were tested in an anechoic chamber The various techniques employed were source noise reduction features of selection of vane-blade ratio to reduce second harmonic noise spacing effects, and lowering the Mach number through a vane row Aft suppression features were investigated which included porosity effects, variable depth treatment, and treatment regenerated flow noise Photographs of test equipment and hardware are included Author N76-10130*# General Electric Co Cincinnati Ohio Aircraft Engine Group DEMONSTRATION OF SHORT-HAUL A I R C R A F T AFT NOISE REDUCTION TECHNIQUES ON A TWENTY INCH (508 cm) DIAMETER FAN. VOLUME 2 An Early Domestic Dissemination Report D L Stimpert Apr 1975 307 p 3 Vol (Proj FEDD Contract NAS3-18021) (NASA-CR-134850 R75AEG252-Vol-2) Avail NASA Regional Dissemination Centers only to US Requesters HC S925/MF $225 CSCL 21 E The 1/3 octave band sound data are plotted for various combinations of fan speeds acoustic angles and frequencies Author N76-10131*# General Electric Co, Cincinnati. Ohio Aircraft Engine Group DEMONSTRATION OF SHORT-HAUL AIRCRAFT AFT NOISE REDUCTION TECHNIQUES OF A TWENTY INCH (508 cm) DIAMETER FAN. VOLUME 3 An Early Domestic Dissemination Report D L Stimpert Apr 1975 725 p 3 Vol (Proj FEDD. Contract NAS3-18021) (NASA-CR-134851 R75AEG252-Vol-3) Avail NASA Regional Dissemination Centers only to US Requesters HC S1725/MF $225 CSCL21E The 1/3 octave band sound data are presented for all the configurations tested The model data are presented on 17 foot (52 cm) arc and extrapolated to 200 foot (6096 m) sideline Author N76-10133*# Pratt and Whitney Aircraft East Hartford Conn REDESIGNED ROTOR FOR A HIGHLY LOADED. 18OO FT/SEC TIP SPEED COMPRESSOR FAN STAGE 1 AERODYNAMIC AND MECHANICAL DESIGN J E Halle and J T Ruschak Sep 1975 68 p refs (Contract NAS3-18020) (NASA-CR-134835 PWA-5266) Avail NTIS HC$425 CSCL 21E A highly loaded high tip-speed fan rotor was designed with multiple-circular-arc airfoil sections as a replacement for a marginally successful rotor which had precompression airfoil sections The substitution of airfoil sections was the only aerodynamic change Structural design of the redesigned rotor blade was guided by successful experience with the original blade Calculated stress levels and stability parameters for the redesigned rotor are within limits demonstrated in tests of the original rotor Author N76-10135# Pratt and Whitney Aircraft East Hartford Conn BOUNDARY-INTEGRAL EQUATION METHOD FOR THREE- DIMENSIONAL ELASTIC FRACTURE MECHANICS ANALY- SIS Interim Scientific Report. 1 Apr 1974 - 31 Mar 1975 T A Cruse 28 May 1975 59 p refs (Contract F44620-74-C-0060 AF Pro) 9782) IAD-A011660 PWA-5272 AFOSR-75-0813TR) Avail NTIS CSCL 11/6 Analytical and numerical modeling improvements in the three-dimensional boundary-integral equation method have been developed for fracture mechanics problems in rotating gas turbine structures for aircraft Improved modeling procedures for accurate stress intensity factor analysis of surface and corner cracks were developed and verified In addition the basic analytical stress analysis tool was extended to include analysis of the steady-state thermo-elastic and centrifugal body force problems Results reported include newly developed analytical formulations for crack analysis and body force problems Extensive numerical results are reported which verify the improved analytical capabilities GRA N76-10137# Naval Weapons Engineering Support Activity Washington D C STATISTICAL CALCULATION AND ANALYSIS FOR THE LOGISTICS OF ENGINE REMOVAL (SCALER) METHODOL- OGY James P Matthesen Feb 1975 81 p refs (AD-A010824, NAVWESA-R-7502) Avail NTIS CSCL 01/3 SCALER was developed in 1973-74 for the Engine Life Management Group (ELMG) as the Navy s self-validating actuarial method of statistically projecting aircraft engine removals and rework requirements and of periodically providing management a usable analysis of removal data The method separates the effects due to administrative policy changes, statistical fluctuations changes in engine age populations and changes in engine reliability The report describes the method assumptions calculations and output reports GRA N76-10138 Missouri Univ Roll a DEVELOPMENT OF HELICOPTER FLIGHT PATH MODELS UTILIZING MODERN CONTROL TECH NIQUES PhD Thesis Alfred Fermelia 1975 134 p Avail Univ Microfilms Order No 75-22319 The nonlinear set of equations which represents helicopter motion are linearized about a prescribed nominal state Once the linearized system is obtained it is validated by comparing the output of the nonlinear system to that of its linearized counterpart Having obtained a linear model, linear system theory may then be applied in order to investigate the stability and control characteristics of the aircraft General techniques for simulating helicopter pilot response for inclusion in a flight path simulation program have been devised To provide the desired flight goal a nominal flight trajectory is obtained from an existing nonlinear model With this basis a deterministic pilot model which attempts to minimize flight deviations from the nominal can be developed for generating descriptions of the desired flight path Dissert Abstr N76-10139 Minnesota Univ Minneapolis IN-FLIGHT THRUST VECTOR CONTROL PhD Thesis Ludo Verhavert 1975 271 p Avail Univ Microfilms Order No 75-21100 28 N76-10907 The impact of in-flight thrust vectoring on the longitudinal stability of heavy subsonic jet transport aircraft was investigated The rigid body equations of motion for a thrust vectored aircraft are developed Longitudinal stability augmentation systems including thrust vector control are synthesized and an evaluation is made of the contribution of the thrust vector control component towards longitudinal stability augmentation and towards further relaxed static stability Dissert Abstr N76-10140*# Aerospace Systems Inc Burlington Mass A SPIRAL GUIDANCE APPROACH CONCEPT FOR COMMERCIAL VTOL OPERATIONS Final Report William C Hoffman and Walter M Holhster May 1975 128 p refs (Contract NASl-12199) (NASA-CR-132651 ASI-TR-75-21) Avail NTIS HCS5 75 CSCL 01C The results of an investigation of the guidance and naviga- tion requirements for VTOL spiral descents in the presence of winds are reported Models were developed to describe the spiral maneuver and candidate guidance laws were formulated and analyzed An important element of the guidance scheme is a unique wind estimator which uses the perturbations in bank angle and heading to improve the knowledge of the winds Finally recommendations for additional research including a flight program were outlined to evaluate the spiral guidance concept Author N76-10141# Naval Postgraduate School Monterey Calif A FLIGHT TEST DETERMINATION OF THE STATIC AND DYNAMIC LONGITUDINAL STABILITY OF THE CESSNA 310H AIRCRAFT MS Thesis William Harvey Siren Jun 1975 77 p refs (AD-A010795) Avail NTIS CSCL 01/3 An investigation was made of the static and dynamic longitudinal stability of a Cessna 31 OH aircraft Stick-fixed and stick-free neutral points were determined for both the cruise and approach configurations Stick-fixed and stick-free maneu- ver points were determined for the cruise configuration Values of the neutral points and maneuver points were also obtained from a theoretical analysis for comparison purposes The longitudinal long period or phugoid mode was investigated for the stick-fixed and stick-free cases and for widely separated center of gravity locations GRA N76-10144# Eidgenossisches Rugzeugwerk Emmen (Switzer- land) CALCULATION OF THE DISPLACEMENT CORRECTION (SOLID BLOCKING) TO RUMP AND WING FOR ARBITRARY RECTANGULAR WIND TUNNELS PART 1 THEORY M Schleicher 2 Jul 1974 30 p refs In GERMAN (Proj 103/230-56) (CH-6032-Emmen. FO-1230) Avail NTIS HC $3 75 Methods for calculating displacement corrections to rump and wings are discussed It is stipulated that angle of incidence and angle of sideslip are always at zero degree in a potential flow A special rotational ellipsoid approximation method is developed for rump calculations A numerical analysis for random trapezoidal wings is formulated that considers wing thickness ratios Transl by G G N76-10145# Eidgenossisches Flugzeugwerk Emmen (Switzer- land) CALCULATION OF THE DISPLACEMENT CORRECTION (SOLID BLOCKING) TO RUMP AND WING FOR ARBITRARY RECTANGULAR WIND TUNNELS PART 2 PROGRAM AND RESULTS M Schleicher 8 Jul 1974 59 p refs In GERMAN (Proj 103/230-56) (CH-6032-Emmen FO-1230) Avail NTIS HC $4 25 Presented are computer programs in FORTRAN 4 that were developed from the theoretical principles contained in Part 1 Also included are some numerical results as well as tables for the displacement corrections to rumps in correlation with volumes and thickness ratios Tables relate to the large subsonic tunnel (measuring section open or closed), the small subsonic tunnel (measuring section open) and the flutter tunnel (measuring section closed) Transl by G G N76-10157# Sanders and Thomas Inc. Pottstown Pa AIRCRAFT DESIGN REFERENCE DATA FOR EXPEDITION- ARY AIRFIELDS Final Report 27 Sep 1974 26 p refs Sponsored by the Navy (AD-A011447 NAEC-ENG-7856) Avail NTIS CSCL 01/5 A description of expeditionary airfields and associated components is presented to familiarize aircraft designers with the expeditionary aircraft concept An expeditionary airfield is a complete airfield that can be transported and assembled easily and have the capability to launch, recover and support certain high performance tactical jet aircraft The report provides necessary design parameters to insure that future aircraft have expeditionary airfield operating capability GRA N76-10530# Air Force Systems Command Wright-Patterson AFB Ohio Foreign Technology Div DETERMINATION OF THE FATIGUE LIFE OF STRUCTURAL ELEMENTS DURING THE BIHARMONIC PROCESS OF LOADING G G Zaveryukha 15 Jan 1975 53 p refs Transl into ENGLISH from Tsentr Aerogidrodmam Inst Uch Zap (USSR) v 4 no 2 1973 p 85-96 (AD-A007179 FTD-MT-24-0285-75) Avail NTIS CSCL 11/6 The experimental data are given on the fatigue life of structural elements made from alloys AK4-1T1 and VAD-23 during the biharmonic process of loading with different frequencies and amplitudes Calculations of fatigue life are presented GRA N76-10845$ School of Aerospace Medicine Brooks AFB, Tex THE TRANSMISSION. ABSORPTION COEFFICIENT, AND INDEX OF REFRACTION OF THE B 1 AND FB-3 WIND- SCREENS Interim Report. IS Jan - 15 Sep 1974 Edward F Maher and Robert E Wynn Feb 1975 49 p refs (AF Pro) 6301) (AD-A007040 SAM-TR-75-3) Avail NTIS CSCL 01/3 Spectral characteristics were measured on the B-1, and two types of FB-111 windscreens in the spectral region of 03 - 2 0 micrometers The total transmission index of refraction dispersion and Lambert absorption coefficients were determined to quantitate the effective protection offered by these windscreens to high-intensity radiation Total windscreen transmission measurements were performed spectrophotometrically with each sample in normal incidence and adjacent to the detection aperture allowing both the direct transmission and the forward scatter to be measured The index of refraction for each windscreen was measured using a laser spectrometer system The index of refraction at eight wavelengths in the visible spectrum was accurately determined with this system Finally a method is presented to calculate the light attenuation offered by the three windscreens to this region of spectral radiation at various angles of incidence GPA N76-10907$ Army Aviation Systems Command St Louis, Mo Systems Analysis Office AVSCOM'S SPARE PARTS BREAKOUT STUDY Mark E Barkeley and Alan R LeMay Jun 1975 94 p refs (AD-A011245.AMSAV-D-75-4, USAAVSCOM-TR-75-20) Avail NTIS CSCL 15/5 The report is delimited to the AVSCOM Spare Parts Breakout Program, with materiel considerations being restricted to those items which are on the demand stockage list (DSL), authorized stockage list (ASL) and select others The objectives of the study are the following Evaluate the current practices and procedures of the Spare Parts Breakout Program for areas of improvement, determine whether potential resource savings can be realized from the Spare Parts Breakout Program GRA 29 N76-10909 N76-109O9# Assistant Secretary of Defense (Program Analysis and Evaluation), Washington. D C ACCEPTANCE RATES AND TOOLING CAPACITY FOR SELECTED MILITARY AIRCRAFT Oct 1974 108 p (AD-A011501) Avail NTIS CSCL 01/3 This paper presents the detailed data for certain military aircraft used in a study of planned and actual production rates prepared by OASD (Program Analysis and Evaluation) for the Secretary of Defense The study objective was to determine the degree of optimism in Service planning and its impact on production of aircraft The conclusions are summarized under the following heads Initial buildup maximum production rate tooling capacity average production rates, and production span Eighteen Navy and Air Force aircraft programs were used as the basis for the analysis GRA N76-10910# Michigan Univ. Ann Arbor Dept of Industrial and Operations Engineering AIRCRAFT ENGINES DEMAND FORECASTING AND INVENTORY REDISTRIBUTION Final Report. 15 May 1973 - 15 Mar 1974 Herbert P Galliher and Richard C Wilson Feb 1975 152 p refs (Contract F33615-73-C-4158) (AD-A011595 ARL-75-0008) Avail NTIS CSCL 21/5 Using historical experience with J79 engines, an investigation was made of the quantitative relationships between engine age, utilization overhaul-rate failure-rate, and fleet age-distribution Based upon these considerations a new computerized method for forecasting demand for spare engines is proposed to replace present AFM 400-1 procedures A procedure for redistributing multi-indentured stocks of repairable components and assemblies from depot to base is proposed The procedure requires forecasts of removal rates, base-to-depot return rates. MOD-METRIC-hke stock-allocation levels repair and ship times as inputs Whenever a stock unit becomes available at the depot or is required at a base the procedure determines in real time a stock allocation which seeks to minimize long-run expected system backorders GRA N76-10979# European Space Agency, Pans (France) LA RECHERCHE AEROSPATIALE BIMONTHLY BULLETIN NO 1974-5 Jul 1975 171 p refs Transl into ENGLISH of La Rech Aerospatiale Bull Bimestnel (Pans) no 1974-5 Sep - Oct 1974 p 247-326 Original French report available from ONERA, Pans 20 F (ESA-TT-181) Avail NTIS HC $6 25 Topics covered are (1) numerical calculation of linearized subsonic flows around wings (2) procedure for calculating the transonic field of convergent ejectors having the shape of truncated cone bodies of revolution. (3) comparative study of two protection methods for super alloys i e the case of NiAI-type coatings on 1 N-100 alloys, (4) explicit form of the optimal piloting law for a rigid aircraft flying in a turbulent atmosphere (5) evaluation of the stress intensity factor by direct measurements on a loaded cracked structure and (6) influence of sloshing in wing tip tanks on the natural vibration modes of an aircraft N76-10980 European Space Agency Paris (France) THE NUMERICAL CALCULATION OF LINEARIZED SUB- SONIC FLOWS AROUND WINGS Henri Viviand and Walid Chazzi In its La Rech Aerospatiale Bimonthly Bull No 1974-5 (ESA-TT-181) Jul 1975 p 1-29 refs Transl into ENGLISH from La Rech Aerospatiale. Bull Bimestnel (Pans) no 1974-5 Sep - Oct 1974 p 247-260 A collocation method which was proposed for the solution of a lifting problem belongs to the general class of finite element methods and presents some advantages over Multhopp methods from the point of view of simplicity and generality Numerical examples are presented and compared with theoretical and experimental results Author (ESA) N76-10983 European Space Agency Paris (France) EXPLICIT FORM OF THE OPTIMAL PILOTING LAW OF A RIGID AIRCRAFT FLYING IN TURBULENCE Gabriel Coupry In its La Rech Aerospatiale Bimonthly Bull No 1974-5 (ESA-TT-181) Jul 1975 p 90-114 refs Transl into ENGLISH from La Rech Aerospatiale Bull Bimestnel (Pans) no 1974-5 Sep - Oct 1974 p 291-302 After havmy shown the differences in principle and in application range corresponding to flight control in tubulence by open loop and closed loop the former method was developed The piloting laws are presented in an explicit form as a function of flight velocity and of the aircraft dimensionless parameters, and the response attenuation is calculated Lastly and application of the method shows which gains may be obtained by using an open loop control for the flight in turbulence of a Mirage 3 aircraft Author (ESA) N76-10985 European Space Agency Pans (France) INFLUENCE OF SLOSHING IN WING TIP TANKS ON THE VIBRATION NATURAL MODES OF AN AIRCRAFT Roger Valid and Roger Ohayon In its La Rech Aerospatiale Bimonthly Bull No 1974-5 (ESA-TT-181) Jul 1975 p 151-165 refs Transl into ENGLISH from La Rech Aerospatiale Bull Bimestnel (Pans) no 1974-5 Sep - Oct 1974 p 319-325 A calculation method is presented that predicts fluid effects on flight stability This method is based either on the fluid finite-element method and the use of a selective criterion to introduce the actually perturbatmg sloshing modes or on the use of a step-by-step method in which only the perturbation acting on previously chosen modes is calculated Author (ESA) N76-10989 European Space Agency Paris (France) PYROTECHNIC BONKERS FOR THE INFLIGHT TESTING OF STRUCTURES Pierre Larue Maurice Millett and Gerard Piazzoli In its La Rech Aerospatiale Bimonthly Bull No 1974-3 (ESA-TT-183) Aug 1975 p 50-75 refs Transl into ENGLISH from La Rech Aerospatiale Bull Bimestnel (Paris) no 1974-3 May - Jun 1974 p 137-146 Following a brief review of the principle of the aeroelastic test method employed the geometrical and mass characteristics of three recently developed types of pyrotechnic pulse generators are cited together with their performances The three devices are, respectively a flat pulse generator with a thrust of 50 daN lasting 22 msec a pulse generator consisting of laminated elements with a thrust of 175 daN lasting 26 msec and a cylindrical shaped pulse generator with a thrust of 20 daN lasting 18 msec A program of acceptance tests for these pulse generators is described as well as some modifications of the generator design to produce generator types suitable for low frequency vibration tests Author (ESA) N76-10995*# National Aeronautics and Space Administration Ames Research Center Moffett Field Calif OPTIMAL CONTROL ALLEVIATION OF TILTING PROPRO- TOR GUST RESPONSE Wayne Johnson Aug 1975 27 p refs Prepared in cooperation with Army Air Mobility R and D Lab Moffett Field. Calif (NASA-TM-X-62494. A-6307) Avail NTIS HCS400 CSCL 018 Optimal control theory is applied to the design of a control system for alleviation of the gust response of tilting proprotor aircraft Using a proprotor and cantilever wing analytical model the uncontrolled and controlled gust response is examined over the entire operating range of the aircraft except for hover helicopter mode, conversion, and airplane mode flight Substantial improvements in the loads ride quality and aeroelastic stability are possible with a properly designed controller A single controller, nominally optimal only at the design point speed (160 knots here), operated efficiently over the entire speed range, with the possible exception of very low speed in helicopter mode Kalman-Bucy filters were used as compensation networks to provide state estimates from various measurements in the wing motion, rotor speed perturbation and tip-path-plane tilt Author 30 N76-11005 N76-10996*# National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif AN ECONOMIC STUDY OF AN ADVANCED TECHNOLOGY SUPERSONIC CRUISE VEHICLE Cynthia L Smith and Louis J Williams Oct 1975 34 p refs (NASA-TM-X-62499 A-6333) Avail NTIS HC $4 00 CSCL 01C A description is given of the methods used and the results of an economic study of an advanced technology supersonic cruise vehicle This vehicle was designed for a maximum range of 4000 n mi at a cruise speed of Mach 2 7 and carrying 292 passengers The economic study includes the estimation of aircraft unit cost, operating cost, and idealized cash flow and discounted cash flow return on investment In addition, it includes a sensitivity study on the effects of unit cost, manufacturing cost production quantity, average trip length, fuel cost, load factor, and fare on the aircraft's economic feasibility Author N76-10997*# Kansas Univ. Lawrence PROCEEDINGS OF THE NASA. INDUSTRY. UNIVERSITY, GENERAL AVIATION DRAG REDUCTION WORKSHOP Jan Roskam ed 1975 454 p refs Conf held at Kansas Univ. Lawrence. 14-16 Jul 1975 (Grant NsG-1175) (NASA-CR-145627) Avail NTIS HCS1200 CSCL 01A The conference on drag reduction research aims to improve general aviation aircraft performance N76-10998* National Aeronautics and Space Administration Ames Research Center, Moffett Field Calif GENERAL OVERVIEW OF DRAG S A Anderson In Kansas Univ Proc of the NASA. Ind Univ. Gen Aviation Drag Reduction Workshop 1975 p 11-37 refs CSCL 01A The state-of-the-art on aerodynamic drag reduction is briefly reviewed The various elements making up the total drag of an aircraft include fuselage wing, nacelles trim, interference tail and cooling drag G G N76-10999* North Carolina State Univ Raleigh PROSPECTS AND TIME TABLES FOR ANALYTICAL ESTIMATION OF THE DRAG OF COMPLETE AIRCRAFT CONFIGURATION Frederick O Smetana In Kansas Univ Proc of the NASA. Ind. Univ. Gen Aviation Drag Reduction Workshop 1975 p 39-41 refs CSCL 01A Analytical drag methods and wind tunnel evaluation of aircraft design features are used to identify excessive drag of general aviation aircraft with reciprocating engines G G N76-11000* National Aeronautics and Space Administration Langley Research Center. Langley Station Va SUMMARY OF DRAG CLEAN-UP TESTS IN NASA LANGLEY FULL-SCALE TUNNEL Marion 0 McKmney In Kansas Univ Proc of the NASA Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 43-60 refs CSCL 01A This summary of drag results presents tabulations on fighter aircraft and light twin general aviation aircraft wind tunnel tests The figures show that the friction drag for light twins is larger than that for the fighters because of the greater wetted area and the smaller wing area used for reference Full scale tunnel tests developed the following design features contributing to excessive drag cooling flow system, engine exhaust stacks landing gears, control surface gaps and wing irregularities and leakages G G N76-11001* National Aeronautics and Space Administration Langley Research Center, Langley Station, Va SIMPLIFIED THEORETICAL METHODS FOR AERODYNAM- IC DESIGN Jan R Tulmius In Kansas Univ Proc of the NASA. Ind. Univ Gen Aviation Drag Reduction Workshop 1975 p 61-76 refs CSCL 01C The objective of this paper is to describe theoretical proce- dures which can be utilized by the general aviation industry for aerodynamic design Discussed are the design process and theoretical methods used to design a wing Then theoretical methods for estimating the interference velocities due to fuselage or other bodies and nacelles are elaborated It is assumed that flow fields due to different components can be superimposed, and then the pressure coefficients computed from the Bernoulli equation Methods to estimate the induced, viscous form and compressible drags are also discussed In addition a procedure for modifying the surface contours to reduce adverse pressure distributions induced by component interference is detailed Author N76-11002* National Aeronautics and Space Administration Langley Research Center Langley Station Va DRAG REDUCTION BACK TO BASICS Oran W Nicks In Kansas Univ Proc of the NASA, Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 77-85 refs CSCL 01C Aeronautical design engineering for general aviation aircraft considers the iteration of wind tunnel test data are lift, weight drag and thrust as the basic balancing factor in drag reduction efforts G G N76-11003* Kansas Univ Lawrence SOME COMMENTS ON FUSELAGE DRAG Jan Roskam In its Proc of the NASA. Ind. Univ, Gen Aviation Drag Reduction Workshop 1975 p 87-102 refs CSCL 01A The following areas relating to fuselage drag are considered (1) fuselage fineness - ratio and why and how this can be selected during preliminary design (2) windshield drag (3) skin roughness and (4) research needs in the area of fuselage drag Author N76-11004* Beech Aircraft Corp Wichita. Kans PROPELLER BLOCKAGE RESEARCH NEEDS R R Tumlmson In Kansas Univ Proc of the NASA Ind Univ, Gen Aviation Drag Reduction Workshop 1975 p 103-105 refs CSCL 01C The effect of mutual propeller/nacelle of fuselage interference on aircraft propulsive efficiency is studied in order to determine accurate drag levels from flight test data by accurately estimating installed thrust and drag and the resulting aircraft performance GG N76-11005* Massachusetts Inst of Tech Cambridge PRESERVATION OF WING LEADING EDGE SUCTION AT THE PLANE OF SYMMETRY AS A FACTOR IN WING- FUSELAGE DESIGN E Eugene Larrabee In Kansas Univ Proc of the NASA Ind, Univ Gen Aviation Drag Reduction Workshop 1975 p 107-115 refs CSCL 01A Most fuselage geometries cover a portion of the wing leading edge near the plane of symmetry and it seems reasonable to expect that a large fraction of the leading edge suction which would be developed by the covered wing at high angles of attack is not developed on the fuselage This is one of the 31 N76-11006 reasons that the Oswald span efficiency factor for the wing body combination fails to approach the value predicted by lifting line theory for the isolated wing Some traditional and recent literature on wing-body interference is discussed and high Reynolds number data on wmg-body-nacelle drag are reviewed An exposed central leading edge geometry has been developed for a sailplane configuration Low Reynolds number tests have not validated the design concept Author A wake traversing probe was used to obtain section drag and wake profile data from the wing of a sailplane The transducer sensed total pressure defect in the wake as well as freestream total pressure on both sides of the sensing element when the probe moved beyond the wake Profiles of wake total pressure defects plotted as a function of distance above and below the trailing edge plane were averaged for calculating section drag coefficients for flights at low dynamic pressures G G N76-11006* Virginia Polytechnic Inst and State Univ Blacksburg ASYMPTOTIC ANALYTICAL METHODS IN FLUID MECHAN- ICS RELATED TO DRAG PREDICTION G R Inger In Kansas Univ Proc of the NASA. Ind. Univ Gen Aviation Drag Reduction Workshop 1975 p 117-124 refs CSCL 20D Some recent theoretical work of a purely analytical nature is described which promises to provide engineering predictions for the important drag-related phenomena of flow in the stall regime This analytical work deals with rigorous asymptotic studies of the complete Navier-Stokes equations that govern the viscous flow around any aerodynamic body under conditions where boundary layer separation takes place from the body surface Author N76-11007* Gates Learjet Corp. Denver. Colo THE ECONOMIC IMPACT OF DRAG IN GENERAL AVIA- TION Ron D Neal In Kansas Univ Proc of the NASA. Ind Univ. Gen Aviation Drag Reduction Workshop 1975 p 125-135 refs CSCL 01C General aviation aircraft fuel consumption and operating costs are closely linked to drag reduction methods Improvements in airplane drag are envisioned for new models their effects will be in the 5 to 10% range Major improvements in fuel consumption over existing turbofan airplanes will be the combined results of improved aerodynamics plus additional effects from advanced turbofan engine designs G G N76-11008* National Aeronautics and Space Administration Langley Research Center, Langley Station. Va SOME METHODS FOR REDUCING WING DRAG AND WING-NACELLE INTERFERENCE Thomas C Kelly In Kansas Univ Proc of the NASA Ind. Univ. Gen Aviation Drag Reduction Workshop 1975 p 137-156 refs CSCL 01C Primary efforts directed toward drag reduction centered on the design of both supercritical and subcntical families of airfoils the reduction of induced drag through the use of vortex diffusers. and the reduction of interference drag for executive-type aircraft Author N76-110O9* Kansas Univ Lawrence DRAG REDUCTION THROUGH HIGHER WING LOADING David L Kohlman In its Proc of the NASA Ind Univ. Gen Aviation Drag Reduction Workshop 1975 p 157-169 refs CSCL 01C A reduction in wing area, thickness and span increases wing loading and lowers parasitic drag for a typical light airplane by 105% GG N76-11010* National Aeronautics and Space Administration Flight Research Center Edwards Calif USE Of A PITOT PROBE FOR DETERMINING WING SECTION DRAG IN FLIGHT Edwin J Saltzman In Kansas Univ Proc of the NASA Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 171-189 ref CSCL 01D N76-11011* Beech Aircraft Corp. Wichita. Kans AN APPLICATION OF THE OGEE TIP Jerald M Vogel In Kansas Univ Proc of the NASA Ind. Univ Gen Aviation Drag Reduction Workshop 1975 p 191-202 refs CSCL 01C Wind tunnel tests show that the aerodynamic performance of a rectangular 3-D wing is increased by changing its tip to an ogee shape Potential gams in both cruise and climb performances for a modified Beech Baron aircraft indicate that incremental crnnges in performance are on the order of the data scatter associated with applied flight test techniques G G N76-11012* Wichita State Univ Kans WING-TIP VANES AS VORTEX ATTENUATION AND INDUCED DRAG REDUCTION DEVICES W H Wentz Jr and M G Nagati In Kansas Univ Proc of the NASA, Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 203-214 refs CSCL QIC Analytical studies have been conducted to examine the feasibility of utilizing wing tip turbines to remove swirl from the wing trailing vortex and hence reduce the potential for upset of fo lowing aircraft Energy recovery from the turbines is also analyzed A computer routine has been developed to permit rapid parametric studies of various tip turbine designs It is shown that the optimum turbine is a non-rotating set of vanes which reduce swirl and recover energy in the form of reduced overall configuration induced drag A specific case study indicates a 23% reduction in induced drag for a rectangular wing of aspect ratio 5 33 operated at a lift coefficient at 1 0 Author N76-11013* Kansas Univ Lawrence WING TIP VORTEX DRAG Vincent U Muirhead In its Proc of the NASA, Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 215-233 refs CSCL 01A Optimization of L/D through minimizing induced drag through a detailed flow study together with force, pressure and vorticity measurements is considered How visualization with neutral helium bubbles provides an excellent means of observing the effects of configuration changes Author N76-11014* Gates Learjet Corp, Denver Colo OVERVIEW OF EXTERNAL NACELLE DRAG AND INTER- FERENCE DRAG Ronald D Neal In Kansas Univ Proc of the NASA, Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 235-244 refs CSCL 01A A historical view of multi-jet engine installations is given that emphasizes integration of the powerplant and the airframe in aircraft design for improved reduction in external nacelle drag and interference drag characteristics G G N76-11015* AiResearch Mfg Co Phoenix. Ariz INSTALLATION DRAG CONSIDERATIONS AS RELATED TO TURBOPROP AND TURBOFAN ENGINES G A Burnett In Kansas Univ Proc of the NASA Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 245-256 CSCL 21E Some of the specific areas associated with straight jet and 32 N76-11024 turboprop engine installations are outlined where drag reduction and thus improved aircraft system performance is obtained Specific areas constitute air intake sizing for general aviation aircraft exhaust duct geometries and cooling system arrangements for propeller powered aircraft G G N76-11016* North Carolina State Univ Raleigh NACELLE DRAG REDUCTION AN ANALYTICALLY- GUIDED EXPERIMENTAL PROGRAM Frederick 0 Smetana In Kansas Univ Proc of the NASA Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 257-261 ref CSCL 01A Modifications are proposed to standard estimating procedures, as well as the BODY computer program which predict that the drag of two nacelles will equal the drag of the fuselage A preliminary computer analysis that considers increased dimensions for the nacelle forebody so that the noise is relatively less blunt indicates a reduction in form drag much greater than the increase in skin friction drag attributable to increased surface area G G N76-11017* Mississippi State Univ, State College AN EXPLORATORY INVESTIGATION OF THE COOLING DRAG ASSOCIATED WITH GENERAL AVIATION PROPUL- SIVE SYSTEMS E J Cross In Kansas Univ Proc of the NASA. Ind. Univ Gen Aviation Drag Reduction Workshop 1975 p 263-272 (Grant NsG-1083) CSCL 01A A systematic investigation of the drag associated with cooling air flow in contemporary general aviation engine installations is proposed Theoretical and experimental methods include a state-of-the-art survey, determination of cooling drag by flight tests, and establishment of relative magnitude and components of cooling drag G G N76-11018* Massachusetts Inst of Tech Cambridge PROPELLERS OF MINIMUM INDUCED LOSS, AND WATER TUNNEL TESTS OF SUCH A PROPELLER E E Larrabee In Kansas Univ Proc of the NASA, Ind Univ, Gen Aviation Drag Reduction Workshoo 1975 p 273-293 refs CSCL 01C The fundamental vortex theory for a single rotation propeller with a finite number of blades is reviewed The theory leads to the specification of a radial distribution of bound circulation on each blade for minimum induced loss analogous to the elliptic spanwise distribution of bound circulation on a wing for minimum induced drag A propeller designed in accord with this theory has been tested in a water tunnel where it exhibited high efficiency in spite of localized ca vita ting flow A knowledge of the flow field for an optimum propeller is of value to the airframe designer seeking to maximize the performance of the airplane-propeller combination Author N76-11019* Kansas Univ Lawrence SOME COMMENTS ON TRIM DRAG Jan Roskam In its Proc of the NASA. Ind . Univ , Gen Aviation Drag Reduction Workshop 1975 p 295-305 refs CSCL 01A A discussion of data of and methods for predicting trim drag is presented Specifically the following subjects are discussed (1) economic impact of trim drag (2) the trim drag problem in propeller driven airplanes and the effect of propeller and nacelle location. (3) theoretical procedures for predicting trim drag, and (4) research needs in the area of trim drag Author N76-11020* Virginia Polytechnic Inst and State Univ Blacksburg .REDUCTION OF TRIMMED DRAG F H Lutze. Jr In Kansas Univ Proc of the NASA Ind. Univ Gen Aviation Drag Reduction Workshop 1975 p 307-318 refs CSCL 01C Methods are reported for reducing the aircraft drag coefficient for a given aircraft lift coefficient or speed The emphasis is placed m determining the load distribution between the wing-body combination and the tail which reduces overall drag coefficient Furthermore a technique is presented which allows the determina- tion of various aerodynamic and geometric parameters to permit the best location to satisfy inherent stability requirements Included in the method is the calculation of sensitivity coefficients which indicate the importance of various parameters in achieving specified goals Preliminary results indicate that such an approach is feasible Author N76-11021* Massachusetts Inst of Tech Cambridge TRIM DRAG IN THE LIGHT OF MUNK'S STAGGER THEOREM E E Larrabee In Kansas Univ Proc of the NASA Ind , Univ Gen Aviation Drag Reduction Workshop 1975 p 319-329 refs CSCL 01A Munks stagger theorem holds that the induced drag of a multiplane is independent of the streamwise position (the stagger) of its lifting elements so long as the gap/span ratios and the element/element lift ratios are specified In particular, a monoplane-tailplane or a monoplane-foreplane (canard) arrangement can be regarded as a biplane of zero gap and the trim drag due to tailplane download or foreplane upload can be readily calculated The trim drag penalty is the same for both configurations Relations are given for trim drag estimates for various practical arrangements Author N76-11022* Beech Aircraft Corp. Wichita. Kans COST CONSIDERATION FOR AIRCRAFT CONFIGURATION CHANGES. 1 R R Tumlmson In Kansas Univ Proc of the NASA Ind, Univ. Gen Aviation Drag Reduction Workshop 1975 p 331-335 CSCL QIC The costs of improvements in aircraft drag reduction design changes are outlined in the context of production decisions A drag reduction design with increased airframe weight requires cost increases for direct labor overhead and direct expenses, plus general and administrative expenses G G N76-11023* Kansas Univ Lawrence DRAG OF THE COMPLETE CONFIGURATION AERODY- NAMIC CONSIDERATIONS. 2 Jan Roskam In its Proc of the NASA. Ind, Univ, Gen Aviation Drag Reduction Workshop 1975 p 337-351 refs CSCL 01A A number of drag items are related to the performance of a complete aircraft configuration First the effect of fuselage camber wing and nacelle incidence are discussed from a viewpoint of design decision making Second the effect of overall cruise drag on the design gross and empty weight of the airplane is discussed Examples show that cruise drag can have a very important influence on total airplane weight Third the effects of usable cruise lift-to-drag ratio and wing loading are shown to be important Finally several research needs relating to design of the complete configuration are reviewed Author N76-11024* Gates Learjet Corp Denver. Colo LEARJET MODEL 25 DRAG ANALYSIS Richard Ross and Ronald D Neal In Kansas Univ Proc of the NASA. Ind Univ Gen Aviation Drag Reduction Workshop 1975 p 353-363 CSCL QIC Procedures and data for estimating drag were used to calculate the drag characteristics of the Model 25 airplane Based on cruise flight test data obtained on the Model 25. these methods generally predicted the total drag characteristics within current acceptable and reasonable engineering accuracy Author 33 N76-11025 N76-11025* National Aeronautics and Space Administration Langley Research Center, Langley Station, Va PROBLEMS IN PROPULSION SYSTEM INTEGRATION W Henderson and J Runckel In Kansas Univ Proc of the NASA, Ind , Umv Gen Aviation Drag Reduction Workshop 1975 p 365-385 refs CSCL 21E Jet engine components are considered that influence propulsion system integration on the airframe and related aircraft drag areas Emphasis is placed on high Mach number inlet geometries, boattailed nozzle configurations propulsive wing installation wing surface blowing lift fuselage mounted nacelles, and thrust reversal G G N76-11026* National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio PROPULSION AIRFRAME INTEGRATION D Mikkelson In Kansas Umv Proc of the NASA Ind, Umv Gen Aviation Drag Reduction Workshop 1975 p 387-402 CSCL QIC Wind tunnel simulation tests are reported that utilize a 20 inch powered nacelle for airframe integration studies Considered are effects of boat tail positioning, nacelle size aft fuselage drag over-the-wing half span model installation, and turboprop and ducted fan configurations G G N76-11027* Mississippi State Univ State College DETERMINATION OF THE LEVEL FLIGHT PERFORMANCE OF PROPELLER-DRIVEN AIRCRAFT E J Cross In Kansas Univ Proc of the NASA Ind, Umv. Gen Aviation Drag Reduction Workshop 1975 p 403-407 refs CSCLQIC A flight test method to determine the level flight performance of propeller driven aircraft is reported that measures the amount of power it takes to overcome a known increment of added drag to maintain steady state flight conditions to determine overall drag and propeller efficiency of a general aviation aircraft Author N76-11028* Purdue Umv. Lafayette, Ind POSSIBLE APPLICATIONS OF SOARING TECHNOLOGY TO DRAG REDUCTION IN POWERED GENERAL AVIATION AIRCRAFT John H McMasters and George M Palmer In Kansas Umv Proc of the NASA, Ind , Umv, Gen Aviation Drag Reduction Workshop 1975 p 409-430 refs CSCL 01C A brief examination of the performance figures achieved by modern soaring machines and a little reflection on the often huge disparity in L/D values between sailplanes and GA aircraft indicates that careful attention to lessons learned in sailplane design and manufacture hold realistic promise for substantial gams in the aerodynamic efficiency of several GA types Author N76-11029* Massachusetts Inst of Tech Cambridge MINIMUM VERTICAL TAIL DRAG E E Larrabee In Kansas Umv Proc of the NASA Ind Univ. Gen Aviation Drag Reduction Workshop 1975 p 43-446 CSCL 01A Tail size requirement calculations are presented for a vertical tail performing a coordinated turn reversal at corresponding load requirements with minimum tail drag G G N76-11030*+ National Aeronautics and Space Administration Ames Research Center. M off en Field Calif FLOW VISUALIZATION OF VORTEX INTERACTIONS IN MULTIPLE VORTEX WAKES BEHIND AIRCRAFT D L Offone and C Lonzo, Jr Jun 1975 60 p refs Original contains color illustrations (NASA-TM-X-62459, A-6193) Avail NTIS HC $4 50 CSCL 01A A flow visualization technique was developed which allows the nature of lift-generated wakes behind aircraft models to be investigated The technique was applied to models being towed underwater in a ship model basin Seven different configura- tions of a small-scale model of a 747 transport aircraft were used to allow observation of typical vortex interactions and merging in multiple vortex wakes It was established that the motion of the wake vortices is often sensitive to small changes in either wing span loading or model attitude Landing gear deployement was found to cause a far-field reformation of vorticity behind a model configuration which dissipated concentrated vorticity in the near-field wake Alleviation of wake vorticity is achievable by configuring the wing span loading to cause the wake vortices to move in paths that result in their interactions and merging The vortices shed from the horizontal stabilizer always moved down rapidly into the wake and merged with the other vortices pnmanly the inboard flap vortices Author N76-11031*# Transemantics Inc Washington, D C CERTAIN PROBLEMS OF EXPERIMENTAL AERODYNAM- ICS S M Gorlm ed Washington NASA Nov 1975 122 p refs Transl into ENGLISH from the book Nekotoryye voprosy ekspenmental noy aerodmamiki, nauchnyye trudy institute mekhaniki MGU, no 24' Moscow, Moscow University Press 1973 p 1-119 (Contract NASw-2792) (NASA-TT-F-16565) Avail NTIS HC $5 50 CSCL 01A Experimental results of a study of the aerodynamic characteris- tics at low subsonic velocities of poorly streamlined bodies having different shapes and of the flow past irregularities on the earth's surface are presented The stress and the forces acting on structures are considered as well as the influence of the shape of certain bodies on the change in flow parameters in their vicinity Author N76-11032*# National Aeronautics and Space Administration Langley Research Center Langley Station. Va THEORETICAL PERFORMANCE OF CROSS-WIND AXIS TURBINES WITH RESULTS FOR A CATENARY VERTICAL AXIS CONFIGURATION Ralph J Muraca Maria V Stephens, and J Ray Dagenhart Oct 1975 85 p refs (NASA-TM-X-72662) Avail NTIS HCS500 CSCL 01A A general analysis capable of predicting performance characteristics of cross-wind axis turbines was developed, including the effects of airfoil geometry support struts, blade aspect ratio windmill solidity, blade interference and curved flow The results were compared with available wind tunnel results for a catenary blade shape A theoretical performance curve for an aerodynamically efficient straight blade configuration was also presented In addition a linearized analytical solution applicable for straight configurations was developed A listing of the computer program developed for numerical solutions of the general performance equations is included in the appendix Author N76-11033*| National Aeronautics and Space Administration Langley Research Center Langley Station Va DEVELOPMENT OF A COMPUTER PROGRAM TO OBTAIN ORDINATES FOR NACA 4-DIGIT, 4-DIGIT MODIFIED. 5 DIGIT. AND 16 SERIES AIRFOILS Charles L Ladson Nov 1975 45 p refs (NASA-TM-X-3284. L-10375) Avail NTIS HCS400 CSCL 01A A computer program developed to calculate the ordmates and surface slopes of any thickness, symmetrical or cambered NACA airfoil of the 4-digit 4-digit modified 5-digit. and 16-series airfoil families is presented The program produces plots of the airfoil nondimensional ordmates and a punch card output of ordmates in the input format of a readily available program for determining the pressure distributions of arbitrary airfoils in subsonic potential viscous flow Author 34 N76-11041 N76-11034*# Boeing Commercial Airplane Co. Seattle Wash TRANSONIC PRESSURE MEASUREMENTS AND COMPAR- ISON OF THEORY TO EXPERIMENT FOR AN ARROW-WING CONFIGURATION VOLUME 1: EXPERIMENTAL DATA REPORT. BASE CONFIGURATION AND EFFECTS OF WING TWIST AND LEADING-EDGE CONFIGURATION Marjone E Manro. Kenneth J R Manning. Thomas H Hallstaff. and John T Rogers Oct 1975 640 p refs (Contract NAS1-12875) (NASA-CR-132727. D6-42670-2-Vol-1) Avail NTIS HCS1625 CSCL01A A wind tunnel test of an arrow-wing-body configuration consisting of flat and twisted wings, as well as a variety of leading- and trailing-edge control surface deflections, was conducted at Mach numbers from 04 to 11 to provide an experimental pressure data base for comparison with theoretical methods Theory-to-expenment comparisons of detailed pressure distributions were made using current state-of-the-art attached and separated flow methods The purpose of these comparisons was to delineate conditions under which these theories are valid for both flat and twisted wings and to explore the use of empirical methods to correct the theoretical methods where theory is deficient Author N76-11035*/-/ Boeing Commercial Airplane Co Seattle Wash TRANSONIC PRESSURE MEASUREMENTS AND COMPAR- ISON OF THEORY TO EXPERIMENT FOR AN ARROW-WING CONFIGURATION VOLUME 2 EXPERIMENTAL DATA REPORT. EFFECTS OF CONTROL SURFACE DEFLECTION Marjone E Manro Kenneth J R Manning. Thomas H Hallstaff, and John T Rogers Oct 1975 614 p refs (Contract NAS1-12875) (NASA-CR-132728 D6-42670-3-Vol-2) Avail NTIS HC $1625 CSCL 01A For abstract see N76-11034 N76-11036*# Boeing Commercial Airplane Co, Seattle. Wash TRANSONIC PRESSURE MEASUREMENTS AND COMPAR- ISON OF THEORY TO EXPERIMENT FOR AN ARROW-WING CONFIGURATION VOLUME 3 DATA REPORT. COMPAR- ISON OF ATTACHED FLOW THEORIES TO EXPERIMENT Marjone E Manro, Kenneth J R Manning, Thomas H Hallstaff and John T Rogers Oct 1975 526 p refs (Contract NAS1-12875) (NASA-CR-132729 D6-42670-4-Vol-3) Avail NTIS HC $1300 CSCL 01A For abstract see N76-11034 N76-11037*# Wichita Univ Kans Aeronautical Engineering Dept EXPERIMENTAL STUDIES OF FLOW SEPARATION AND STALLING ON TWO-DIMENSIONAL AIRFOILS AT LOW SPEEDS PHASE 2 STUDIES WITH FOWLER FLAP EXTENDED Semiannual Progress Report. 1 Jun - 30 Nov 1975 H C Seetharam and W H Wentz. Jr 30 Nov 1975 20 p refs (Grant NGR-17-003-021) (NASA-CR-145741) Avail NTIS HC $3 50 CSCL 01A Results were given on experimental studies of flow separation and stalling on a two-dimensional GA(W)-1 17 percent thick airfoil with an extended Fowler flap Experimental velocity profiles obtained from a five tube probe survey with optimum flap gap and overlap setting (flap at 40 deg) are shown at various stations above below and behind the airfoil/flap combination for various angles of attack The typical zones of steady flow intermittent turbulence, and large scale turbulence were obtained from a hot wire anemometer survey and are depicted graphically for an angle of attack of 12 5 deg Local skin friction distributions were obtained and are given for various angles of attack Computer plots of the boundary layer profiles are shown for the case of the flap at 40 deg Static pressure contours are also given A GA(W)-2 section model was fabricated with 30 percent Fowler flaps and with pressure tabs YJA N76-11038*# National Aeronautics and Space Administration Langley Research Center Langley Station, Va AN INVESTIGATION OF THE INCREASE IN VORTEX INDUCED ROLLING MOMENT ASSOCIATED WITH LANDING GEAR WAKE James C Patterson and Frank L Jordan Jr Nov 1975 18 p refs (NASA-TM-X-72786) Avail NTIS HC $3 50 CSCL 01A Flight tests were conducted to verify the results found in ground base facilities of the effect of span lift load variation as well as the vortex attentuation of the high energy jet engine exhaust through proper thrust programming During these flight tests a large increase in vortex strength was experienced as a result of extending the landing gear Tests in the Langley Vortex Research Facility indicate that the wake produced by the landing gear may possibly form an aerodynamic endplate or reflection plane at the inboard edge of each inboard flap which increases the effective aspect ratio of the flap and thereby increases the strength of the flap outer edge vortex Author N76-11039*# National Aeronautics and Space Administration Ames Research Center Moffett Field, Calif A TECHNIQUE FOR ACCELERATING ITERATIVE CONVER- GENCE IN NUMERICAL INTEGRATION. WITH APPLICA- TION IN TRANSONIC AERODYNAMICS E Dale Martin Oct 1975 19 p refs (NASA-TM-X-62495) Avail NTIS HC $3 50 CSCL 01A A technique is described for the efficient numerical solution of nonlinear partial differential equations by rapid iteration In particular a special approach is described for applying the Aitken acceleration formula (a simple Fade approximant) for accelerating the iterative convergence The method finds the most appropri- ate successive approximations which are in a most nearly geometric sequence for use in the Aitken formula Simple examples are given to illustrate the use of the method The method is then applied to the mixed elliptic-hyperbolic problem of steady mviscid transonic flow over an airfoil in a subsonic free stream Author N76-11O40*# Virginia Univ. Charlottesville School of Engineering and Applied Science NASA/FRC WAKE TURBULENCE FLIGHT TEST PROGRAM RIDE QUALITY ASPECTS David A Deptula Nov 1975 36 p refs (Grant NGR-47-005-181) (NASA-CR-145700. Memo-403225, ESS-4032-104-75) Avail NTIS HC$400 CSCL 01A To determine how much the ride quality of the Shuttle Carrier (Boeing 747) Aircraft is affected at various spoiler settings, the PEMS II (Portable Environmental Measuring System) was used to measure onboard motion during a test flight October 15 1975 The PEMS II measures acceleration in the vertical, transverse and longitudinal directions as well as angular rates of pitch, roll and yaw The data acquired by this instrument combined with an airline passenger comfort model gives an indication of how passengers would react to the motion induced by flying in a vortex alleviation configuration Author N76-11041*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THEORETICAL AERODYNAMICS OF UPPER-SURFACE- BLOWING JET-WING INTERACTION C Edward Lan and James F Campbell Washington Nov 1975 50 p refs (NASA-TN-D-7936 L-10037) Avail NTIS HC $400 CSCL 01A A linear mviscid subsonic compressible flow theory is formulated to treat the aerodynamic interaction between the wing and an mviscid upper-surface-blowing (USB) thick |et with Mach number nonuniformity The predicted results show reasonably good agreement with some available lift and induced-drag data It was also shown that the thin-|et-flap theory is inadequate for the USB configurations with thick let Additional theoretical results show that the lift and mduced drag were reduced by increasing jet temperature and increased by increasing jet Mach number 35 N76-11042 Reducing jet aspect ratio while holding jet area constant caused reductions in lift induced drag and pitching moment at a given angle of attack but with a minimal change in the curve of lift coefficient against induced-drag coefficient The jet-deflection effect was shown to be beneficial to cruise performance The aerodynamic center was shifted forward by adding power or jet-deflection angle Moving the jet away from the wing surface resulted in rapid changes in lift and induced drag Reducing the wing span of a rectangular wing by half decreased the jet- circulation lift by only 24 percent at a thrust coefficient of 2 Author N76-11042*$ National Aeronautics and Space Administration Langley Research Center, Langley Station. Va FREE-FLIGHT MODEL INVESTIGATION OF A VERTICAL- ATTITUDE VTOL FIGHTER WITH TWIN VERTICAL TAILS Sue B Grafton and Ernie L Anghn Washington Nov 1975 29 p refs (NASA-TN-D-8089 L-10450) Avail NTIS HCS400 Free-flight tests were conducted in the Langley full-scale tunnel to determine the stability and control characteristics of a vertical-attitude VTOL fighter having twin vertical tails and a pivoted fuselage forebody (nose-cockpit) arrangement The flight tests included hovering flights and transition flights from hover to conventional forward flight Static force tests were also made to aid in the analysis of the flight tests The model exhibited satisfactory stability and control characteristics, and the transition from hovering flight to conventional forward flight was relatively smooth and straightforward Author An mtegro-differential method was used for numerically solving unsteady incompressible viscous flow problems A computer program was prepared to solve the problem of an impulsively started 9% thick symmetric Joukowski airfoil at an angle of attack of 15 deg and a Reynolds number of 1000 Some of the results obtained for this problem were discussed and compared with related work completed previously Two numerical procedures were used an Alternating Direction Implicit (ADD method and a Successive Line Relaxation (SLR) method Generally, the ADI solution agrees well with the SLR solution and with previous results are stations away from the trailing edge At the trailing edge station, the ADI solution differs substantially from previous results, while the vorticity profiles obtained from the SLR method there are in good qualitative agreement with previous results Y J A N76-11O48/J/ European Space Agency, Pans (France) AERODYNAMICS OF AIRFOILS IN TRANSONIC FLOW Jul 1975 299 p refs Transl into ENGLISH of Tragfluegel- Aerodynamik bei schallnahen Stroemungen" DGLR, Cologne Report DLR-Mitt-73-04. 1973 299 p Proc of DGLR Symp, Goettmgen. West Ger, 26-27 Oct 1972 Original German report available from DFVLR, Porz West Ger 44 60 DM (ESA-TT-175 DLR-Mitt-73-04) Avail NTIS HC $9 25 Results of investigations into transonic flows around airfoils are presented along with experimental and theoretical investiga- tions of sweptback wings New methods of calculating shock-free flow around airfoil sections in the transonic range, and a new wind tunnel test section for transonic profiles are discussed N76-11043*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va INTRODUCTION TO THE AERODYNAMICS OF FLIGHT Theodore A Talay Washington 1975 203 p refs (NASA-SP-367) Avail NTIS HC $7 75 CSCL 01A General concepts of the aerodynamics of flight are discussed Topics considered include the atmosphere fluid flow, subsonic flow effects, transonic flow supersonic flow, aircraft performance, and stability and control J M S N76-11044*| National Aeronautics and Space Administration Langley Research Center, Langley Station Va LOW SPEED AERODYNAMIC CHARACTERISTICS OF A TRANSPORT MODEL HAVING 4233 DEG SWEPT LOW WING WITH SUPERCRITICAL AIRFOIL. DOUBLE-SLOTTED FLAPS. AND T-TAIL OR LOW TAIL Paul G Fournier Washington Nov 1975 94 p refs (NASA-TM-X-3276 L-9957) Avail NTIS HC $500 CSCL 01A A low-speed investigation was conducted in the Langley V/STOL tunnel over an angle-of-attack range of approximately 4 deg to 24 deg to determine the static longitudinal stability characteristics and high lift performance of a general research model which represented an advanced subsonic transport configuration The model had a 42 33 deg swept aspect ratio 705 wing with a supercritical airfoil and high lift system consisting of a leading edge device (slat or Kruger flap) and a double-slotted flap The flaps were deflected for take off and landing configurations and were not deflected for tests of the clean configuration The model was tested with the horizontal tail in either a T tail or low tail position The effects of various arrangements of flowthrough nacelles which represent a three engine configuration (two large wing-mounted nacelles and a vertical tail mounted nacelle) and a four engine configuration (four smaller wing-mounted nacelles) were determined Author N76-11046*# Georgia Inst of Tech Atlanta STUDY OF VISCOUS FLOW ABOUT AIRFOILS BY THE INTEGRO DIFFERENTIAL METHOD Final Report James C Wu and Sarangan Sampath Oct 1975 61 p refs (Grant NsG-1004) (NASA-CR-145693) Avail NTIS HCS450 CSCL 01A N76-11049 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt Goettmgen (West Germany) Inst fuer Stroemungsmechanik COMPARATIVE MEASUREMENTS ON THREE GEOMETRI- CALLY SIMILAR CALIBRATION MODELS OF A TRANSPORT AIRCRAFT TYPE IN THE TRANSONIC WIND-TUNNEL AT THE AVA. GOETTINGEN W Lorenz-Meyer In ESA Aerodynamics of Airfoils m Transonic Flow (ESA-TT-175) Jul 1975 p 1-27 refs Transl into ENGLISH from "Tragfluegel-Aerodynamik bei schallnahen Stroemungen" DGLR. Cologne Report DLR-Mitt-73-04, 1973 p 1-31 (DGLR-Paper-72-122) Results are presented of 3-component measurements in the transonic wind tunnel at AVA in the Mach-number range Ma = 0 7 to 0 96 on three geometrically similar calibration models of a transport aircraft type (an ONERA project) A detailed description of the experimental conditions is given and the effects of the Reynolds number and of the accuracy of modelling were investigated Further, for particular conditions (Mach number and Reynolds number) the results obtained are compared with those measured in the wind tunnels S2MA (Modane-Avneux) and Sigma 4 (St Cyr) Author (ESA) N76-11050 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt Brunswick (West Germany) Inst fuer Aerodynamik THE CALCULATION OF THE BUFFET BOUNDARY FOR SWEPTBACK WINGS G Redeker In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 28-81 refs Transl into ENGLISH from ' Tragfluegel-Aerodynamik bei schallnahen Stroemungen ' DGLR. Cologne Report DLR-Mitt-73-04 1973 p 32-90 (DGLR-Paper-72-123) A computational method for determining the buffet boundary of a sweptback wing in the transonic range of velocities is described Thomas's method for determining the buffet boundary for wings without sweepback or only slightly sweptback is extended to wings with marked sweepback This is done by considering an infinitely long sheared wing using the Sinnott method for calculating the transonic pressure distributions and an integral method for calculating the 3-dimensional turbulent 36 N76 11057 compressible boundary-layer Theoretical calculations of the buffet boundary by these methods agree well with the experimental results for sweptback wings Author (ESA) N76-11051 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raunrvfahrt. Porz (West Germany) Inst fuer Angewandte Gasdynamik THEORETICAL INVESTIGATION OF TRANSITION PHENOMENA IN THE BOUNDARY LAYER ON AN INFINITE SWEPTBACK WING E H Hirschel In ESA Aerodynamics of Airfoils in Transonic Row (ESA-TT-175) Jul 1975 p 82-101 refs Trsnsl into ENGLISH from Tragfluegel-Aerodynamik bei schallnahen Stroemungen" DGLR. Cologne Report DLR-Mitt-73-04 1973 P91-112 (DGLR-Paper-72-124) The transition in compressible three-dimensional boundary layers on infinite sweptback wings was investigated by applying stability criteria and transition criteria to numerically calculated boundary layer flows The inviscid flow fields were found experimentally and represent transonic flows about airfoils with embedded supersonic regions The different criteria and their application to the boundary-layer flows are discussed The study was made under variation of the two main parameters angle of sweepback and free-stream Reynolds number Author (ESA) N76-11052 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt Goettmgen (West Germany) Inst fuer Stroemungsmechanik ON THE EFFECT OF A STRAKE ON THE FLOW FIELD OF A DELTA WING (LAMDA EQUALS 2) AT NEAR-SONIC VELOCITIES W Stahl In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 102-122 refs Transl into ENGLISH from ' Tragfluegel-Aerodynamik bei schallnahen Stroemungen" DGLR, Cologne Report DLR-Mitt-73-04 1973 p 113-136 (DGLR-Paper-72-125) Experimental investigations were earned out on a delta wing with an aspect ratio lambda = 2 and on a double delta wing derived from it The flow field on the suction side of the basic delta wing with a sharp leading edge is strongly affected by the leading-edge vortices A forewmg (strake) with large sweepback and sharp edges, attached to the main wing affects by its leading-edge vortices the flow field over the mam wing The resulting changes in the forces, in the pressure distributions on the suction side, and in the flow field were examined at subsonic, and especially at near-sonic, velocities (Ma = 0 5 to 0 9) The vortex-breadown phenomena occurring at high angles of incidence were investigated for the wing with and without the strake Author (ESA) N76-11053 Messerschmitt-Boelkow-Blohm G m b H , Ottobrunn (West Germany) IMPROVEMENT OF MANEUVERABILITY AT HIGH SUBSONIC SPEEDS W Staudacher In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 123-139 refs Transl into ENGLISH from 'Tragfluegel-Aerodynamik bei schallnahen Stroemungen . DGLR, Cologne Report DLR-Mitt-73-04. 1973 p 137-158 (DGLR-Paper-72-126) A number of studies were carried out to improve the maneuverability of combat aircraft As a geometrically variable configuration, slotted and unslotted flaps were fitted to the leading edge and trailing edge of a pilot model, which was tested in the wind-tunnel up to transonic speeds As geometrically fixed variants of the plan shape, strakes i e modifications of the leading edge which have a large angle of sweepback were attached to the trapezoidally shaped basic wing near the wing root, and were investigated over the whole range of Mach numbers (6-component measurements were taken) By combining various aids to maneuverability, an improvement of 100% in performance in certain flight regions could be obtained as compared with the basic wing Strakes were considerably more efficient than flap systems at high angles of attack Author (ESA) N76-110S4 Technische Hochschule Darmstadt (West Germany) Inst fuer Flugtechnik SIDE-SLIPPING AIRFOILS IN TRANSONIC FLOW B Wagner In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 140-165 refs Transl m«o ENGLISH from Tragfluegel-Aerodynamik bei schallnahen Stroemungen DGLR Cologne Report DLR-Mitt-73-04, 1973 p 159-192 (DGLR-Paper-72-127) A method was developed which takes into account the vortex sheet leaving the lateral edge of a side-slipping wing The theory of singular integral equations was used to derive an integral equation for the vorticity of the wing wake This integral equation is similar to the familiar integral equations for sweptback wings in a symmetrical transonic flow The method of solution developed can be applied to airfoils with arbitrary camber and twist The singularities in the vortex distribution at the wing apex and at the start of the wake are discussed Author (ESA) N76-11055 Dornier-Werke G m b H Fnednchshafen (West Germany) THE CALCULATION OF SUPERCRITICAL FLOWS ROUND AIRFOILS BY THE MURMAN-KRUPP DIFFERENCE METHOD R Vanino In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 166-187 refs Transl into ENGLISH from "Tragfluegel-Aerodynamik bei schallnahen Stroemungen DGLR, Cologne Report DLR-Mitt-73-04 1973 p 193-223 (DGLR-Paper-72-128) The results from the Krupp relaxation method show that this method is a useful tool in the practical design of airfoils Using a simple scheme of calculation, feasible solutions can be obtained within acceptable times by starting from the undisturbed flow Examples illustrate the wide applicability of the method which gives good results for thick airfoils with strong suction peaks, at high angles of attack Author (ESA) N76-11056 Deutsche Versuchsanstalt fuer Luft- und Raumfahrt, Aachen (West Germany) Inst fuer Theoretische Gasdynamik AN ANALOGUE-ANALYTICAL CONSTRUCTION FOR SUPERCRITICAL FLOWS ROUND AN AIRFOIL H Sobieczky et al In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 188-197 refs Transl into ENGLISH from Tragfluegel-Aerodynamik bei schallnahen Stroemungen' DGLR, Cologne Report DLR-Mitt-73-04 1973 p 224-240 (DGLR-Paper-72-129) A method is presented for solving a mixed elliptic-hyperbolic differential equation in the particular boundary-value problem of supercritical flow round an airfoil As an analog of a plane inviscid fluid flow, an electric potential flow is used From these measurements the subsonic region of the flow round the airfoil and a starting point are determined for an analytical calculation of the flow in the supersonic region With this method both shock-free flows and flows with weak shocks can be determined ' Author (ESA) N76-11067 Messerschmitt-Boelkow-Blohm G m b H , Hamburg (West Germany) RESULTS ON THE USE OF SHOCK-FREE TRANSONIC AIRFOILS FOR TRANSPORT AIRCRAFT J Scheerer In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 198-226 refs Transl into ENGLISH from 'Tragfluegel-Aerodynamik bei schallnahen Stroemungen'. DGLR. Cologne Report DLR-Mitt-73-04 1973 p 241-275 (DGLR-Paper-72-130) Results concerning the design and calculation of supercritical profiles in order to ascertain the applicability of collisionless transonic profiles for wings of large and medium aspect ratio are discussed In order to determine whether the 37 N76-11058 aerodynamic properties of these profiles can be applied to wings, test results concerning the design of straight and yawing quasi-two-dimensional wings are presented and discussed In spite of the fact that the test results are not satisfactory in every respect, the limited use of sweepback theory in the case of supercritical wings is regarded as useful for design purposes In a comparison with comparable conventional profiles an estimate is made of the separation behavior of supercritical profiles in the low-velocity range (Re equals 10,000,000) In connection with the results and experiences discussed for supercritical profiles a possibility of transonic wing design is indicated and discussed Author (ESA) N76-11058 Aeronautical Research Inst of Sweden, Bromma THE PREDICTION OF AIRFOIL DISTRIBUTIONS FOR SUBCRITICAL VISCOUS FLOW AND FOR SUPERCRITICAL INVISCID FLOW A Gustavsson In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 227-245 refs Transl into ENGLISH from Tragfluegel-Aerodynamik bei schallnahen Stroemungen DGLR Cologne Report DLR-Mitt-73-04, 1973 p 276-294 (DGLR-Paper-72-131) An approximate method is described for calculating the pressure distribution on a thick cambered airfoil in subcntical viscous flow The results obtained are compared with recent experimental results for subcntical flow conditions For supercritical mviscid flow conditions pressure distributions were calculated with two finite difference methods A comparison is made between the two methods and with recent experimental results Author (ESA) N76-11059 Messerschmitt-Boelkow-Blohm G m b H Ottobrunn (West Germany) TRANSONIC AIRFOIL THEORY A CRITICAL COMPARISON OF VARIOUS METHODS A Eberle et al In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 246-271 refs Transl into ENGLISH from Tragfluegel-Aerodynamik bei schallnahen Stroemungen" DGLR. Cologne Report DLR-Mitt-73-04, 1973 p 295-328 (DGLR-Paper-72-132) The use of theoretical methods for the design of profiles in the supercritical flow range and the employment of computation procedures for the determination of profile characteristics is discussed The results obtained with the aid of various methods are compared on the basis of an investigation covering six selected profiles Suggestions regarding the merits of the individual methods for the selection and definition of supercritical profiles are presented, and a new formulation is provided concerning the design approach for profiles with shockless compressing Author (ESA) N76-11O60 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany) Inst fuer Aerodynamik THE TRANSONIC TEST-SECTION FOR AIRFOIL MEASUREMENTS IN THE INSTITUTE FOR AERODYNAMICS. BRAUNSCHWEIG G Kausche In ESA Aerodynamics of Airfoils in Transonic Flow (ESA-TT-175) Jul 1975 p 272-287 refs Transl into ENGLISH from Tragfluegel-Aerodynamik bet schallnahen Stroemungen" DGLR. Cologne Report DLR-Mitt-73-04 1973 p 329-346 (DGLR-Paper-72-133) A proposed transonic wind tunnel for profile measurements at fairly high Reynolds numbers is described A detailed account is given of the present state of development of this tunnel, which is a reconstruction of a formerly existing supersonic wind tunnel The concept underlying the design of this tunnel is reviewed Criteria for the design of the tunnel are outlined, and the range of operation of the tunnel is discussed Author (ESA) N76-11061jjl Aeronautical Research Inst of Sweden Stockholm Aerodynamics Dept TRANSONIC AND SUPERSONIC WIND TUNNEL TESTS ON SLENDER CRUCIFORM WING-BODY-TAIL CONFIGURATIONS IN DIFFERENT PITCH AND ROLL POSITIONS Final Report S E Gudmundson and L Torngren 1975 198 p refs (Contracts F-INK-07-12-15 F-INK-82223-72-004) (FFA-TN-AU-988) Avail NTIS HC $7 50 Wmd-tunnel tests were performed to high angles of attack at 7 different Mach numbers between 0 7 and 3 08 and at 5 different roll angles between 0 deg and 45 deg 5-component measurements were done with 9 different model configurations a 15 diameter long cylinder body with a 1 5 diameter long ogive nose together with two different cruciform tails, two different cruciform wings alone and in combination with the body the larger cruciform wings with body and two different tails and the larger wings and tails with the wings mounted three diameters further back on the body Author (ESA) N76-11O63# European Space Agency Paris (France) ON THE LIFTING PROBLEM OF WARPED WINGS IN SUPERSONIC FLOWS Arabmdo Das Jul 1975 62 p refs Transl into ENGLISH of "Zum Auftnebsprobl von Tragfluegeln mit Woelbung u Verwm- dung bei Ueberschallstroemung DFVLR Brunswick Report DLR-FB-75-10, 1975 Original German report available from DFVLR, Pore. West Ger 23 80 DM (ESA-TT-174 DLR-FB-75-10) Avail NTIS HC $4 50 Lift distributions for minimum pressure drag require wing surfaces possessing both camber and twist For this direct problem of finding wing forms under prescribed lift distributions, a simple analytical method is presented The derivations of the approximat- ing formulas follow directly from the general solutions of the perturbation fields in supersonic flow, in which the assumption of moderately slender wings is subsequently introduced In order to check the applicability of the approximating theory the aerodynamic characteristics of delta wings with various camber and twist were calculated and compared with the corresponding values obtained from the exact theories for higher order conical flows As a special case the treatment includes the results for plane wings without warping The calculations of wing shapes under prescribed lift distributions were performed in an obvious and simple manner Linear superposition of various basic distributions permits the generation of complex wing forms Author (ESA) N76-11064# European Space Agency Pans (France) INFLUENCE OF SPLITTER WEDGES ON THE LIFT AND DRAG OF A RECTANGULAR WING WITH A BLUNT TRAILING EDGE M Tanner Sep 1975 51 p refs Transl into ENGLISH of "Einfluss von Trennkeilen auf den Auftneb u Widerstand emes Rechteckfluegels mit stumpfer Hmterkante" DFVLR Goettmgen. West Ger Report DLR-FB-74-61 Jul 1974 Original German report available from DFVLR. Pore West Ger 16 DM (ESA-TT-187 DLR-FB-74-61) Avail NTIS HCS450 Lift and drag measurements were performed on a rectangular wing with a blunt trailing edge fitted with various splitter wedges The Mach number had a value of 0 15 and the Reynolds number a value of 2 million, approximately The results show that for optimum dimensions of the splitter wedge the base drag practically vanishes Then the wing with a blunt trailing edge fitted with a splitter wedge has an equally high maximum lift to drag ratio as a conventional wing with a sharp trailing edge Author (ESA) N76-11065# European Space Agency. Pans (France) UNSTEADY PRESSURE MEASUREMENTS ON OSCILLAT- ING WING/BODY COMBINATIONS COMPARISON BETWEEN THEORY AND EXPERIMENT H Tnebstem et al Sep 1975 76 p refs Transl into ENGLISH of Instationaere Druckverteilungen an schwmgenden schlanken Fluegel-Rumpf-Kombmationen Vergleich zwischen Theone u 38 N76-11080 Messung". DFVLR. Goettingen West Ger Report DLR-FB-74-47. 26 Apr 1974 Original German report available from DFVLR. Port, West Ger 24 DM (ESA-TT-189. DLR-FB-74-47) Avail NTIS HC $5 00 The results of unsteady pressure measurements performed on harmonically oscillating wing-body-combinations in in- compressible flow are discussed The measurements were made in a subsonic wind tunnel at harmonically pitching oscillations about two different pitching axes and at rolling oscillations about the midchord on two different wing-body models with the aspect ratios lambda = 057 and lambda = 1 02 The flow speeds were V = 25 m/s and V = 50 m/s. and the oscillation frequencies were f = 6. 12, 18 and 24 cps The reduced frequencies ran from 0 7 to 5 8 The results of the measurements were critically compared with corresponding theoretical results of the slender-body theory Author (ESA) N76 11070# Naval Postgraduate School. Monterey. Calif FUEL CELL PRESSURE LOADING DURING HYDRAULIC RAM M.S Thesis John W Patterson Jun 1975 62 p refs (AD-A012411) Avail NTIS CSCL 01/3 Hydraulic ram is the phenomenon associated with the damage caused by high speed projectile impacts with fuel tanks It is divided into five phases, entry, shock drag cavity and exit The entry, shock and drag phases were of concern in this study An analytical solution for the pressures developed in the shock phase was formulated based on bullet impact parameters Pressures developed in the drag phase were experimentally correlated with theoretical predictions These pressures were proven to be dependent on front wall wave reflections GRA N76-11067# Ohio State Univ Columbus Aeronautical and Astronautical Research Lab HIGH REYNOLDS NUMBER TRANSONIC TESTING Final Report. 30 Jun 1971 - 30 Jun 1974 John D Lee May 1975 44 p (Contract F33615-71-C-1911. AF Proj 7065) (AD-A011983 ARL-75-0112) Avail NTIS CSCL 20/4 An experimental program was conducted to investigate the feasibility of using a pressurized blowdown wind tunnel to simulate transonic flows at flight Reynolds numbers A 4 inch by 10 inch channel proved to be capable of supplying essentially two- dimensional flows over airfoil models flow departure from the two-dimensional approximation occurred when shock waves terminating local flows of Mach number greater than about 1 5 caused separation of the sidewall boundary layers Simulation of the interaction between the terminal shock wave and the model boundary layer appeared to be adequate Comparisons with data from a larger wind tunnel indicated little or no interference in the subcritical flow range but a large and unpredictable induced attack angle GRA N76-11068+ Wetenschappelijk en Technisch Documentatie- en Informatiecentrum voor de Knjgsmacht. The Hague (Nether- lands) Aircraft Engineering Section FLIGHT SAFETY BIBLIOGRAPHY. 1968 - 1974 B J J Warrmk comp Jan 1975 181 p refs Partly in ENGLISH. GERMAN. FRENCH and DUTCH (TDCK-65616) Avail NTIS HC $7 50 The 373 abstracts of articles and reports available at TDCK are presented Sources of unsafely le mid-air collisions, meteorological and aerodynamic phenomena fog, fire, actual accidents prevention, and survivabihty, safety and survival equipment are the subjects covered in detail ESA N76-11069*# National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif HAZARD CRITERIA FOR WAKE VORTEX ENCOUNTERS Robert I Sammonds and Glen W Stinnett. Jr Aug 1975 45 p refs (NASA-TM-X-62473 A-6232) Avail NTIS HCS400 CSCL 01A A piloted motion-base simulation was conducted to evaluate the ability of simulators to produce realistic vortex encounters and to develop criteria to define hazardous encounters Evaluation of the simulation by pilots experienced in vortex encounters confirmed the capability of the simulator to realistically reproduce wake vortex encounters A boundary for encounter hazard based on subjective pilot opinion was identified in terms of maximum bank angle For encounter altitudes from 200 to 500 ft (61 0 to 1524 m), tentative hazard criteria established for visual flight conditions indicated that the acceptable upset magnitude increased nearly linearly with increasing altitude The data suggest that the allowable upsets under instrument conditions no greater than 50 percent of that allowable under visual conditions Author N76-11077+ Engineering Sciences Data Unit London (England) ESTIMATION OF CRUISE RANGE PROPELLER-DRIVEN AIRCRAFT Aug 1975 18 p refs Sponsored by Roy Aeronautical Soc (ESDU-75018) Copyright Avail NTIS HCS14650 Methods for estimating the cruise air range of propeller- driven aircraft were given Expressions were also given for the fuel flow consumption, specific air range and endurance Piston-engmed and turbo-prop engmed aircraft were discussed Author N76-11078*# Lockheed-Georgia Co, Marietta HIGH REYNOLDS NUMBER TESTS OF A C-141A AIRCRAFT SEMISPAN MODEL TO INVESTIGATE SHOCK-INDUCED SEPARATION W T Blackerby and J F Cahill Washington NASA Oct 1975 193 p refs (Contract NAS2-8269) INASA-CR-2604) Avail NTIS HC $7 50 CSCL 01C Results from a high Reynolds number transonic wind tunnel investigation are presented Wing chordwise pressure distributions were measured over a matrix of Mach numbers and angles-of- attack for which shock-induced separations are known to exist The range of Reynolds number covered by these data nearly spanned the gap between previously available wind tunnel and flight test data The results are compared with both flight and low Reynolds number data, and show that use of the semispan test technique produced good correlation with the prior data at both ends of the Reynolds number range, but indicated strong sensitivity to details of the test setup Author N76-11079*# National Aeronautics and Space Administration Ames Research Center -Moffett Field. Calif DESIGN. COST, AND ADVANCED TECHNOLOGY APPLICA- TIONS FOR A MILITARY TRAINER AIRCRAFT Gary C Hill and Michael Harper Aug 1975 36 p refs (NASA-TM-X-62469) Avail NTIS HC $4 00 CSCL QIC The potential impact is examined of advanced aerodynamic and propulsive technologies in terms of operating and acquisition costs on conceptual mission and performance requirements for a future undergraduate jet pilot trainer aircraft Author N76-11080# Eidgenossisches Flugzeugwerk Emmen (Switzer- land) DESCRIPTION OF THE POSSIBILITY TO UTILIZE A ROTATING CYLINDER AS MOUSTACHE M Martmagha 9 Jan 1973 30 p In GERMAN (CH-6032-Emmen FO-1153) Avail NTIS HC $3 75 A high lift airfoil for the fuselage nose of the Mirage 3 S is developed that reduces starting- and landing-runs This extra airfoil increases lift by increasing the angle of attack, it is kept relatively small for retraction at high flight velocities A rotational cychnder (Magnus effect) is investigated as an alternative to the Moustache effect because of its high C sub A value Transl by G G 39 N76-11081 N76-11081# European Space Agency. Paris (France) CONTROL CONFIGURED VEHICLES (CCV) May 1975 128 p refs Transl into ENGLISH of Regler- Gestuetzte Flugzeuge (CCV)" OGLR. Cologne Report DLR-Mitt- 74-11. 1974 128 p Proc of Joint Meeting of DGLR Specialist Comm 'Flight Characteristics and "Flight Control'. Hamburg. 18 Oct 1973 Original German report available from ZLDI. Munich 26 90 DM (ESA-TT-164. DLR-Mitt-74-11) Avail NTIS HC $6 00 Requirements and possible solutions for control configured vehicles (CCV) are discussed A review is given of control technology problems associated with CCV design, and research is reported on two specimen aircraft with regard to artificial stabilization Requirements for maneuverability and dynamic behavior in longitudinal motion were established A design for a damper-stabilizer system in an aircraft with an elastic elevator system was investigated for different suboptimal control unit structures with limited recovery capacity N76-11082 Messerschmitt-Boelkow-Blohm G m b H . Ottobrunn (West Germany) CONTROL TECHNOLOGY ASPECTS OF AIRCRAFT WITH ARTIFICIAL STABILITY (CCV) WITH PARTICULAR RE- SPECT TO HANDLING UNDER MANEUVER LOADING Wolfgang Kubbat In ESA Control Configured Vehicles (CCV) (ESA-TT-164) May 1975 p 7-32 Transl into ENGLISH from Regler-gestuetzte Flugzeuge (CCV)' DGLR Cologne Report DLR-Mitt-74-11. 1974 26 p Control technology problems with the control configured vehicle (CCV) are reviewed The proposals discussed include control of unstable aircraft control of maneuver loading, reduction of gustmg flutter damping, and control valves In connection with the problem of gustmg reduction/maneuver loading control, it is shown that the solution cannot be treated in isolation, and the concept of an integrated total control of the elastic aircraft is deduced This exercise includes both the control of rigid structural forms (the prevailing task) and the addition of forms of elastic movement Results are presented for two illustrative aircraft The growing difficulty of the complexity of signal gam and processing is discussed Author (ESA) ELEVATOR Gunther Schaenzer In ESA Control Configured Vehicles (CCV) (ESA-TT-164) May 1975 p 104-128 refs Transl into ENGLISH from "Regler-gestuetzte Flugzeuge (CCV) DGLR. Cologne Report DLR-Mitt-74-11. 1974 25 p The design of a damper-stabilizer system in an aircraft with an elastic elevator system was investigated for different sub-optimal control unit structures with limited recovery capacity Probing vertical gustmg was used as the exciting factor Pitch angle speed, flight path speed error, and elevator activity were all taken into consideration in the quadratic quality index Contrary to expectation, the additional return action of the two elevator variables produces only minor improvement of control quality Considerable improvements in control quality are achieved via the strong recovery action of the elevator servo-motor sweep speed The optimal equivalent damping level for the elevator servo-motor amounts to about D = 8 in the specimen aircraft and leads to good control characteristics In all the control unit structures investigated, the elastic elevator brings a deterioration of control quality by comparison with the rigid elevator Author (ESA) N76-11086# Air Force Flight Dynamics Lab, Wright-Patterson AFB Ohio AIRCRAFT GOUND TEST VALIDATION OF A VARIABLE- RESPONSE LANDING GEAR CONCEPT Final Report. Aug 1973 - Aug 1974 Joseph G Mercer Mar 1975 65 p refs (AF Proj 1369) (AD-A011657 AFFDL-TR-74-143) Avail NTIS CSCL 01/3 Taxi tests involving an A-37B aircraft were performed at Wichita Municipal Airport. Kansas The mam landing gear was modified to minimize strut friction and to incorporate a softer pneumatic spring It was found that elimination of strut friction alone or elimination of strut friction combined with the use of a softer pneumatic spring could significantly reduce aircraft wing stresses For the cantilever type strut tested, it was determined that reduction of strut friction should be the primary target in attempting to reduce the transmission of ground loads to the airframe These tests also verified the ability to test trends in landing gear load transmission characteristics using a landing gear drop tower and a hydraulic vibration machine GRA N76-11083 Messerschmitt-Boelkow-Blohm G m b H , Hamburg (West Germany) PARAMETRIC INVESTIGATION OF LONGITUDINAL MOVEMENT OF CCV TRANSPORT AIRCRAFT Heiko Anders In ESA Control Configured Vehicles (CCV) (ESA-TT-164) May 1975 p 57-75 Transl into ENGLISH from "Regler-gestuetzte Flugzeuge (CCV) , DGLR Cologne Report DLR-Mitt-74-11 1974 19 p Making use of two specimen aircraft (the A-300 B and the CON 30 STOL transport project design), research into the artificial stabilization of these aircraft was carried out Require- ments for maneuverability and dynamic behavior in longitudinal movement were established These served for control system design and for definition of critical boundaries Also investigated were the effects of different parameters on the critical boundaries to establish trends for future design work The specimen aircraft were used to demonstrate how much can be achieved in additional performance by artificial stabilization (useful load, range) It was established that in the transport aircraft investigated a renuncia- tion of natural stability can lead to an improvement in cost- effectiveness Author (ESA) N76-11084 Bodenseewerk Geraetetechnik G m b H Ueberlmgen (West Germany) FUNDAMENTAL RESEARCH INTO THE OPTIMAL DESIGN OF A DAMPER-STABILIZER SYSTEM WITH AN ELASTIC N76-11086# Teledyne Ryan Aeronautical Co. San Diego, Calif COMPOSITE MANEUVER AUGMENTATION (COMMA) FOR FIGHTER AIRCRAFT PRELIMINARY DESIGN STUDY Robert B Chisman Jan 1974 311 p refs (Contract F33657-73-A-O056-0005) (AD-A011772 TRA-30120-1 AFFDL-TR-73-143) Avail NTIS CSCL 01/3 The Air Force Flight Dynamics Laboratory plans to test an advanced composite wing with an internally blown jet flap on a low cost, low risk unmanned vehicle This technical report identifies required modifications to the BQM-34F target vehicle, including the engine and wing interface constraints, to support the flight test program Emphasis was given to the fuselage structure elevator control power, bleed air valve and ducting, flight control system, vehicle electrical system and the instrumentation and telemetry systems AFFDL provided the wing definition and jet flap wind tunnel test data GRA N76-11087# Goodyear Aerospace Corp. Litchfield Park. Ariz WINDOW CONTOURED GLASS/PLASTIC TRANSPARENT ARMOR FOR THE UH-1D HELICOPTER Final Report. 4 Jan 1973 - 20 Jan 1975 Wilson C McDonald and Richard A Huyett May 1975 82 p (Contract DAAG46-73-C-0075) (AD-A012215 GERA-2074. AMMRC-CTR-75-12) Avail NTIS CSCL 01/3 40 N76-11094 The objectives of this program relate to the design of a transparent armor installation for the UH-1D helicopter This effort incorporated for the first time significant amounts of high performance glass/plastic laminate armor in an aircraft Eight slipsets of armor were produced one of which was installed and flight tested Environmental testing was also conducted to define armor performance and characteristics GRA N76-11088$ Advanced Technology Center. Inc. Dallas, Tex DESIGN STUDIES OF TRANSONIC AND STOL AIRFOILS WITH ACTIVE DIFFUSION CONTROL Final Report. 19 Apr 1973 - 19 Jun. 1974 C H Haight. T D Reed, and B T Mortand 19 Jun 1974 88 p refs(Contract N00019-73-C-0426) (AD-A011928. ATC-B-94300/4CR-24) Avail NTIS CSCL 01/3 Results of parametric design studies are presented for supercritical airfoils which employ active diffusion control Efforts were concentrated on two basically different airfoil profiles One type of airfoil has a 6% thickness to chord ratio and employs an antiseparation tailored contour (ATC) located in the forward lower surface This type of airfoil is considered to be a promising candidate for improving the transonic performance of combat aircraft The second type of airfoil is 12% thick and has an ATC within the aft. upper surface This type of wing section is applicable to transonic transports and is compatible with previous STOL designs which employ ATC's Theoretical analyses indicate both airfoils have large values of the transonic cruise parameter, good transonic lift characteristics, and. in general, offer improved transonic performance GRA N76-11089$ United Aircraft Corp. Stratford, Conn Sikorsky Aircraft Div HELICOPTER MAINTENANCE EFFECTIVENESS ANALYSIS Final Report Calvin Holbert and Gary Newport May 1975 131 p (Contract DAAJ02-73-C-0029. DA Pro] 1F1-62205-A-119) (AD-A012225. USAAMRDL-TR-75-14) Avail NTIS CSCL 01/3 A study has been made of U S Army maintenance operations to determine the significance of repetitive maintenance and incorrect diagnoses in regard to U S Army maintenance efficiency A questionnaire was distributed to Army maintenance personnel to solicit their views on maintenance efficiency In addition. Army aircraft inspection and maintenance data (DA Form 2408-13 and Operations Reliability Maintainability Engineering Data) were reviewed to quantify the number of repetitive maintenance actions These data included maintenance personnel and maintenance actions for the UH-1H. Ch-47C. and CH-54B model helicopters GRA N76-1109O# Raven Industries Inc. Sioux Falls. S Dak POBAL-S. THE ANALYSIS AND DESIGN OF A HIGH ALTITUDE AIRSHIP Final Report. Oct. 1972 - Mar 1976 Jack D Beemer. Roger R Parsons Loren L Rueter Paul A Seuferer and La Del I R Swiden 15 Feb 1975 183 p refs (Contract F19628-73-C-0076. AF Proj 6665 AF Pro] 6866) (AD-A012292. R-0275006, AFCRL-TR-75-0120) Avail NTIS CSCL 01/3 An engineering analysis and development effort has been executed to design a superpressure airship, POBAL-S, capable of station keeping at an altitude of 21 kilometers for a duration of 7 days while supporting a payload weighing 890 newtons and requiring 500 wans of electncal power A detailed parametric trade-off between various power sources and other design choices was performed The computer program used to accomplish this analysis is described and many results are presented Th system concept which resulted was a fuel cell powered, propeller driven airship controlled by an on-board autopilot with basic commands telemetered from a ground control station Design of the balloon power tram, gimbaled propeller assembly and electronic/electrical systems is presented Flight operations for launch and recovery are discussed GRA N76-11091# Naval Intelligence Support Center. Washington. D C Translation Div THE SORMOVICH EXPERIMENTAL AIR CUSHION VEHI- CLE A Zhivotovskn V Shenberg and A Mmchenya 28 May 1975 7 p Transl into ENGLISH from Rechn Transp (USSR), no 3 1973 p 53-54 (AD-A012080 NISC-Trans-3677) Avail NTIS CSCL 13/10 The subject experimental air cushion passenger vehicle is an amphibious craft with a nozzle system for forming the air cushion a flexible skirt, and location of the engine room, fan and air propellers in the stern and delivery of power to all users from a single engine through a system of gears and shafts GRA N76-11092# Lockheed-Georgia Co Marietta EVALUATION OF THE FLYING QUALITIES REQUIREMENTS OF MIL-F-8785B ASG USING THE C-5A AIRPLANE Final Report. Sep 1974 - Mar 1975 Charles C Silvers and Clifton C Withers 20 Mar 1975 335 p (Contract F33615-75-C-3012) (AD-A011728 AFFDL-TR-75-3) Avail NTIS CSCL 01/2 The study was conducted to validate military specification MIL-F-8785B(ASG). Flying Qualities of Piloted Airplanes, dated 7 August 1969 Interim Amendment-1 (USAF). dated 31 March 1971 by performing a detail comparison of its requirements with the known characteristics of the Lockheed C-5A and pilot comments on them The comparison was based primarily on existing flight test data supplemented by analytical data as required for this evaluation process Paragraph by paragraph validations of discrepancies are noted, resolution attempted if necessary, and any recommendations given In addition, recommendations are made enumerating experimental and analytical investigations beyond the scope of this study which will provide data for further validation and updating of the requirements GRA N76-11093# Bell Helicopter Co, Fort Worth Tex AN INVESTIGATION OF HIGH G MANEUVERS OF THE AH-1G HELICOPTER James R VanGaasbeek Apr 1975 179 p refs (Contract DAAJ02-73-C-0092, DA Proj 1F1-62208-AA-43) (AD-A012234 USAAMRDL-TR-75-18) Avail NTIS CSCL 01/2 The high-g maneuver capabilities of the AH-1G have been investigated in this effort Flight test data for 132 high-g maneuvers have been studied and statistically analyzed to determine the relationships among the variables A series of fixed-collective symmetric pullups was simulated, using the Rotorcraft Flight Simulation Program C81 to determine the mechanisms limiting high-g maneuvers of the AH-1G Statistical analysis of the C81 data was used to supplement the analysis of the test data Three additional maneuvers, similar to the most severe test maneuvers were simulated GRA N76-11094# Boeing Vertol Co Philadelphia. Pa ENGINE/TRANSMISSION/AIRFRAME ADVANCED INTE- GRATION TECHNIQUES Final Technical Report Theodore Himka and Richard D Semple May 1975 172 p refs (Contract DAAJ02-74-C-0043. DA Pro] 1G2-62207-AH-89) (AD-A012236 D210-10900-1 USAAMRDL-TR-75-16) Avail NTIS CSCL 01/3 Innovative engine/transmission/airframe integrated design concepts were developed to provide total airflow and power management for a utility transport helicopter which meets 41 W 7(5-11095 projected requirements of future Army aircraft These requirements include engine compartment cooling, drive train and transmission oil cooling, engine oil cooling, exhaust plume and hot matal infrared ( IR) signature suppression and engine inlet foreign particle protection GRA M7S-11095# Hughes Helicopters Culver City Calif PRODUCIBILITY AMD SERVICEABILITY OF KEVLAR-49 STRUCTURES MADE ON HOT LAYUP TOOLS Final Report. 31 Rflov 1974 - 30 Apr 1975 B Head J Leach. R Goodall and C Sitterly May 1975 114 p refs (Contract DAAG46-74-C-0100) (AD-A012265. AMMRC-CTR-75-10) Avail NTIS CSCL11/4 The purposes of the program were evaluate the producibihty of a helicopter structural component made from Kevlar-49 fibers, demonstrate the low cost aspects of using hot layup tools to fabricate composite structures, and evaluate the serviceability of the Kevlar-49 structure in actual field operations GRA N78-11O97*# National Aeronautics and Space Administration Langley Research Center, Langley Station, Va DUCT LINER OPTIMIZATION FOR TUR8OMACHINEHY NOISE SOURCES Harold C Lester and Joe W Posey Nov 1975 20 p refs Presented at 90th Meeting of the Acoust Soc of Am , San Francisco. 4-7 Nov 1975 (NASA-TM-X-72789) Avail NTIS HC $3 50 CSCL21E An acoustical field theory for axisymmetnc multisectioned lined ducts with uniform flow profiles was combined with a numerical minimization algorithm to predict optimal liner configurations having one, two, and three sections Source models studied include a point source located on the axis of the duct and rotor/outlet-stator viscous wake interaction effects for a typical research compressor operating at an axial flow Mach number of about 04 For this latter source, optimal liners for equipartition-of energy, zero-phase and least-attenuated-mode source variations were also calculated and compared with exact results It is found that the potential benefits of liner segmentation for the attenuation of turbomachmery noise is greater than would be predicted from point source results Furthermore, effective liner design requires precise knowledge of the circumferential and radial modal distributions Author R)78-11098°# Solar San Diego, Calif ADVANCED LOW NO SUB a COMBUSTORS FOR SUPER- SONIC HIGH-ALTITUDE AIRCRAFT GAS TURBINES Report for Rflor 1974 - Jun 1975 P B Roberts. D J White, and J R Shekleton Nov 1975 81 p refs (Contract NAS3-18028) (NASA-CR-134889 RDR-1814) Avail NTIS HCS500 CSCL A test rig program was conducted with the objective of evaluating and minimizing the exhaust emissions, in particular NO sub x of three advanced aircraft combustor concepts at a simulated, high altitude cruise condition The three combustor designs, all members of the lean reaction premixed family, are the Jet Induced Circulation (JIC) combustor, the Vortex Air Blast (VAB) combustor, and a catalytic combustor They were rig tested in the form of reverse flow can combustors in the 0 127 m (50 in) size range Various configuration modifications were applied to each of the initial JIC and VAB combustor modal designs in an effort to reduce the emissions levels The VAB combustor demonstrated a NO sub x level of 1 1 gm NO2/kg fuel with essentially 100% combustion efficiency at the simulated cruise combustor condition of 50 7 N/sq cm (5 atm). 833 K (1500 R) inlet pressure and temperature respectively and 1778 K (3200 R) outlet temperature on Jet-AI fuel Early tests on the catalytic combustor were unsuccessful due to a catalyst deposition problem and were discontinued in favor of the JIC and VAB tests In addition emissions data were obtained on the JIC and VAB combustors at low combustor inlet pressure and temperatures that indicate the potential performance at engine off-design conditions Author M73-11099°# Naval Air Propulsion Test Center. Trenton. NJ ROTOR BURST PROTECTION PROGRAM STATISTICS 0RJ AIRCRAFT GAS TURBINE ENGINE ROTOR FAILURES THAT OCCURRED IN US COMMERCIAL AVIATION DURING 1973 Final Report. 1972 - 1973 R A De Lucia and G J Mangano Aug 1975 28 p (NASA Order C-41581-B) (NASA-CR-134854 NAPTC-PE-61) Avail NTIS HCS375 CSCL 21E Statistical data on gas turbine rotor failures that have occurred in U S commercial aviation during 1973 was presented Analysis of the data led to the following conclusions (1) the incidence of rotor failure and uncontamed burst is significantly high enough to warrant continuation of the efforts of the Rotor Burst Protection Program (RBPP), (2) of all the types of fragments generated, disk fragments because of their size, high energy content and high rate of uncontamment (100 %), continue to be a major threat to the welfare and safety of commercial aircraft passengers, (3) the number of uncontamed blade failures is surprisingly high since rotor blade containment is required for engine certification under FAA regulations. (4) it appears that causes beyond the control or scope of pressent technology are still primarily responsible for most of the rotor failures that occur YJA W78-111CO*# Transemantics. Inc. Washington, DC THE PROBLEM OF FLOW MIXING IN A DOUBLE-FLOW ENGINE Barbara Jung Washington NASA Nov 1975 20 p refs Transl into ENGLISH from Technika Lotnicza i Astronautyczna (Poland) v 22 Aug 1967 p 5-10 (Contract NASw-2792) (NASA-TT-F-16648) Avail NTIS HC $3 50 CSCL21E The problem of mixing gas flow from the main channel and air flow from the outer channel of a double-flow engine was discussed Methods of designing the mixing chambers to achieve a constant cross-section and a constant pressure in the range of subsonic velocities for both flows were presented, and the usefulness of flow mixing was justified Some typical construc- tion designs for mixing chambers were described Author N76-11103# Southwest Research Inst San Antonio. Tex DEVELOPMENT OF A ROTATING CYLINDER DEPOSITION TEST Interim Report. 1 Feb 1972 - 31 Mar 1975 J P Cuellar and B B Baber Jun 1975 65 p refs (Contract F33615-72-C-1097. AF Proj 3048) (AD-A012298. SwRI-RS-629, AFAPL-TR-75-37) Avail NTIS CSCL 11/8 A rotating cylinder deposition test for the evaluation of aircraft turbine engine lubricants was investigated The device was selected for study on the basis of its promise for achieving controlled or measurable lubricant films and oxidative exposure conditions Evaluation tests with this configuration were performed with four coded lubricants Performance criteria in these tests included deposit rating, viscosity and neutralization number change, and oxygen consumption Test conditions selected for this series of runs results in severe fluid deterioration for all but one lubricant GRA N78-11105*# National Aeronautics and Space Administration. Washington. D C FLIGHT-DETERMINED STABILITY AND CONTROL DERIVA- TIVES FOR AN EXECUTIVE JET TRANSPORT Harriet J Smith Jul 1975 46 p refs (NASA-TM-X-56034. H-901) Avail NTIS HC $400 CSCL 01C A modified maximum likelihood estimation (MMLE) technique which included a provision for including a priori information about unknown parameters was used to determine the aerodynamic derivatives of the Lockheed JetStar airplane Two hundred sixty-five maneuvers'were performed with the JetStar airplane, which was modified to include direct lift controls to obtain lateral-directional and longitudinal derivatives Data were obtained at altitudes of 3048 meters 6096 meters, and 9144 meters 42 N76-11317 (10.000 feet 20.00O feet and 30.000 feet) and over an angle of attack range from approximately 3 deg to 13 deg and a Mach number range from 025 to 075 Side force generators were installed and tested in 87 maneuvers to determine their effectiveness and their effect on the other derivatives Lateral- directional data for four flight conditions were analyzed without using a pnon information to assess the effect of this feature on the results The MMLE method generally gave consistent (repeatable) estimates of the derivatives, with the exception of the rolling moment due to yaw rate which showed large vanances Author N76-11106jjl Honeywell. Inc . Minneapolis. Minn Government and Aeronautical Products Div DEVELOPMENT OF A HYDROFLUIDIC STABILIZATION AUGMENTATION SYSTEM HYSAS FOR AN AX CLASS AIRCRAFT Final Report. Dec 1972 - Nov 1974 Holger C Kent Jan 1975 177 p (Contract F33615-73-C-3068) (AD-A011727. Honeywell-W-3068, AFFDL-TR-74-147) Avail NTIS CSCL01/3 This program consisted of the design, development, fabrica- tion and evaluation of a Hydrofluidic Yaw Axis Stability Augmentation System (HYSAS) The objective was to develop a low cost reliable lightweight, flightworthy HYSAS with moderate performance and low-field maintenance characteristics compared to an electro-hydraulic SAS for jet powered AX class tactical aircraft A system analysis was conducted that included a computer simulation of the Fairchild Aircraft Co A-10 aircraft From the results of the computer simulation, a yaw damper configuration was determined that improved flying quality characteristics by increasing dutch roll damping throughout the Hight envelope of the AX Class Tactical Aircraft (AXCTA) GRA N76-11107# Bell Helicopter Co Fort Worth. Tex FLIGHT CONTROL SYSTEM RELIABILITY AND MAINTAIN- ABILITY INVESTIGATIONS Final Report John Zipperer, Gavin Jenney. and Jerry Bryant Mar 1975 294 p refs (Contract OAAJ02-73-C-0026. DA Pro) 1F1-62203-A-119) (AD-A012233. USAAMRDL-TR-74-57-FR) Avail NTIS CSCL 01/3 Army helicopter nonrotatmg flight control system specifications standards and design handbooks were reviewed \for areas in which improvements could be made to requirements affecting system and mission reliability and maintainability R and M requirements were essentially missing from all documents reviewed and therefore specific requirements were added for reliability, maintainability, and supporting workmanship qualifica- tion and production acceptance Special emphasis was directed toward requiring those distributional material properties, failure and maintenance time data and analytical methods which permit Design for Reliability (Probabilistic Design) and Maintainability directly into components and thus into the flight control system GRA N76-11179* National Aeronautics and Space Administration Lyndon B Johnson Space Center Houston. Tex FIRE-RESISTANT AIRCRAFT MATERIALS DEVELOPMENT AND EVALUATION PROGRAM Richard W Bncker and Robert N Stuckey In its 8th Conf on Space Simulation 1975 p 833-854 refs (Paper-70) CSCL 14B An aircraft flammability program was undertaken to utilize spacecraft developed fire-resistant materials to improve passenger safety and decrease losses from unattended fires in commercial aircraft Five full-scale aircraft flammability tests were performed to evaluate the effectiveness of improved fire-resistant materials by comparing their burning characteristics with those of pre-1968 aircraft materials Author N76-11267# Boeing Aerospace Co . Seattle Wash Research and Engineering Div EVALUATION OF REINFORCED THERMOPLASTIC COMPO- SITES AND ADHESIVES Final Report. 1 Apr 1974 - 1 Feb 1976 J T Hoggatt and A D VonVolkli Mar 1975 100 p refs (Contract N00019-74-C-0226) (AD-A011407 D180-17503-3) Avail NTIS CSCL 11/4 Kevlar-49 fabnc laminates with polysulfone resin matrix were evaluated for mechanical and electrical properties and environmen- tal resistance to explore its potential for secondary and primary aircraft structure Investigations indicated Kevlar-49 reinforced thermoplastic laminates in general exhibited properties equivalent to laminates made with thermosetting matrices Thermoplastic polymers with service temperatures in excess of +300 F were screened with three polymers being subjected to in-depth study These polymers were 200P polysulfone (+325 F service) 720P polysulfone (+400 F service) and NR150A polyimide (+450 F service) Each material exhibited good property translation and thermal stability within the stated service temperature range Processing conditions for the polymers were within the limitations of most commercial autoclaves Polysulfone resin was evalu- ated as an adhesive and exhibited excellent adhesive properties for bonding stainless steel and composites Values in excess of 4500 psi and 3400 psi were obtained at 70 F and +250 F. respectively, on stainless steel lap bond specimens Composite-to- composite bonds produced values in excess of 8000 psi with a polysulfone adhesive GRA N76-11292jjf Ministry of Defence London (England) THE EVALUATION OF VHR 2A AND VHR 3A GLASSES (GLAVERBEL-MECANIVER S A ) FOR AEROSPACE APPLIC- ATIONS N S Corney Mar 1975 32 p refs (BR44083 DR-Mat-198) Avail NTIS HCS400 The mechanical properties of two glasses for aircraft transparencies were evaluated using beam specimens of 2mm thickness The products are shown to be of reproducible quality with modulus of rupture 247 MPa (standard deviation 11 MPa) for VHR 2A and 233 MPa (standard deviation 7 MPa) for VHR 3A The effects of a standard sand abrasion at two levels of severity were investigated Some thermal ageing experiments were carried out on both glasses in the unloaded condition Sustained loading experiments for 3000h at 60% of the modulus of rupture in the as-received (or appropriately abraded condition) were earned out and indicated no significant effect of sustained loading on modulus of rupture Likewise cyclic loading experiments on the as-received glasses for 2000h at a cycle of 3h on load (at a value of 30% of the initial modulus of rupture) 0 5h off load, caused no degradation of the modulus of rupture Climatic weathering tests on these glasses are in progress and the results to date show no deterioration of the modulus of rupture after 1 year exposure in the unloaded condition It is shown that both VHR2A and VHR3A glasses of 2mm thickness have properties entirely suitable for certain aircraft applications eg as facing glasses for structural plies of plastic materials or as laminating piles for low speed aircraft Because of the improved resistance of the VHR3A glass at the more severe level of abrasion this glass might be preferred in particular applications Author (ESA) N76-11317# Mar, Inc. Rockville Md FEASIBILITY STUDY OF , HELICOPTER-TOWED AIR CUSHION LOGISTIC VEHICLES Final Report. 31 Mar - 30 Jun 1975 V F Neradka J C Stevens and R L Levin Jun 1975 67 p refs (Contract N00014-73-C-0178) (AD-A011803. TR-148) Avail NTIS CSCL 13/10 A feasibility study of a helicopter-towed air cushion logistic vehicle (ACLV) was performed The scope of the study encompassed movement of loaded LASH system lighters on unmanned air-cushion platforms from an off-shore ship onto a sand beach in support of amphibious assault operations Motive power is to be provided by towing with RH-53 helicopter Color illustrations reproduced in black and white GRA 43 N76-11396 N76-11396# Massachusetts Inst o1 Tech, Cambridge Fluid Dynamics Research Lab ON THE DEVELOPMENT OF A UNIFIED THEORY FOR VORTEX FLOW PHENOMENA FOR AERONAUTICAL APPLICATIONS Technical Report. 1 Nov 1973 - 31 Oct 1974 Thomas K Matoi 14 Apr 1975 145 p refs (Contract N00014-67-A-0204-0085. NR Proj 215-230} (AD-A012399) Avail NTIS CSCL 20/4 The low-speed performance of a high span loading aircraft depends critically on the structure and stability of the vortex flow field created by the wing Conventional formulation of lifting surface theory is not adequate to handle the low-aspect-ratio wing problem since the leading edge vortices add several complications Specifically the nonplanar nature of the vortex sheet may have to be considered explicitly, the leading-edge loading is altered, and vortex breakdown is a rotational phenom- enon Due to those additional difficulties, a study was made of the state of the art in vortex-wing interactions GRA N76-1144O# Technische Hochschule Vienna (Austria) ACTUAL DESIGN CRITERIA IN MECHANICAL ENGINEER- ING Franz Mueller-Magyan and Walter Sperr 1975 7 p refs In GERMAN ENGLISH summary (ICAF-Doc-794) Avail NTIS HC $3 50 Some methods by which the determination of the fatigue life of aircraft components can be performed were discussed Two of these the Safe Life and the Fail Safe approaches are the basis for numerous studies in fatigue analysis and fracture mechanics In this case the crack length in a component is introduced as a measure of damage and the crack propagation rate as a criterion for the fatigue life The objectives are an analysis of the local stress distribution in the cracked area and the question of damage accumulation The empirical (program tests) and the analytical evaluation of damage accumulation (accumulation hypothesis) were discussed The basis of such studies are evaluations of load-time histories and the correlation of load input and dynamic response data A very recent item of engineering design, the transition from allowable-stress design to fatigue life prediction criteria, was also discussed Author N76-11448jP McDonnell Aircraft Co, St Louis. Mo RELIABILITY OF STEP-LAP BONDED JOINTS Final Report E B Birchfield R T Cole and L F Impellizzen Apr 1975 177 p refs (Contract F33615-74-C-3015. AF Pro) 4364) IAD-A012009. AFFDL-TR-75-26) Avail NTIS CSCL 13/5 The objective of the program was an improved technology base of data and methods applicable to the efficient design of graphite-epoxy to titanium step-lap-bonded airframe |omts that are optimized for reliability under military flight loading A random spectrum was used in repeated load tests to establish a data base for defining lifetime and residual strength characteris- tics Static strength tests were also conducted which show good comparison with prediction of an elastic-plastic analysis procedure The static strength, residual strength and lifetime data were assumed to be from Weibull distributions The shape and scale parameters for each of these distributions were calculated using the best linear unbiased (BLU) estimation procedure Using these procedures wearout models were calibrated and checked and conclusions concerning scaling, and translation of parameters were drawn Tests were also conducted to determine the effect upon lifetime of load truncation load frequency, relaxation time between missions, and temperature GRA discussed by distinguishing between two engineering applications (1) high-stressed thick-walled components, such as pressure vessels or turbine-rotor discs, which show relatively short critical crack lengths and plane strain conditions, and (2) thin-walled, stiffened components like aircraft shell structures In the first case, the analysis deals with methods for the prevention of brittle fracture and crack initiation difficulties may arise with the introduction of dynamic loads and corrosive effects on subcntical crack growth In the second case, subcntical crack growth under random loads and the determination of the fracture strength of the components are of main interest The advantage of a more simple theoretical approach in plane stress conditions is opposed by the necessity to introduce the influence of a large plastic zone at the crack tip Practical applications of these concepts are given Author N76-11472# European Space Agency. Pans (France) A NEW DEVICE FOR THE VIBRATORY EXCITATION OF MECHANICAL STRUCTURES Jean-Francois Boisseau Sep 1975 45 p refs Transl into ENGLISH of "Un Nouveau Dispositif d'Excitation Vibratoire de Struct Mecan ONERA Pans Report ONERA-NT-223. 1974 (ESA-TT-184 ONERA-NT-223) Avail NTIS HCS400 Vibration generators are described which include a rotating mobile dynamically balanced element, driving a mass in a linear movement along an unlimited travel The rotation kinetic energy of the mechanism and the kinematic ratio are optimized for the required conditions (available force, expected perturbations, and mass participation in the excited structure) The proposed solutions present some interesting properties which lie between those of the reversible electrodynamic and the irreversible hydraulic generators Ground and flight test results on several models (force 40 to 450 N and travel 50 to 450 mm) were in good agreement with the calculations and known results Other applications are being considered for heavy structures excited between 0 1 and 30 Hz, in harmonic and random modes Author (ESA) N76-11915# RAND Corp Santa Monica Calif ESTIMATING LIFE-CYCLE COSTS A CASE STUDY OF THE A-7D Marco Fiorello Feb 1975 65 p (Contract F44620-73-C-0011) (AD-A011643, R-1518-PR) Avail NTIS CSCL 15/5 The report is concerned with the determination of costs incurred in acquiring and owning a weapon system and the data problems associated therewith Incurred or historical costs can be used to anticipate future costs of operations and support, to compare forecast with incurred costs for evaluating fore- casting techniques, or to estimate a weapon system s total life cycle costs (LCC) for use along with the associated weapon system capability, in force structure planning The principal objective of the study is to demonstrate the derivation of the life-cycle cost GRA N76-11456* Technische Hochschule Vienna (Austria) THE FRACTURE MECHANICS APPROACH IN STRUC- TURAL DESIGN Walter R Sperr 1975 8 p refs In GERMAN, ENGLISH summary (ICAF-Doc-795) Avail NTIS HC $3 50 The concept of fracture mechanics in structural design was 44 SUBJECT INDEX AERONAUTICAL ENGINEERING /A Special Bibliography (Suppl 67) Typical Subject Index Listing FEBRUARY 1976 COHBGSTIOI PHISICS- •Combnstion generated noise in gas turbine combustorsl engine noise/noise redaction [8*Si-CB-13U6»3] H76-10123 TITLE NUMBER The title is used to provide a description of the subject matter When the title is insufficiently descriptive of the document content a title extension is added separated from the title by three hyphens The NASA or AIAA accession number is included in each entry to assist the user in locating the abstract in the abstract section of this supplement If applicable a repon number is also included as an aid in identifying the document ACCELEBATIOH PBOTBCTICi Botor burst protection program: statistics on aircraft gas tnrtine engine rotor failures that occurred in US commercial aviation during 1973[BASA-CB-134854] B76-11099 ACCEPTABILITY acceptance rates and tooling capacity for selected military aircraft[AD-A011501] 1176-10909 AC00SIIC ATTEBOATIOI Discrete components in ejector noise and techniques for suppressing then A76-10241 ACOOSTIC HEASUBBHEBTS Rake vortex prograi status A76-10399 Design, fabrication and acoustic tests of a 36 inch (0.914 meter) statorless turbotip fan [HlSi-CB-2597] N76-10125 iCCOSTIC PBOPBBTIES Investigation of the acoustic characteristics of a supersonic jet flowing into a cylindrical tube A76-10250 AEBODTiABIC BA1ABCE Some comments on trim drag H76-11019 ABBODYBAHIC CBABACTEBISTICS Practical aerodynamics of the Iak-40 aircraft /2nd revised and enlarged edition/ Russian book A76-10307 Unsteady transonic aerodynamics - in aeronautics challenge A76-10350 Response of a nozzle to an entropy disturbance Example of thermodynamically unsteady aerodynamics A76-10356 On lifting-line theory in unsteady aerodynamics A76-10357 Generalized similarity lavs for flows past three-dimensional bodies A76-115HO Banging gliders - Theory and practice. I A76-11897 A passive gust alleviation system for a light aircraft [BASS-CB-2605] H76-10002 Aerodynamic characteristics of a large-scale hybrid upper surface blown flap model having four engines CHASA-TH-X-62460] H76-10063 Aerodynamic characteristics of a tandem wing configuration of a Hach number of 0.30 [HASA-TH-X-72779] B76-10066 An application of the Ogee tip H76-11011 Certain problems of experimental aerodynamics [BASA-IT-P-16565] B76-11031 Transonic airfoil theory: A critical comparison of various methods [DSLB-EAPEB-72-132] B76-11059 The transonic test-section for airfoil measurements in the Institute for Aerodynamics, Braunschweig [DGIB-PAPBB-72-133] B76-11060 AEBODYHAHIC COEFFICIENTS On aerodynamic coefficients of arbitrary biplane Ming sections A76-10713 Advanced panel-type influence coefficient methods applied to subsonic and supersonic flows B76-10042 ABBODYHAUIC COBFIGOBATIOIS Effect of forebody shape and shielding technique on 2-D supersonic inlet performance [AIAA PAPBB 75-1183] A76-10253 Aerodynamic profiles conformal mapping generation with several corner points A76-11097 Aerodynamic design consideration for maneuverability A76-11972 Secent developments in propulsive-lift aerodynamic theory B76-10039 An integrated system for the aerodynamic design and analysis of supersonic aircraft 576-10016 Indicial compressible potential aerodynamics around complex aircraft configurations B76-10047 Design, fabrication and acoustic tests of a 36 inch (0.914 meter) statorless turbotip fan [BASA-CB-2597] B76-10125 Asymptotic analytical methods in fluid mechanics related to drag prediction B76-11006 AEBOOTBAHIC DBAG Estimation of velocities and roll-up in aircraft vortex wakes A76-11229 Effects of jet exhaust gas properties on exhaust simulation and afterbody drag [BASA-TB-B-44H] B76-10006 Prospects and time tables for analytical estimation of the drag of complete aircraft configuration B76-10999 Simplified theoretical methods for aerodynamic design B76-11001 Propeller blockage research needs H76-1100* Asymptotic analytical methods in fluid mechanics related to drag prediction H76-11006 The economic impact of drag in general aviation 876-11007 Drag of the complete configuration aerodynamic considerations, 2 H76-11023 Learjet model 25 drag analysis B76-11024 Influence of splitter wedges on the lift and drag of a rectangular wing with a blunt trailing edge [ESA-TT-187] H76-11064 A-1 UBODIIUUC FOBCBS SUBJECT IIDBI AEBODTIAHIC FOBCBS Forces on aastaggeted airfoil cascades in unsteady in-phase lotion «ith applications to harmonic oscillation 476-10359 1BBODT1AHIC HBATII6 Towards bypersonics civil and military flight 176-12300 1EBODI11BIC IBTZBFBBBHCB The development of theoretical models for jet-indaced effects on V/STOL aircraft [AIAA P1PBB 75-1216] A76-10263 Becent advances in techniques for dynamic stability testing at BAE 176-10330 So»e conclusions froa an investigation of blade-vortex interaction 176-11772 ABBODTBAHIC IOADS Subsonic flow past an oscillating cascade with stead; blade loading - Basic forialation 176-10360 Joint aircraft loading/structure response statistics of tiie to service crack initiation [AD-A011646] N76-10120 Bedesigned rotor for a highly loaded, 1800 ft/sec tip speed compressor fan stage 1: Aerodynamic and mechanical design [BASA-CB-134835] H76-10133 AEBODTIABIC BOISE Discrete components in ejector noise and techniques for suppressing them A76-10241 Acoustic pressure field of vortex sound near rotating blades A76-10242 Influence of the turbulence of the flow incident on a body on the intensity of vortex sound emission 176-10243 Vortex noise of rotating machinery A76-10244 Blade-wheel noise caused by random inhonogeneities of an incoming flo« 176-10248 Noise-con 75; Proceedings of the National Conference on Boise Control Engineering, Gaithersbnrg, Hd., September 15-17, 1975 176-10318 Jet noise - Ige 25 aerodynaaic flow and noise generation theories 176-10319 AEBODTBABIC ST1BIIITT 1 method for analyzing the stability of a wing in flight A76-10701 The CCV concept Control Configured Vehicle A76-11660 A flight test determination of the static and dynamic longitudinal stability of the Cessna 310H aircraft [AD-1010795] H76-10141 AEBODIBAHIC SI1LIHG Becent developments in dynamic stall 176-10327 Transonic buffet response testing and control 176-10341 Ronlinear relay model for post-stall oscillations 176-11228 Experimental studies of flow separation and stalling on two-dimensional airfoils at low speeds. Phase 2: Studies with Fowler flap extended [N1SA-CB-145741] B76-11037 ABBODIIAHICS Unsteady aerodynamics; Proceedings of the Syiposium, University of Arizona, Tucson, Ariz., Harch 18-20, 1S75. Volumes 162 A76-10326 lerodynanc analyses Beqniring Advanced Computers, Part 1 [HAS4-SP-347-PT-1] B76-10007 A technique for accelerating iterative convergence in numerical integration, with application in transcnic aerodynamics [B1SA-TB-X-62495] H76-11039 Theoretical aerodynamics of upper-surface-blowing jet-wing interaction [HASA-TH-D-7936] N76-11041 1BBOBL1STICITI The design, analysis and experimental evaluation of an elastic model wing [HASA-CB-144535] H76-10092 AEBOB10IIC1L BB6IBBBBIBG Antivibration insulation in the aeronautics field A76-10517 International Council of the Aeronautical Sciences, Congress, 9tj>, Haifa, Israel, August 25-30, 1974, Proceedings. Volume 1 - Fluid Dynamics, Aerodynamics and Gas Dynamics. Volume 2 - Structures, Materials, Dynamics, Propulsion, Design, Boise and Pollution A76-11166 Actual design criteria in mechanical engineering [IC1F-DOC-794] H76-11440 AEBOSP1CB BieiHEEBIIG La Becherche Aerospatiale. Bimonthly Bulletin Ho. 1974-5 [ESA-TT-181] B76-10979 AEBOSPACB STSTBHS Systems engineering and air transport A76-12154 APTBBBODIES Beynolds number effect on nozzle/afterbody throttle-dependent pressure forces in T.F-17 scale model [AIAA FAPBB 75-1295] A76-10282 Effects of jet exhaust gas properties on exhaust simulation and afterbody drag [HASA-TB-B-444] B76-10006 AFTBBBUBBIBG Air-cooled ground noise suppressor for afterburning engines using the Coanda effect [AIAA PAPEB 75-1328] 176-10289 Some reasons for crack formation in afterburner chamber shells A76-11895 AIB COOIIIG Air-cooled ground noise suppressor for afterburning engines using the Coanda effect [AHA PAEEB 75-1328] A76-10289 An exploratory investigation of the cooling drag associated with general aviation propulsive systems B76-11017 AIB FLOH Introduction to the aerodynamics of flight including aircraft stability, and hypersonic flight [BASA-SP-367] B76-11043 AIB IIXAKBS Poppet valve control of throat stability bypass to increase stable airflow range of a Hack 2.5. inlet with 60 percent internal contraction [BASA-TH-I-3297] B76-10004 AIB JETS Analysis of the flow field of cross blown lifting jets by flow field measurements [ESA-TT-165] N76-10071 AIB BAVIG1TIOB 1 spiral guidance approach concept for commercial VTOl operations [H1S1-CB-132651] 876-10140 AIB TBABSPOBTATIOB International air transportation; Proceedings of the Conference, San Francisco, Calif., Harch 24-26, 1975 A76-10389 The airlines' prospect after the 1974 energy crisis A76-10390 The effect of the energy crisis on economic regulation of the air transport industry A76-10392 Beview of BAS1 short-haul studies 176-10393 Canadian experience with short haul air transport 176-10394 Rake vortex program status 176-10399 Systems engineering and air transport 176-12154 AIBBOBHE/SPACBBOBHB COHPOfBBS Status of a digital integrated propulsion/flight control system for the YF-12 airplane [AIAA PAPBB 75-1180] A76-10252 A-2 SUBJECT IHDEZ AIBCBAFT BSGIBBS AIBCBAFT Estimation of cruise range: Propeller-driven aircraft [ESDO-75018] B76-11077 AIBCBAFT ACCIDBlt IBVISTIGATIOB The safety of flight operations A76-12156 AIBCBAFT 1CCIDEIIS Trailing vortex takes /First Society Anglo-Dutch Exchange Lecture/ 476-11621 Flight safety: Bibliography, 1968 - 1971 [TDCK-65616] B76-11068 AIECBAFT APPBOACB SEACIIG Trailing vortex Hakes /First Society Anglo-Dutch Exchange lecture/ A76-11621 AIBCBAFT BBAKES Aircraft stopping systems A76-10556 AIBCBiFT COIPIGOBATIOSS Indicial compressible potential aerodynamics aronnd complex aircraft configurations 876-10047 Proceedings of the RASA, Industry, University General Aviation Drag Reduction lorkshop [BASA-CB-145627] B76-10997 General overview of drag H76-10998 Prospects and tine tables for analytical estimation of the drag of complete aircraft configuration H76-10999 Drag reduction: Back to basics H76-11002 Propeller blockage research needs B76-11004 Installation drag considerations as related to turboprop and turbofan engines B76-11015 Seduction of trimmed drag H76-11020 Drag of the complete configuration aerodynamic considerations, 2 1176-11023 Problems in propulsion system integration N76-11025 Propulsion airframe integration H76-11026 Himnua vertical tail drag 1176-11029 AIBCBiFT COBTBOI Development of an integrated propulsion control system for fighter aircraft [AIAA PAPEB 75-1178] 176-10251 Status of a digital integrated propulsion/flight control system for the IF-12 airplane [AIAA PAPEB 75-1180] A76-10252 The CCV concept Control Configured Vehicle A76-11660 Oniversal system for loading the control elements of flight simulators A76-12487 A passive gust alleviation system for a light aircraft [BASA-CB-2605] B76-10002 Development of helicopter flight path models utilizing modern control techniques B76-10138 Explicit form of the optimal piloting lav of a rigid aircraft flying in turbulence aircraft control B76-10983 Control configured vehicles (CCV) [ESA-TT-164] B76-11081 Control technology aspects of aircraft »ith artificial stability (CCT) with particular respect to handling under maneuver loading B76-11082 Flight-determined stability and control derivatives for an executive jet transport control stability/control equipment - maximum likelihood estimates [BASA-TH-I-56034] H76-11105 AIHCBAFT DBSIGI Hybrid upper surface blown flap propulsive-lift concept for the Quiet Short-Baal Besearch Aircraft (AIAA PAPEB 75-1220] A76-10264 Propulsion system and airfrane structural integration analysis CAIAA PAPEB 75-1310] A76-10286 Investigation of non-symmetric two-dimensional nozzles installed in twin-engine tactical aircraft C A I A A PAPEB 75-1319] A76-10288 International air transportation; Proceedings of the Conference, San Francisco, Calif., Harch 24-26. 1975 A76-10389 The 197<1 energy crisis - A perspective - The effect on commercial aircraft design A76-10391 Beview of BASA short-haul studies A76-10393 Beducing the impact of aircraft noise - An airport viewpoint A76-10397 The Dolphin airship with undulating drive - Ondulators with rigid or elastic blade with different nndnlator diameter at rest and during circular running A76-10845 Concorde now /The sholto Douglas Hemorial Lecture/ development testing and prognosis for implenentation A76-11100 Dassault-Breguet - From the Hercure-100 to the Hercure-200. I twin-jet transport aircraft design A76-11134 The CCV concept Control Configured Vehicle A76-11660 Hanging gliders - Theory and practice. I A76-11897 Aerodynamic design consideration for maneuverability A76-11972 Airline profit pinch clouds harvest of gains lower-cost fuel-efficient transport technology A76-12159 Builders vie for short/medium market transport aircraft design A76-12160 Short-haul designs include trade-offs A76-12161 Towards hypersonics civil and military flight A76-12300 The airship - Phoenix or Dodo 476-12500 The present outlook for aerostatic techniques A76-12516 Bultivariate Analysis, Retrieval, and Storage system (HABS). Volume 1: BABS system and analysis techniques [BASA-CB-137671] B76-10089 Hultivariate Analysis, Betrieval, and Storage system (HABS). Volume 6: HABS system; a sample problem (gross weight of subsonic transports) [HASA-CB-137722] B76-10091 Study of flatter related computational procedures for minimum weight structural sizing of advanced aircraft, supplemental data [BASA-CB-132722] B76-10094 Aircraft design reference data for expeditionary airfields [AD-A011447] B76-10157 Overview of external nacelle drag and interference drag H76-11014 Cost consideration for aircraft configuration changes, 1 B76-11022 Possible applications of soaring technology to drag reduction in powered ganeral aviation aircraft 876-11028 Development of a computer program to obtain ordinates for BACA 4-digit, 4-digit modified, 5-digit, and 16 series airfoils [HASi-TH-X-3284] B76-11033 Fundamental research into the optimal design of a damper-stabilizer system with an elastic elevator B76-11084 AIBCBAFT EISIBBS Performance evaluation methods for the high-bypass-ratio turbofan [AIAA PAPEE 75-1206] 176-10258 A-3 AIBCBAFT BQDIPBEHT SUBJECT IHDEI An early glimpse at long-tera subsonic commercial tarbofan technolegy requirements fuel conservation [AIAA PAPEB 75-1207] A76-10259 Engine life cycle cost considerations daring the validation phase aircraft turbine engine [AIAA PAPEB 75-1289] A76-10279 Application of new development concepts to F101 engine for B-1 aircraft [AIAA PAPEB 75-1290] A76-10280 The F101-GE-100 engine structural design [AIAA PAPEB 75-1308] A76-10285 Thrust in aircraft powerplants A76-108<42 Airplane engine selection by optimization on surface fit approximations A76-11230 Compatibility analysis of turbojet engine and engine intake A76-1189U Statistical calculation and analysis for the logistics of engine reioval (SCALES) methodology aircraft maintenance [AD-A010824] H76-10137 Aircraft engines: Demand forecasting and inventory redistribution [AD-A011595] H76-10910 An exploratory investigation of the cooling drag associated with general aviation propulsive systems H76-11017 Development of a rotating cylinder deposition test [AD-A012298] H76-11103 AIBCBAFT ECOIPHEBT AAES failure modes and requirements for AIBIS interface [AE-A010550] H76-10122 AIBCBAFT FOE1 SYSTEBS Fuel cell pressure loading during hydraulic ram [AD-A012411] H76-11070 ilBCBiFT GOIEAHCB A spiral guidance approach concept for commercial VIOL operations [HASA-CB-132651] H76-101UO AIBCBAFT BYDBiOLIC SISTERS Aircraft stopping systems A76-10556 Aircraft power transfer units A76-10557 Hydraulic servicing - A manufacturer's view A76-10558 AIBCBAFT IBDOSTBY The revolution in production processes A76-10714 AIBCBAFT LABEIHG probabilistic evaluation of safe landing for a transport aircraft A76-11898 1IBCBAFT HAIBTEBABCE Econouc benefits of engine technology to commercial airline operators [AIAA PAPBB 75-1205] A76-10257 Bydranlic servicing - A manufacturer's view A76-10558 Basic concepts of a progressive maintenance system. II computerized aircraft maintenance A76-108U3 The asset »anagement approach to spares support for aircraft maintenance A76-12U98 US-IB assessment and comparative fleet evaluations [AD-A010781] H76-10121 Statistical calculation and analysis for the logistics of engine removal (SCA1EB) methodology aircraft maintenance [AD-A010824] B76-10137 Helicopter maintenance effectiveness analysis [AD-A012225] H76-11089 IlBCBiFT BABBOVBBS Transonic buffet response testing and control A76-103»1 Banging gliders - Theory and practice. I A76-11897 Control technology aspects of aircraft vith artificial stability (CCV) with particular respect to handling under maneuver loading H76-11082 AIBCBAFT HODEIS The development of theoretical models for jet-induced effects on V/STOL aircraft [AIAA PAPEB 75-1216] A76-10263 Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration. Volume 1: Experimental data report, base configuration and effects of wing twist and leading-edge configuration nind tunnel tests, aircraft models [HASA-CB-132727] S76-11034 Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration. Volume 2: Experimental data report, effects of control surface deflection wind tunnel tests - aircraft models [HASA-CB-132728] 876-11035 Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration. Volume 3: Data report, comparison of attached flow theories to experiment wind tunnel tests, aircraft models [HASi-CB-132729] B76-11036 Low speed aerodynamic characteristics of a transport model having 42.33 deg swept low wing with supercritical airfoil, double-slotted flaps, and T-tail or low tail [HASA-TH-X-3276] H76-11041 Bigh Beynolds number tests of a C-141A aircraft semispan model to investigate shock-induced separation boundary layer separation [HASA-CB-2604] B76-11078 AIBCBAFT BOISE HOISEXPO '15; National Boise and Vibration Control Conference, 3rd, Atlanta, Sa., April 30-Day 2, 1975, Proceedings of the Technical Program A76-10091 Application of the AICDZ concept to HAS Oceana, Virginia Beach, Virginia Air Installation Compatible Use Zone A76-10092 Community noise caused by small aircraft and noise of small aircraft in takeoff configuration A76-10094 Interior noise levels of two propeller driven light aircraft A76-10095 Beports of sleep interference and annoyance by aircraft noise 476-10096 Comparative noise and structural vibration levels from Concorde and subsonic aircraft A76-10097 Boise-con 75; Proceedings of the national Conference on Noise Control Engineering, Gaithersburg, Bd., September 15-17, 1975 A76-10318 Aircraft noise - A Government point of view A76-10320 NASA aircraft noise reduction research and technology program overview A76-10321 The USAF noise control program - An overview A76-10323 Seducing the impact of aircraft noise - An airline viewpoint A76-10396 Beducing the impact of aircraft noise - An airport viewpoint A76-10397 Duct liner optimization for tnrbomachinery noise sources aircraft noise/engine noise - numerical analysis [BASA-TB-X-72789] B76-11097 AIBCBAFT FABTS Titanium alloy castings for aircraft parts A76-10513 The evaluation of VBB 2A and VBB 3A glasses (Glaverbel-aecaniver S.A.) for aerospace applications [BBUB083] B76-11292 AIBCBAFT PEBFOBSABCB Effect of forebody shape and shielding technique on 2-D supersonic inlet performance [AIAA PAPEB 75-1183) A76-10253 Dassanlt-Breguet - From the Bercnre-100 to the Bercure-200. II civil transport aircraft specifications A76-11135 A-4 SUBJECT IHDEI AIBFOI1S propolsive effects doe to flight through turbulence A76-11233 Hilitarj cargo aircraft of the AHST program Advanced Bedim STOL Transport 476-11665 Simulation stody of aircraft handling daring engine failure A76-12486 Determination of the level flight performance of propeller-driven aircraft B76-11027 Estimation of cruise range: Propeller-driven aircraft CBSDO-75018] H76-11077 ilBCBiPt PEODDCTIOB The revolution in production processes 176-10714 AIBCBAFT SAPBTT The safety of flight operations A76-12156 Flight safety: Bibliography, 1968 - 1974[TDCIt-65616] B76-11068 AIBCBAPf SPECIFICATIONS Practical aerodynamics of the Iak-40 aircraft /2nd revised and enlarged edition/ Bnssian book 176-10307 Dassault-Eregaet - From the Hercare-100 to the Hercnre-200. II civil transport aircraft specifications A76-11135 Documentation of survivability/vnlnerability related aircraft military specifications and standards [AB-A011509] H76-10118 AIBCBAFT STABILITI Nonlinear relay nodel for post-stall oscillations A76-11228 The CCV concept Control Confignred Vehicle A76-11660 Flap-lag stability of helicopter rotor blades in forward flight A76-11771 Influence of sloshing in wing tip tanks on the vibration natural codes of an aircraft B76-10985 Introduction to the aerodynamics of flight including aircraft stability, and hypersonic flight [NASA-SP-367] B76-11043 Control technology aspects of aircraft with artificial stability (CCV) with particular respect to handling under maneuver loading B76-11082 Fundamental research into the optimal design of a damper-stabilizer system with an elastic elevator N76-11084 Development of a hydroflnidic stabilization augmentation system hysas for an AX class aircraft[AD-A011727] B76-11106 AIBCBAFT STBOCTOBES Technological progress in aircraft construction Russian book A76-10155 The fatigue substantiation of the lyni helicopter A76-10555 Building the B-1 graphite/epoxy slat A76-11570 Military cargo aircraft of the ABST program Advanced Hedium STOL Transport A76-11665 Pyrotechnic bonkers for the inflight testing of structures B76-10989 On the development of a unified theory for vortex flow phenomena fcr aeronautical applications [AD-A012399] H76-11396 A new device for the vibratory excitation of mechanical structures [ESA-TT-184] H76-11472 AIBCBAFI SDBVIVABIIITI Documentation of survivability/vnlnerability related aircraft military specifications and standards [AD-A011509] N76-10118 AIBCBAFT RAKES lake vortex program status A76-10399 Estimation of velocities and roll-up in aircraft vortex wakes A76-11229 Trailing vortex wakes /First Society Anglo-Dntch Exchange Lecture/ A76-11621 survey of computational methods for lift-generated wakes B76-10040 Dse of a pitot probe for determining wing section drag in flight B76-11010 Flow visualization of vortex interactions in multiple vortex wakes behind aircraft [BASA-TB-I-62459] B76-11030 An investigation of the increase in vortex induced rolling moment associated with landing gear wake [BASA-TH-I-72786] B76-11038 Bazard criteria for wake vortex encounters [BASA-TH-I-62473] B76-11069 AIBFOIL PBOFILES Becent developments in dynamic stall A76-10327 Separation and reattachment of the boundary layer on a symmetrical aerofoil oscillating at fixed incidence in a steady flow A76-10328 Experimental results for an airfoil with oscillating spoiler and flap A76-10329 Impulsive motion of an airfoil in a viscous fluid A76-10347 An experimental investigation of unsteady airfoil motion in a supersonic stream A76-10352 A simplified theory of oscillating airfoils in transonic flow A76-103S4 Some examples of unsteady transonic flows over airfoils A76-103S8 vibration characteristics of two types of subsonic profiles A76-10694 Aerodynamic profiles conformal mapping generation with several corner points A76-11097 Generalized similarity laws for flows past three-dimensional bodies A76-11540 Computerized procedures for airfoil design B76-10032 Dse of a pitot probe for determining wing section drag in flight H76-11010 Experimental studies of flow separation and stalling on two-dimensional airfoils at low speeds. Phase 2: Studies with Fowler flap extended [HASA-CB-145741] B76-11037 Study of viscous flow about airfoils by the integro-differential method [SASA-CB-145693] H76-11046 Aerodynamics of airfoils in transonic flow sweptback wings and shockfree flow calculation [ESA-TT-175] B76-11048 The calculation of supercritical flows round airfoils by the Hurman-Krupp difference method (DGLB-PAPBB-72-128] H76-11055 An analogue-analytical construction for supercritical flows round an airfoil electric potential flow [DG1B-PAPBB-72-129] H76-11056 Transonic airfoil theory: A critical comparison of various methods [DGLB-PAPE8-72-132] B76-11059 The transonic test-section for airfoil measurements in the Institute for Aerodynamics, Braunschweig [DGLB-PAPBB-72-133] B76-11060 AIBFOILS Effects of compressibility in unsteady airfoil lift theories A76-10353 Simulation of turbulent transonic separated flow over an airfoil computerized simulation H76-10021 A-5 AIBFBABI •HBBI1LS SUBJECT IBDBI Bnmerical solution of the Bavier-Stokes equations for arbitrary two-dimensional airfoils H76-10023 1 computer program for the analysis of Multielement airfoils in tvo-dieensional subsonic, viscous flow H76-10033 Application of numerical optimization techniques to airfoil design H76-10034 TSFOIL: 1 computer code for two-dimensional transonic calculations* including wind-tunnel wall effects and wave-drag evaluation H76-10035 numerical integration of the small-disturbance potential and Euler equations for unsteady transonic flow H76-10036 Process in application of direct elliptic solvers to transonic flow conputations B76-10038 Application of noltivariable search techniques to the optimization of airfoils in a low speed nonlinear inviscid flow field [NASA-CB-137760] H76-10062 Pressure data from a 614010 airfoil at transonic speeds in heavy gas media of ratio of specific heats from 1.67 to 1.12 [BASA-TB-X-62468] N76-10064 Some methods for reducing wing drag and wing-Hacelle interference H76-11008 Development of a computer program to obtain ordinates for HACA 4-digit. 4-digit modified, 5-digit, and 16 series airfoils [BASA-TH-X-3284] N76-11033 The prediction of airfoil distributions for snbcritical viscous flow and for supercritical inviscid flow [D6IH-PAPEB-72-131] H76-11058 AIBFBAHE HATEBIALS Evaluation of reinforced thermoplastic composites and adhesives [AD-A011407] 1176-11257 AIBFBAHES Propulsion system and airframe structural integration analysis [AIAA PAPEB 75-1310] A76-10286 Airplane engine selection by optimization on surface fit approximations A76-11230 Aerodynamic design consideration for maneuverability A76-11972 Propulsion airframe integration N76-11026 Reliability of step-lap bonded joints[AD-A012009] H76-11448 AIBLIHE OPIBATIOBS Economic benefits of engine technology to commercial airline operators[AIAA PAPEB 75-1205] A76-10257 The airlines' prospect after the 1974 energy crisis A76-10390 Beducing the impact of aircraft noise - An airline viewpoint A76-10396 Airline profit pinch clouds harvest of gains lower-cost fuel-efficient transport technology A76-12159 AIBFOBT PLAHBUG Reducing the impact of aircraft noise - An airline viewpoint A76-10396 Seducing the impact of aircraft noise - An airport viewpoint A76-10397 AIBPOBTS Community noise caused by small aircraft and noise of small aircraft in takeoff configuration A76-1009U Reports of sleep interference and annoyance by aircraft noise A76-10096 AIBSHIPS The Dolphin airship with undulating drive - Ondulators with rigid or elastic blade with different nndnlator diameter at rest and during circular running A76-108U5 The airship - Phoenix or Dodo A76-12500 The present outlook for aerostatic techniques A76-12516 AIALOS SIBDLATIOI An analogue-analytical construction for supercritical flows round an airfoil electric potential flow [DSLB-PAPEB-72-129] B76-11056 AHSLE Ot ATTACK Internal flow calculations for axisynmetric supersonic inlets at angle of attack [AIAA PAPEB 75-1214] A76-10262 Propulsive effects due to flight through turbulence A76-11233 AHTISKID DEVICES Aircraft stopping systems A76-10556 APPBOACB A spiral guidance approach concept for commercial VTOL operations [BASA-CB-132651] B76-10140 ABHOB window contoured glass/plastic transparent armor for the OH-1D helicopter performance tests [AD-A012215] B76-11087 ABBOB ilBGS Comparisons of theoretical and experimental pressure distributions on an arrow-wing configuration at transonic speed B76-10049 Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration. Volume 1: Experimental data report, base configuration and effects of wing twist and leading-edge configuration wind tunnel tests, aircraft models [NASA-CB-132727] 876-11034 Transonic pressure measurements and comparison of theory to experiment for an arrow- mng configuration. Volume 2: Experimental data report, effects of control surface deflection wind tunnel tests - aircraft models [BASA-CB-132728] B76-11035 Transonic pressure measurements and conparison of theory to experiment for an arrow-wing configuration. Volume 3: Data report, comparison of attached flow theories to experiment wind tunnel tests, aircraft models [BASA-CB-132729] B76-11036 ASPECT BATIO Investigation of non-symmetric two-dimensional nozzles installed in twin-engine tactical aircraft [AIAA PAPEB 75-1319] A76-10288 ASYMPTOTIC flBTHODS Asymptotic theory of two-dimensional trailing-edge flows 876-10015 Asymptotic analytical methods in fluid mechanics related to drag prediction H76-11006 ATHOSPHEBIC TDBBDLEHCE Explicit form of the optimal piloting law of a rigid aircraft flying in turbulence aircraft control H76-10983 ATTACK AIBCBAFT Acceptance rates and tooling capacity for selected military aircraft [AD-A011501] S76-10909 Aircraft gound test validation of a variable-response landing gear concept [AD-A011657] 876-11085 Development of a hydroflnidic stabilization augmentation system hysas for an AI class aircraft [AD-A011727] B76-11106 AOTOHATIC COBTBOL VALVES Poppet valve control of throat stability bypass to increase stable airflow range of a Bach 2.5. inlet with 60 percent internal contraction [HASA-TH-X-3297] 876-10004 AOTOHATIC TEST BQDIPHEBT New automatic fatigue test system for compressor blade A76-11132 AXIAL FLOB Bew automatic fatigue test system for compressor blade A76-11132 4-6 SUBJECT IHDBI CAHiED COBFI60BATIOBS Time-dependent transonic flow solutions for axial torbomachinery B76-10027 Internal and external axial corner flows H76-10029 IXIil FLOi TOBBIIES Optimum design of axial flow fans with cambered blades of constant thickness A76-12285 AIISIHHETBIC BODIES Investigation of non-symmetric two-dimensional nozzles installed in twin-engine tactical aircraft [AIAA PAPBB 75-1319] A76-10288 AIISISBETHIC FIOI Axisymmetnc transonic flow including »ind tunnel •all effects H76-10052 B B-1 AIBCBAFT Application of new development concepts to F101 engine for B-1 aircraft [ A I A A PAPEB 75-1290] A76-10280 Building the B-1 graphite/epoxy slat A76-11570 B-52 AIBCBAFT Flight flatter testing of multi-jet aircraft H76-10109 B-58 AIBCBiFT Flight flatter testing the B-58 airplane H76-10111 BIBLI06BAPHIBS Flight safety: Bibliography, 1968 - 1971 [TDCK-65616] 876-11068 BIP1ABES On aerodynamc coefficients of arbitrary biplane wing sections A76-10713 BLADE TIPS Design, fabrication and acoustic tests of a 36 inch (0.911 meter) statorless tarbotip fan [NASA-CB-2597] N76-10125 BLOCKIBG Calculation of the displacement correction (solid blocking) to r u m p and wing for arbitrary rectangular wind tunnels. Part 1: Theory [CH-6032-EMUEN] H76-10144 BLORDOiB ilHD TDHHE1S The transonic test-section for airfoil measurements in the Institute for Aerodynamics, Braunschweig [D6LB-PAPEB-72-133] H76-11060 BODY-UK AHD Till COlFIGOBiTIOBS Comparisons of theoretical and experimental pressure distributions on an arrow-wing configuration at transonic speed N76-10049 numerical modeling of tunnel-wall and body shape effects on transcnic flow over finite lifting wings B76-10050 Approximate method for calculating transonic flow about lifting wng body combinations B76-10054 General overview of drag H76-10998 Redaction of trimmed drag H76-11020 Trim drag in the light of Hunk's stagger theorea H76-11021 Transonic and supersonic wind tunnel tests on slender cruciform wing-body-tail configurations in different pitch and roll positions [FFA-TS-AD-988 ] H76-11061 BODI-8II6 COHFIGOB1XIOIS Calculation of the displacement correction (solid blocking) to r u m p and wing for arbitrary rectangular wind tunnels. Part 1: Theory [CB-6032-EBBEH] H76-1014U overview of external nacelle drag and interference drag H76-11014 Drag of the complete configuration aerodynamic considerations. 2 H76-11023 Unsteady pressure measurements on oscillating wing/body combinations. Comparison between theory and experiment [ESi-TT-189] H76-11065 Composite maneuver augmentation (COHHA) for fighter aircraft preliminary design study CAD-A011772] H76-11086 BOEIB6 747 AIBCBAFT HASA/FBC wake turbulence flight test program: Bide quality aspects [HASA-CB-145700] H76-11040 BOBBEB AIECBAPT Acceptance rates and tooling capacity for selected military aircraft [AD-A011501] H76-10909 BOUHDABY 1ATEB COBTB01 Internal flow calculations for axisymmetric supersonic inlets at angle of attack [AIAA PAPEB 75-1214] A76-10262 Design studies of transonic and STOL airfoils with active diffusion control [AD-A011928] H76-11088 BODBDABI IAIEB FLOS Unsteady aerodynamics; Proceedings of the Symposium, University of Arizona, Tucson, Ariz., Barch 18-20, 1975. Volumes 162 A76-10326 BOUHDAHY LAIEB SEPABATIOB Separation and reattachaent of the boundary layer on a symmetrical aerofoil oscillating at fixed incidence in a steady flow A76-10328 Vibration characteristics of two types of subsonic profiles A76-10694 High Beynolds number tests of a C-141A aircraft semispan model to investigate shock-induced separation boundary layer separation [HASA-CB-2604] H76-11078 BODHDABT LAIEB TBABSITIOH Theoretical investigation of transition phenomena in the boundary layer on an infinite sweptback wing [DGLB-PAPEB-72-124] N76-11051 BOUHDAHY »A1UB PBOBLBHS Boundary-integral equation method for three-dimensional elastic fracture mechanics analysis gas turbines - boundary value problems [4D-A011660] H76-10135 BDFFBTIBG Transonic buffet response testing and control 176-10341 Aerodynani.es of airfoils in transonic flow sweptback wings and shockfree flow calculation [ESi-TT-175] H76-11048 The calculation of the buffet boundary for sweptback wings at transonic flow [DG1B-PAPEB-72-123] B76-11050 BIPASSES Poppet valve control of throat stability bypass to increase stable airflow range of a Bach 2.5. inlet with 60 percent internal contraction [8ASA-TH-X-3297] H76-10004 C-5 AIBCBAFI Evaluation of the flying qualities requirements of HII-F-8785B ASG using the C-5A airplane [SD-A011728] H76-11092 C-135 AIBCBAFT Flight flutter testing of multi-jet aircraft H76-10109 C-141 AIBCBAFT High Beynolds number tests of a C-141A aircraft semispan model to investigate shock-induced separation boundary layer separation [HASA-CB-2604] B76-11078 CADBEB Optimum design of axial flow fans with cambered blades of constant thickness A76-12285 CABABD COIFIGUBATIOHS Aerodynamic characteristics of a tandem wing configuration of a Bach number of 0.30 [HASA-TH-X-72779] B76-10066 C1HBOH PIEEH BBIHPOBCZD PLASTICS SOBJBCX IHDBZ CABBOH FIBIB BBIHPOBCBD FUSTICS Building the B-1 graphite/epoxy slat A76-11570 CAB60 1IBCB1PT Military cargo aircraft of the AHST program Advanced fledini STOL Transport A76-11665 CASCADE FLOW Forces on uustaggered airfoil cascades in unsteady in-phase notion with applications to barsonic oscillation A76-10359 Subsonic flow past an oscillating cascade with steady blade loading - Basic formulation A76-10360 Experimental study of a supersonic blade array vith small deflection angle A76-11664 Optimum design of axial flow fans with cambered blades of constant thickness A76-12285 CAST ALLOTS Titanium alloy castings for aircraft parts A76-10513 CATBHABIBS Theoretical performance of cross-wind axis turbines with results for a catenary vertical axis configuration [HASA-TH-X-72662] H76-11032 CBSSHA AIBCBAFf A flight test determination of the static and dynamic longitudinal stability of the Cessna 310H aircraft [AD-A010795] B76-10141 CH-07 BBLICOPTBB Technology research at Boeing Tertol Company helicopter design A76-11622 Helicopter develop tent at Boeing Vertol Company A76-11623 CIVIL iVIATIOH Application of the AICDZ concept to DAS Cceana, Virginia Beach, Virginia Air Installation Compatible Use Zcne A76-10092 Botor burst protection program: Statistics on aircraft gas turbine engine rotor failures that occurred in OS commercial aviation during 1973 [HASA-CB-1318511] H76-11099 COAHDA EFFECT Air-cooled ground noise suppressor for afterburning engines using the Coanda effect [AIAA PAPEB 75-1328] A76-10289 COCKPIT SIBDLATOBS LBT - The training simulator for Concorde A76-10518 COBBAT Aerodynamic design consideration for maneuverability A76-11972 COBBOSTIOB CBA8BEBS Some reasons for crack formation in afterburner chamber shells A76-11895 Combustion generated noise in gas turbine combastors engine noise/noise reduction [BASA-CB-134843] H76-10123 Experimental clean combnstor program, phase 1 aircraft exhaust/gas analysis - gas turbine engines [BASA-CB-131736] N76-10124 Noise addendum experimental clean combustor program, phase 1 [BASA-CB-134820] B76-10128 COHBOSTIOH PBTSICS Combustion generated noise in gas turbine combnstors engine noise/noise reduction [HASA-CB-13Q843] H76-10123 COHBOSTIOI PBODOCTS Advanced low BO sat x combustors for supersonic high-altitude aircraft gas turbines [BASA-CB-1311889] B76-11098 COHBBBCIA1 AIBCB1FT An early glimpse at long-term subsonic commercial tnrbofan technolcgy requirements fuel conservation [AIAA PAPEB 75-1207] A76-10259 The 1974 energy crisis - A perspective - The effect on commercial aircraft design A76-10391 Fire-resistant aircraft materials development and evaluation program [PAPEB-70] 1176-11179 COHPLEI SXSTE0.S Systems engineering and air transport A76-12154 COHPOSITE HATEBIALS Flight service evaluation of Kevlar-49/epoxy composite panels in wide-bodied commercial transport aircraft [HASA-CB-132733] B76-10116 Prodncibility and serviceability of Kevlar-49 structures made on hot laynp tools [AD-A012265] B76-11095 Evaluation of reinforced thermoplastic composites and adhesives [AD-A011407] H76-11257 COHPOSIIE STBOCTOBES Building the B-1 graphite/epoxy slat A76-11570 Composite maneuver augmentation (COHBA) for fighter aircraft preliminary design study [AD-A011772] N76-11086 COBPBBSSIBILITY. EFFECTS Effects of compressibility in unsteady airfoil lift theories A76-10353 COHPBBSSIBIE BOOHDABT LAXEfi Theoretical investigation of transition phenomena in the boundary layer on an infinite sHeptback wing [DGLB-PAPEB-72-124] B76-11051 COHPBBSSIBLE FLO! Calculation of three-dimensional compressible laminar and turbulent boundary layers. Calculation of three-dimensional compressible boundary layers on arbitrary wings N76-10010 Indicial compressible potential aerodynamics around complex aircraft configurations B76-100U7 COBPBBSSOB BLADES Ben automatic fatigue test system for compressor blade A76-11132 Experimental study of a supersonic blade array mth small deflection angle A76-11664 COBPBESSOB BOTOBS Bedesigned rotor for a highly loaded, 1800 ft/sec tip speed compressor fan stage 1: Aerodynamic and mechanical design [BASA-CH-134835] B76-10133 COBPOIEB PBOGBABBIBG Calculation of the displacement correction (solid blocking) to rump and wing for arbitrary rectangular wind tunnels. Part 2: Program and results [CB-6032-EBBEH] B76-10145 COBPOTEB PB06BABS Transient airload computer analysis for simulating vind induced impulsive noise conditions of a hovering helicopter rotor [BASA-CB-137772] B76-10005 Time-dependent transonic flow solutions for axial tnrbomachinery B76-10027 A computer program for the analysis of multielement airfoils in two-dimensional subsonic, viscous flow B76-10033 TSFOIL: A computer code for two-dimensional transonic calculations, including wind-tunnel wall effects and wave-drag evaluation B76-10035 An integrated system for the aerodynamic design and analysis of supersonic aircraft B76-10046 Indicial compressible potential aerodynamics around complex aircraft configurations B76-10047 flultivariate Analysis, Betrieval, and storage system (DABS). Volume 1: HABS system and analysis technignes [BASA-CB-137671] B76-10089 Development of a computer program to obtain ordinates for BACA 4-digit, 4-digit modified, 5-digit, and 16 series airfoils [SASA-TB-X-3284] B76-11033 A-8 SOBJECT IBDBI COS1 1STIHATBS COBFOTEB T1CHIIQOBS Bnmeric calcalation of unsteady forces over thin pointed slogs in sonic flo« A76-10351 Basic concepts of a progressive maintenance system. II computerized aircraft maintenance A76-10843 Aerodynamic Analyses Begairing Advanced Computers, Part 1 [BASA-SE-347-PT-1] 1176-10007 Application of numerical optimization technignes to airfoil design H76-10034 Calculation of inviscid shear flov using a relaxation method for the Ealer equations B76-10037 Process in application of direct elliptic solvers to transonic flov computations H76-10038 Survey of conputational methods for lift-generated wakes 876-10010 Advanced panel-type influence coefficient methods applied to subsonic and supersonic flovs B76-10042 Some recent applications of the suction analogy to vortex-lift estimates B76-10043 A three-dinensional solution of flovs over vings vitb leading edge vortex separation B76-10044 Comparisons of theoretical and experimental pressure distributions on an arrov-ving configuration at transonic speed H76-10049 Axisymmetric transonic flov including Hind tunnel vail effects H76-10052 Approximate method for calculating transonic flov about lifting ving body combinations S76-10054 Application of nultivariable search techniques to the optimization of airfoils in a lov speed nonlinear inviscid flov field [BASA-CK-137760] B76-10062 COBPOTBBIZED DBSISH Dassault-Bregnet - From the Hercure-100 to the Bercnre-200. I t»in-Jet transport aircraft design A76-11134 Airplane engine selection by optimization on surface fit approximations A76-11230 Computerized procedures for airfoil design H76-10032 Application of numerical optimization techniques to airfoil design N76-10034 An integrated system for the aerodynamic design and analysis of supersonic aircraft N76-10046 COBPOTBBIZ2D SIBOLATICB Simulation of turbulent transonic separated flov over an airfoil computerized simulation B76-10021 COHCOBDE AIBCBAPT Comparative noise and structural vibration levels from Concorde and subsonic aircraft A76-10097 LHT - The training simulator for Concorde A76-10518 Concorde nov /The Sholto Douglas Memorial Lecture/ development testing and prognosis for implementation A76-11100 COBPEBEHCES BOISEXPO '75; National Boise and Vibration Control Conference, 3rd, Atlanta, Ga., April 30-Hay 2, 1975, Proceedings of the Technical Program A76-10091 Boise-con 75; Proceedings of the Bational Conference on Boise Control Engineering, Gaithersburg, Bd., September 15-17, 1S75 A76-10318 Unsteady aerodynamics; Proceedings of tbe Symposium, University of Arizona, Tucson, Ariz., Harch 18-20, 1S75. Volumes 162 A76-10326 International air transportation; Proceedings of the Conference, San Francisco, Calif., Barch 24-26, 1975 A76-10389 International Council of the Aeronautical Sciences, Congress, 9th, Haifa, Israel, August 25-30, 1974, Proceedings. Volume 1 - Fluid Dynamics, Aerodynamics and Gas Dynamics. Volume 2 - Structures, Baterials, Dynamics, Propulsion, Design, Boise and Pollution 476-11166 Aerodynamic Analyses Beguiring Advanced Computers, Part 1 CBASA-SP-347-PT-1] B76-10007 Flight Flutter Testing Symposium [BASA-SP-385] B76-10095 Proceedings of the BASA, Industry, University General Aviation Drag Bednction Workshop [BASA-CB-145627J B76-10997 Aerodynamics of airfoils in transonic flov sveptback vings and shockfree flov calculation [BSi-TT-175] B76-11048 Control configured vehicles (CCV) {ESA-TT-164] B76-11081 COBFOBHAL HAPPIIG On aerodynamic coefficients of arbitrary biplane ving sections A76-10713 Aerodynamic profiles conformal mapping generation vith several corner points A76-11097 COBTBOL COBFI60BBD VBBICLBS The CCV concept Control Configured Vehicle A76-11660 Control configured vehicles (CCV) [ESA-TT-164] B76-11081 Control technology aspects of aircraft vith artificial stability (CCV) vith particular respect to handling under maneuver loading B76-11082 Parametric investigation of longitudinal movement of CCV transport aircraft B76-11083 COBTBOL EODIPBEHT Flight-determined stability and control derivatives for an executive jet transport control stability/control equipment - maximum likelihood estimates [BASA-TB-X-56034] H76-11105 COBTBOL SIBOLATIOH Simulation study of aircraft handling during engine failure A76-12486 COBTBOL STABILITY Flight-determined stability and control derivatives for an executive jet transport control stability/control equipment - maximum likelihood estimates [BASA-TB-X-56034] B76-11105 COBTBOL STICKS Oniversal system for loading tbe control elements of flight simulators A76-12487 COBTBOL SOBPACES Transonic flight flutter tests of a control surface utilizing an impedance response technique B76-10114 COST ABALYSIS Estimating life-cycle costs: A case study of the A-7D [AD-A011643] H76-11915 COST BPFBCTIVBHBSS The 1974 energy crisis - A perspective - The effect on commercial aircraft design A76-10391 The effect of the energy crisis on economic regulation of the air transport industry A76-10392 Airline profit pinch clouds harvest of gains lover-cost fuel-efficient transport technology A76-12159 The airship - Phoenix or Dodo A76-12500 COST ESTIMATES Engine life cycle cost considerations during the validation phase aircraft turbine engine [AIAA PAPEB 75-1289] A76-10279 A-9 CB1CR IIITIATIOB SUBJECT IIDBI Cost consideration for aircraft configuration changes, 1 B76-11022 CHICK IBITIATIOI Some reasons for crack formation in afterburner chamber shells A76-11895 CBACKIBG (PBACTDBIB6) Joint aircraft loading/structure response statistics of tiie to service crack initiation [AD-A011646] H76-10120 CBABZS State of development and effectiveness of flying cranes in the GDB A76-10838 Prospective development of helicopter cranes for higher lead levels A76-10839 CBITBBIi Actual design criteria in mechanical engineering [ICAF-DOC-79«] H76-11440 CBOSS PLOW Analysis of the flew field of cross blown lifting jets by flow field measurements [BSA-IT-165] B76-10071 Theoretical perfornance of cross-Hind axis turbines with results for a catenary vertical axis configuration [BASA-TH-X-72662] H76-11032 CBOCIPOBB IIBGS Transonic and supersonic wind tunnel tests on slender cracifom wing-body-tail configurations in different pitch and roll positions [FFA-TB-AO-988] B76-11061 CBOISIB6 F1ISBT An economic study cf an advanced technology supersonic cruise vehicle [BASA-TB-X-62499] B76-10996 Estimation of cruise range: Propeller-driven aircraft [BSDD-75018] B76-11077 COBVBD PABBIS Advanced panel-type influence coefficient methods applied to subsonic and supersonic flows B76-10042 DASSAULT AIBCBAPT Dassault-Breguet - Fron the Bercure-100 to the Hercure-200. I twin-jet transport aircraft design A76-11134 Oassault-Ereguet - Prom the Bercure-100 to the Bercure-200. II civil transport aircraft specifications A76-11135 DATA BASES Hultivariate Analysis, Retrieval, and Storage system (USES). Volume 1: BABS system and analysis techniques [BAS4-CB-137671] H76-10089 Hultivariate Analysis, Betrieval, and Storage system (HABS). Volume 4: Turbojet and turbofan data base (by engine) [BASA-CB-137674] B76-10090 Bultivariate Analysis, Betrieval, and storage system (NABS). Volume 6: DABS system; a sample problem (gross weight of subsonic transports) [BASA-CB-137722] B76-10091 DATA BETBIEVAL Bultivariate Analysis, Betrieval, and Storage system (BASS). Volume 4: Turbojet and turbofan data base (by engine) [NASA-CB-137674] H76-10090 DATA STOBAGB Bultivariate Analysis, Betrieval, and storage system (BABS). Volume 4: Turbojet and turbofan data base (by engine) [HASA-CB-137674] H76-10090 DELTA BUGS Influence of the initial values on the camber, twist, planfori, and wave-drag coefficient of the absolutely optimum thin-section delta wing in supersonic flew A76-11868 On the effect of a strake on the flow field of a delta wing (lamda equals 2) at near-sonic velocities [DGLB-PAPEB-72-125] B76-11052 Improvement of maneuverability at high subsonic speeds fighter aircraft maneuverability improvement at high subsonic speeds by slotted and unslotted leading and trailing edge flaps on delta wing CDGLB-PAPBB-72-126] B76-11053 DIFPBBBHTIiL BQOATIOBS Study of viscous flow about airfoils by the integro-differential method [BASA-CB-145693] B76-11046 BIFPOSBBS Some methods for reducing wing drag and wing-Nacelle interference B76-11008 DIGITAL SXSTBBS Status of a digital integrated propulsion/flight control system for the IF-12 airplane [AIAA PAPBB 75-1180] A76-10252 DISPLAI DEVICES AAES failure modes and requirements for AIBIS interface [AD-A010550] B76-10122 DBAG BBASDBBBBHT Determination of the level flight performance of propeller-driven aircraft B76-11027 DBAG BBDOCTIOI Proceedings of the BASA, Industry, University General Aviation Drag Beduction Workshop [BASA-CB-145627] B76-10997 General overview of drag B76-10998 Summary of drag clean-up tests in MASA langley full-scale tunnel 876-11000 Drag reduction: Back to basics B76-11002 Some comments on fuselage drag B76-11003 Some methods for reducing wing drag and ving-Bacelle interference H76-11008 Drag reduction through higher ving loading B76-11009 Use of a pitot probe for determining wing section drag in flight H76-11010 King-tip vanes as vortex attenuation and induced drag reduction devices H76-11012 King tip vortex drag 1176-11013 Overview of external Nacelle drag and interference drag B76-11014 Installation drag considerations as related to turboprop and turbofan engines B76-11015 Bacelle drag reduction: An analytically-guided experimental program B76-11016 Propellers of minimum induced loss, and water tunnel tests of such a propeller B76-11018 Some comments on trim drag B76-11019 Seduction of trimmed drag H76-11020 Trim drag in the light of Bunk's stagger theorem H76-11021 Cost consideration for aircraft configuration changes, 1 B76-11022 Problems in propulsion system integration B76-11025 Propulsion airframe integration B76-11026 Binimum vertical tail drag B76-11029 DDCTS Duct liner optimization for turbomachinery noise sources aircraft noise/engine noise - numerical analysis [NASA-TB-X-72789] B76-11097 A-10 SOBJECT IBDBI EBTBOPT DIB1BIC BODBLS Estnation of velocities and roll-op in aircraft vortez wakes 176-11229 DYB1HIC STiBILITI Recent advances in techniques for dynamic stability testing at BIB 176-10330 DTB1HIC STBDCTOBAL 1B1IISIS FEOpulsion system and airfraae structural integration analysis [1111 PIPES 75-1310] 176-10286 In integrated systei for the aerodynamic design and analysis of supersonic aircraft 876-10046 B1BLY I1BBIBG SISTEBS High performance dash on warning air aobile, missile system intercontinental ballistic missiles - systeis analysis [B1S1-TH-X-62479] B76-10088 ECOBOHIC IBillSIS Econonic tenefits of engine technology to commercial airline operators [1111 P1PSB 75-1205] 176-10257 The airlines' prcspect after the 1974 energy crisis 176-10390 Review of NISI short-haul studies 176-10393 Canadian experience mth short haul air transport 176-10394 In economic study of an advanced technology supersonic cruise vehicle [B1S1-IB-X-62499] H76-10996 ECONOMIC P1CTOBS The effect of the energy crisis on economic regulation of the air transport industry 176-10392 Considerations concerning the economic and operational effectiveness of using helicopters in the electrification of railroads 176-10841 The economic impact of drag in general aviation H76-11007 EJECTOBS Discrete components in ejector noise and techniques for suppressing then 176-10241 EliCTBIC COBBEBT 11ES failure modes and requirements for 1IHIS interface [1D-1010550] B76-10122 ELECTHIPIC1IIOB Considerations concerning the economic and operational effectiveness of using helicopters in the electrification of railroads 176-10841 BLBCTBOB BOBBlBDBEBt Titanium alloy castings for aircraft parts 176-10513 BLECTBOBIC COBIB01 The evolution of turbojet control systems 176-11663 BLBV1TOBS (COHTB01 SOBP1CBS) Fundamental research into the optimal design of a damper-stabilizer system mth an elastic elevator H76-11084 B1IIPTIC DIHBBBBTIU EQ011IOBS Process in application of direct elliptic solvers to transonic flow computations H76-10038 In analogue-analytical construction for supercritical flews round an airfoil electric potential flov [DGLB-P1PEB-72-129] 876-11056 EIBB6I C01SBBV1II01 International air transportation: Proceedings of the conference, San Francisco, Calif., Harch 24-26, 1975 176-10389 The airlines' prospect after the 1974 energy crisis 176-10390 The 1974 energy crisis - 1 perspective - The effect on commercial aircraft design 176-10391 The effect of the energy crisis on economic regulation of the air transport industry 176-10392 BBSIBB COBfBOL Development of an integrated propulsion control system for fighter aircraft [1111 P1PEB 75-1178] 176-10251 Status of a digital integrated propulsion/flight control system for the YF-12 airplane [1111 F1PEB 75-1180] 176-10252 EBSIHE DESI6B Engine life cycle cost considerations during the validation phase aircraft turbine engine [1111 P1PEB 75-1289] 176-10279 Application of nev development concepts to F101 engine for B-1 aircraft [1111 PIPES 75-1290] 176-10280 The F101-GE-100 engine structural design [1111 P1PEB 75-1308] 176-10285 1 three-dimensional approach to the optimization of a gas turbine disc and blade attachment [1111 PIPES 75-1312] 176-10287 Airplane engine selection by optimization on surface fit approximations 176-11230 Study of variable cycle engines equipped with supersonic fans [B1S4-CS-134777] 876-10127 Problems in propulsion system integration 876-11025 Engine/transnission/airframe advanced integration techniques [1D-1012236] S76-11094 EBGIBB P1IIOBE Some reasons for crack formation in afterburner chamber shells 176-11895 Simulation study of aircraft handling during engine failure 176-12486 EBGIBE ISLETS Effect of forebody shape and shielding technique on 2-D supersonic inlet performance [1111 PIPES 75-1183] 176-10253 Unsteady flow phenomena causing weapons fire-aircraft engine inlet interference problems - Theory and experiments 176-10339 Compatibility analysis of turbojet engine and engine intake 176-11894 BB6IBB BOISE Interior noise levels of two propeller driven light aircraft 176-10095 Blade-wheel noise caused by random inhomogeneities of an incoming flow 176-10248 The Prop-Fan - 1 new look in propulsors [1111 PIPES 75-1208] 176-10260 lir-cooled ground noise suppressor for afterburning engines using the Coanda effect [1111 PIPES 75-1328] 176-10289 NISI aircraft noise reduction research and technology program overview 176-10321 Combustion generated noise in gas turbine combustors engine noise/noise reduction [B1S1-CB-134843] B76-10123 Noise addendum experimental clean combustor program, phase 1 [S1SA-CB-134820] 876-10128 Duct liner optimization for tnrbomachinery noise sources aircraft noise/engine noise - numerical analysis [B1S1-TH-X-72789] H76-11097 BBGIBB TESTS Economic benefits of engine technology to commercial airline operators [1111 PIPES 75-1205] 176-10257 Performance evaluation methods for the high-bypass-ratio tnrbofan [1111 PIPES 75-1206] 176-10258 BBTBOEI Besponse of a nozzle to an entropy disturbance Example of thermodynamically unsteady aerodynamics 176-10356 1-11 BBVIBOBBBBT EFFECTS SUBJECT IBDBX BBTIBOBBEHT EFFECTS Application of the AICOZ concept to HAS Oceana, Virginia Beach, Virginia iir Installation Compatible Dse Zcne A76-10092 Community noise caused by snail aircraft and noise of snail aircraft in takeoff configuration A76-10094 Reports of sleep interference and annoyance by aircraft noise A76-10096 Hoise-con 75; Proceedings of the National Conference on noise Control Engineering, Gaithersburg, Bd., September 15-17, 1975 A76-10318 The OSAF noise control program - An overview A76-10323 EBVIBOBBEBTA1 QDALITI H01SEIPO '75; Sational Hoise and Vibration Control Conference, 3rd, Atlanta, Ga., April 30-Hay 2, 1975, Proceedings of the Technical Progran A76-10091 EPOXT. BESIBS Flight service evaluation of Kevlar-49/epoxy composite panels in Hide-bodied commercial transport aircraft [NiSA-CB-132733] H76-10116 SQDIPBEBT SPECIFICATICBS Flight control system reliability and maintainability investigations [AD-A012233] H76-11107 BBEOB COBBICTIBG DEVICES Calculation of the displacement correction (solid blocking) to rump and ving for arbitrary rectangular vind tunnels. Part 2: Program and results [CH-6032-EHBES] H76-10145 ESIIHATES Trim drag in the light of Honk's stagger theorem B76-11021 ESTIHATIBG Prospects and tine tables for analytical estimation of the drag of complete aircraft configuration 576-10999 Propeller blockage research needs B76-11004 Learjet model 25 drag analysis N76-11024 BOIEB EQUATIONS OF BOTIOB Numerical integration of the small-disturbance potential and Euler eguations for unsteady transonic flov B76-10036 Calculation of inviscid shear flov using a relaxation method for the Baler equations H76-10037 EXBAOST FlOi SIHDLAIICH Effects of jet exhaust gas properties on exhaust simulation and afterbody drag [NASA-TB-B-144] H76-10006 numerical methods for the calculation of three-dimensional nozzle exhaust flov fields H76-10030 BXBADST 6ASBS Experimental clean combnstor program, phase 1 aircraft exhaust/gas analysis - gas turbine engines [NASA-CB-134736J N76-10124 EXBADS1 BOZZIBS Comparison of testing technigues for isolated axisymmetric exhaust nozzles in transonic flov [AIAA PAPBB 75-1292] A76-10281 Investigation of ncn-symmetric tvo-dimensional nozzles installed in tvin-engine tactical aircraft [AIAA PAPBB 75-1319] A76-10288 Bumerical methods for'the calculation of three-dimensional nozzle exhaust flov fields B76-10030 Thrust performance of isolated 36-chute suppressor plug nozzles vith and without ejectors at Bach numbers from 0 tc 0.45 [BASA-Tfl-X-3298] H76-10126 BIPEBIHEITAI DBSXGB The Sormovich experimental air cushion vehicle [AD-A012080] 876-11091 EXPBBIBBHTATIOI Experimental studies of flov separation and stalling on tvo-dimensional airfoils at lov speeds. Phase 2: Studies vith Fovler flap extended [HASA-CB-145741] M76-11037 BITEBHAI STOBES Overviev of external Bacelle drag and interference drag H76-11014 EXT2BBALLI BLOBB FLAPS Hybrid upper surface blovn flap propulsive-lift concept for the Quiet Short-Haul Besearch Aircraft [AIAA PAPEB 75-1220] A76-10264 F-17 AIBCBAFT Beynolds number effect on nozzle/afterbody throttle-dependent pressure forces in IF-17 scale model [AIAA PAPEB 75-1295] A76-10282 FABBICATIOB Building the B-1 graphite/epoxy slat A76-11570 FAILDBB BODBS AAES failure modes and requirements for AIBIS interface [AD-A010550] B76-10122 FATIGOB LIFE Determination of the fatigue life of structural elements during the inharmonic process of loading [AD-A007179] H76-10530 Beliability of step-lap bonded joints [AD-A012009] H76-11448 FATIGOB TESTIBS BACBIBES Hen automatic fatigue test system for compressor blade A76-11132 FATIGDE BESTS The fatigue substantiation of the Lynx helicopter A76-10555 FIGHTBB AIBCBAFT Transonic buffet response testing and control A76-10341 Summary of drag clean-up tests in NASA Langley full-scale tunnel H76-11000 Improvement of maneuverability at high subsonic speeds fighter aircraft maneuverability improvement at high subsonic speeds by slotted and nnslotted leading and trailing edge flaps on delta ving [DGLB-PAPEB-72-126] H76-11053 FIBITB DIFFEBBBCE IBBOBI Internal flov calculations for axisymmetric supersonic inlets at angle of attack [AIAA PAPBB 75-1214] A76-10262 Numerical solutions of the unsteady Navier-Stokes eguations for arbitrary bodies using boundary-fitted curvilinear coordinates A76-10346 Internal and external axial corner flovs N76-10029 The calculation of supercritical flovs round airfoils by the Hurman-Krupp difference method [DGLB-PAPEB-72-128] B76-11055 FIBITB ELBBBB1 BBTHOD A three-dimensional approach to the optimization of a gas turbine disc and blade attachment [AIAA PAPBB 75-1312] A76-10287 The numerical calculation of linearized subsonic flovs around vings by finite element method N76-10980 FIBE PBBVBBTIOH Fire-resistant aircraft materials development and evaluation program [PAPEB-70] B76-11179 FIXED ilNGS Numeric calculation of unsteady forces over thin pointed vings in sonic flov A76-10351 FLAPS (COB1BOL SOBFACBS) Experimental results for an airfoil vith oscillating spoiler and flap A76-10329 A-12 SUBJECT IBDBX FLO! STABILITY Aerodynamic characteristics of a large-scale hybrid tippet surface blovn flap model having four Engines [BASA-TB-I-62460] H76-10063 FIAT PI1TBS Effects of compressibility in unsteady airfoil lift theories 476-10353 Calculation of the pressure distribution induced by a jet on a flat plate [ESA-TT-159] H76-10068 Pi16HI CHABJCTBBISTICS Practical aerodynaiics of the Iak-40 aircraft /2nd revised and enlarged edition/ Bassian book A76-10307 Free-flight model investigation of a vertical-attitude 7TOL fighter vith tvin vertical tails IBASA-TB-D-8089] B76-11042 Introduction to the aerodynaaics of flight including aircraft stability, and hypersonic flight [BASA-SP-367] B76-11043 Evaluation of the flying qualities requirements of H11-P-8785B ASG osing the C-51 airplane [iD-4011728] H76-11092 FLIGHT COBTBOL Explicit fora of the optiial piloting lav of a rigid aircraft flying in turbulence aircraft control B76-10983 Control configured vehicles (CC7) [ESA-TT-164] B76-11081 Development of a hvdroflnidic stabilization augmentation system hysas for an IX class aircraft [AD-A011727] B76-11106 Flight control system reliability and Maintainability investigations [AE-A012233] S76-11107 FLIGHT GAZABOS Hazard criteria for Hake vortex encounters [BASA-TB-I-62473] H76-11069 FLIGHT BECBiHICS In-flight thrust vector control H76-10139 Introduction to the aerodynanics of flight including aircraft stability, and hypersonic flight [BASA-SP-367] H76-11043 FLIGHT PATHS Development of helicopter flight path models utilizing modern control tecbnigues B76-10138 PLIGHT SAFETY Probabilistic evaluation of safe landing for a transport aircraft A76-11898 The safety of flight operations A76-12156 FLIGHT SIBDLATIOB Simulation study of aircraft handling during engine failure A76-12486 An investigation of high-G aaneuvers of the AH-1G helicopter flight simulation/flight tests [AD-A012234] 876-11093 FLIGHT SIBOL1TOBS LBT - The training simulator for Concorde A76-10518 Universal systei for loading the control elements of flight sianlators A76-12187 FLIGHT STABILITY TESTS Flight-determined stability and control derivatives for an executive Jet transport control stability/control equipment - maximum likelihood estimates [BASA-TH-X-56031J M76-11105 FLIGHT TESTS Comparison of model and flight test data for an augmented jet flap STOL research aircraft [BASA-TB-I-62U91 ] H76-10093 Flight Flutter Testing Sy»posium [SiSA-SP-385] B76-10095 A theory of flight flutter testing B76-10096 In-flight damping Measurement H76-10098 A flight investigation of oscillating air forces: Equipment and technique H76-10101 Flight flutter testing using pulse techniques 876-10104 Stabilizer flatter investigated by flight test 876-10105 Flight flutter testing of the C6H 876-10107 Transient flight flutter test of a wing with tip tanks 876-10108 Flight flutter testing of inlti-jet aircraft B76-10109 Flight flutter testing of supersonic interceptors B76-10110 Flight flutter testing the B-S8 airplane H76-10111 Douglas experience in flight flutter testing 876-10112 Transonic flight flutter tests of a control surface utilizing an impedance response technique B76-10114 A flight test determination of the static and dynamic longitudinal stability of the Cessna 310H aircraft CAD-A010795] B76-10141 Pyrotechnic bonkers for the inflight testing of structures 876-10989 HASA/FBC Hake turbulence flight test progran: Bide quality aspects [BASA-CB-145700] B76-11040 Free-flight model investigation of a vertical-attitude VTOL fighter vith twin vertical tails [BASA-TB-D-8089] 876-11042 An investigation of high-G naneuvers of the AH-1G helicopter flight simulation/flight tests [AD-A012234] B76-11093 FLOS OISTOBTIOH Pious around accelerated, slender bodies for B less than, equal to, and greater than 1 A76-11870 Calculation of the displacement correction (solid blocking) to rump and wing for arbitrary rectangular vind tunnels. Part 1: Theory [CH-6032-EHHBH] S76-10110 Calculation of the displacement correction (solid blocking) to rump and wing for arbitrary rectangular wind tunnels. Part 2: Program and results [CB-6032-EHHEB] B76-10145 FLO! OISTBIBOTIOB On modeling aerodynamically induced nonlinear responses of self-excited structures A76-10342 Subsonic flov past an oscillating cascade with steady blade loading - Basic formulation A76-10360 Simulation of turbulent transonic separated flow over an airfoil computerized simulation B76-10021 Process in application of direct elliptic solvers to transonic flov computations 876-10038 Application of multivariable search techniques to the optimization of airfoils in a low speed nonlinear inviscid flow field CHASA-CB-137760] 876-10062 Analysis of the flov field of cross blown lifting jets by flov field measurements [ESA-TT-165] H76-10071 Propellers of minimum induced loss, and water tunnel tests of such a propeller 876-11018 On the effect of a strake on the flov field of a delta ving (lamda equals 2) at near-sonic velocities [DGLB-PiPEB-72-125] H76-11052 FLO! STABILITY. Becent advances in techniques for dynamic stability testing at BAB A76-10330 Some factors affecting the flov unsteadiness in supersonic intakes A76-10340 A-13 FlOi IBIOBI SUBJECT IHDBX TLOt TBEOBI 1 simplified theory of oscillating airfoils in transonic flov 176-10354 On lifting-line theory in unsteady aerodynamics 476-10357 Aerodynamic Analyses Requiring advanced Computers, Part 1 [BASA-SP-347-PT-1] S76-10007 Theoretical investigation of transition phenonena in the boundary layer on an infinite sveptback wing [DGLB-PAPBB-72-124] H76-11051 Transonic airfoil theory: A critical comparison of various methods [DGLB-PAPBB-72-132] H76-11059 FLOI fELOCITI Estimation of velocities and roll-np in aircraft vortex »akes 476-11229 PLOI VISU1LIZATIOH Flov visualization studies of the XFV-12A [AD-A010794] H76-10078 Flow visualization of vortex interactions in multiple vortex vakes behind aircraft [BASA-m-I-624E9] B76-11030 FXOTD DISAIICS On the development of a unified theory for vortex flov phenomena for aeronautical applications [1E-4012399] S76-11396 P10ID H2CH4IICS 4symptotic analytical methods in fluid mechanics related to drag prediction M76-11006 FLUID POBEH Aircraft pover transfer units 476-10557 FLDIDICS Time dependent fuel injectors [4IAA P4PEB 75-1305] 476-10284 PLDTTEB Flight Flutter Testing Symposium [HASA-SP-385] S76-10095 A theory of flight flutter testing H76-10096 A general aerodynamic approach to the problem of decaying or groving vibrations of thin, flexible vings with supersonic leading and trailing edges and no side edges B76-10097 In-flight damping measurement N76-10098 A flight investigation of oscillating air forces: Equipient and technigne H76-10101 Flight flutter testing using pulse techniques H76-10104 Stabilizer flutter investigated by flight test 876-10105 Flight flutter testing of the P6H H76-10107 Transient flight flutter test of a ving vith tip tanks B76-10108 Flight flatter testing of multi-jet aircraft B76-10109 Plight flutter testing of supersonic interceptors H76-10110 Flight flutter testing the B-58 airplane S76-10111 Douglas experience in flight flutter testing B76-10112 Transonic flight flutter tests of a control surface utilizing an impedance response technique B76-10114 FLOTTBB AI4LTSIS On modeling aerodynamically induced nonlinear responses of self-excited structures 476-10342 A method for analyzing the stability of a ving in flight 476-10701 Nonlinear relay model for post-stall oscillations A76-11228 Some problems in research on vhirl flutter in 7/STOL aircraft rotary vings and propellers [ESA-TT-160] B76-10069 Study of flutter related computational procedures for minimum veight structural sizing of advanced aircraft, supplemental data [HASA-CB-132722] 1176-10094 FOBEBODIES Effect of forebody shape and shielding technique on 2-D supersonic inlet performance [AIAA PAPEB 75-1183] A76-10253 FOBHXIG TBCBHIQOES Prodncibility and serviceability of Eevlar-49 structures made on hot laynp tools [AD-4012265] H76-11095 FBACTOBE BBCBASICS Boundary-integral equation method for three-dimensional elastic fracture mechanics analysis gas turbines - boundary value problems [4D-4011660] H76-10135 The fracture mechanics approach in structural design [ICAF-DOC-795] H76-11456 FBAGBEBTATIOI Botor burst protection program: Statistics on aircraft gas turbine engine rotor failures that occurred in US commercial aviation during 1973 [HASA-CB-134854] H76-11099 FBAHCE La Becherche Aerospatiale. Bimonthly Bulletin Mo. 1974-5 CBSA-TT-181] H76-10979 PBBB JETS Calculation of the pressure distribution induced by a jet on a flat plate [ES4-TT-159] 876-10068 FBEE HOLECOLAB PI01 Generalized similarity lavs for flovs past three-dimensional bodies 476-11540 FBEE VIBBATIOB A method for analyzing the stability of a ving in flight 476-10701 Influence of sloshing in ving tip tanks on the vibration natural modes of an aircraft H76-10985 FDEL CELLS POB4L-S, the analysis and design of a high altitude airship fuel cell povered, propeller driven tethered balloon [4D-4012292] H76-11090 FUEL COBSOBfTIOB An early glimpse at long-term subsonic commercial tnrbofan technology requirements fuel conservation [AIAA PAPEB 75-1207] A76-10259 The Prop-Fan - A nev look in propnlsors [AIAA PAPEB 75-1208] A76-10260 The airlines' prospect after the 1974 energy crisis 476-10390 The 1974 energy crisis - 4 perspective - The effect on commercial aircraft design 476-10391 Airline profit pinch clouds harvest of gains lover-cost fuel-efficient transport technology 476-12159 FDEL IHJECTIOB Time dependent fuel injectors [AI44 P4PEB 75-1305] 476-10284 FOBL T4HKS Fuel cell pressure loading during hydraulic ram [AD-A012411] B76-11070 FUSELAGES Some comments on fuselage drag H76-11003 GAS ABALISIS Experimental clean combustor program, phase 1 aircraft exhaust/gas analysis - gas turbine engines [BASA-CB-134736] B76-10124 GAS DIBASICS Flovs around accelerated, slender bodies for B less than, equal to, and greater than 1 A76-11870 GAS FLOI Unsteady transonic aerodynamics - An aeronautics challenge A76-10350 A-14 SOBJECT IBDBI HELICOPTEB PBBFOBBABCB Response of a nozzle to an entropy disturbance Example of thermcdynamically unsteady aerodynamics. A76-10356 The problem of flow uliog in a double-flov engine [NASA-TT-F-166Q8J H76-11100 GAS TDEBIBB BH6IBBS & three-dimensional approach to the optimization of a gas turbine disc and blade attachment [AliA PIPES 75-1312] A76-10287 Thrust in aircraft poverplants A76-10842 Coabnstion generated noise in gas tarbine combustors engine noise/noise redaction tNASA-CB-13 Concorde and subsonic aircraft A76-10097 An early glimpse at long-term subsonic commercial tnrbofan technolcgy requirements fuel conservation [AIAA PAPBB 75-1207] A76-10259 SOBSOBIC FLOi Effects of compressibility in unsteady airfoil lift theories A76-10353 A computer program for the analysis of multielement airfoils in two-dimensional subsonic, viscous flow H76-10033 Advanced panel-type influence coefficient methods applied to subsonic and supersonic flows H76-10042 The numerical calculation of linearized subsonic flows around wings by finite element method B76-10980 Certain problems of experimental aerodynamics [BASATTT-F-16565] B76-11031 SOBSOIIC FIOTfBB Subsonic flow past an oscillating cascade with steady blade loading - Basic formulation A76-10360 Vibration characteristics of two types of subsonic profiles A76-10694 SOBSOIIC SPB1D On the effect of a strake on the flow field of a delta wing (lamda equals 2) at near-sonic velocities [D8LB-PAPBB-72-125] B76-11052 Improvement of maneuverability at high subsonic speeds fighter aircraft maneuverability improvement at high subsonic speeds by slotted and nnslotted leading and trailing edge flaps on delta wing [DG1B-PAPBB-72-126] H76-11053 SOFEBCBRIC11 FlOB The calculation of supercritical flows round airfoils by the Inrman-Krapp difference method [DGLB-PAPBB-72-128] B76-11055 An analogue-analytical construction for supercritical flows round an airfoil electric potential flow [DG1B-PAPBB-72-129] H76-11056 The prediction of airfoil distributions for subcritical viscous flow and for supercritical inviscid flow [DG1B-PAPEB-72-131 ] 1176-11058 SOPEBCBITICAL iIHGS Computerized procedures for airfoil design 876-10032 Low speed aerodynamic characteristics of a transport model having 42.33 deg swept low wing with supercritical airfoil, double-slotted flaps, and I-tail or low tail [BASA-TH-X-3276] H76-11044 Besults on the use of shock-free transonic airfoils for transport aircraft [DGLB-PAPBB-72-130] 876-11057 Transonic airfoil theory: A critical comparison of various nethods [DG1B-PAPEB-72-132] H76-11059 Design studies of transonic and STOL airfoils with active diffusion control [AD-A011928] 876-11088 SDPEBSOHIC AIBCBAFT An integrated system for the aerodynamic design and analysis of supersonic aircraft 876-10046 Flight flutter testing of supersonic interceptors N76-10110 An economic study of an advanced technology supersonic cruise vehicle [NASA-TH-X-62499] B76-10996 Advanced low 80 sub x combnstors for supersonic high-altitude aircraft gas turbines [HASA-CB-134889] H76-11098 SOPBBSOBIC COBCBESSOBS Experimental study of a supersonic blade array with small deflection angle 476-11664 SOFEBSOBIC FLIGHT Flows around accelerated, slender bodies for H less than, equal to, and greater than 1 A76-11870 SOPEBSOBIC FIOB Influence of the initial values on the camber, twist, planform, and wave-drag coefficient of the absolutely optimum thin-section delta wing in supersonic flow A76-11868 Advanced panel-type influence coefficient methods applied to subsonic and supersonic flows 876-10042 Study of variable cycle .engines egnipped with supersonic fans [HASA-CB-134777] B76-10127 On the lifting problem of warped wings in supersonic flows tESA-TT-174] 876-11063 SOPBBSOBIC IHLBTS Effect of forebody shape and shielding technique on 2-D supersonic inlet performance IAIAA PAPEB 75-1183] A76-10253 Internal flow calculations for axisymmetric supersonic inlets at angle of attack [AIAA PAPEB 75-1214] A76-10262 Some factors affecting the flow unsteadiness in supersonic intakes A76-10340 An experimental investigation of unsteady airfoil motion in a supersonic stream A76-10352 A comparison of a shock-capturing technique with experimental data for three-dimensional internal flows 876-10028 SOPBBSOBIC JET BLOB Investigation of the aconstic characteristics of a supersonic jet flowing into a cylindrical tube A76-10250 SOPBBSOBIC TBABSPOBIS Besnlts OB the use of shock-free transonic airfoils for transport aircraft [DG1B-PAPEB-72-130] B76-11057 A-24 SOBJSCt IBDBX TIT1IIOB 1UOIS SOEBBSOHIC BUD TOH IB IS The transonic test-section for airfoil •easnreients in the Institute for Aerodynamics, Braunschweig [D6LB-P1PBB-72-133] H76-11060 SilPI 1IIS3 Besalts on the use of shock-free transonic airfoils for transport aircraft [DGLB-PAPEB-72-130] H76-11057 SBZPTBACK BUGS Aerodynamics of airfoils in transonic flov sweptback wings and shockfree flow calculation [ESA-TT-175] B76-11048 The calculation of the buffet boundary for sweptback wings at transonic flov [DGLB-PAPBB-72-123] H76-11050 Theoretical investigation of transition phenomena in the boundary layer on an infinite sveptback wing [DGLB-PAPBB-72-124] H76-11051 SISTERS 1B1LISIS High performance dash on varning air mobile, missile systea intercontinental ballistic missiles - systeis analysis [HASA-TH-X-62479] B76-10088 SISTZBS BHGIHBBBIBG Development of an integrated propulsion control system for fighter aircraft [Alia PiPBB 75-1178] 476-10251 Systeis engineering and air transport 176-12151 TAIL ASSEBB1IBS Trim drag in the light of Hunk's stagger theorem B76-11021 TAIL SOBF1CBS Binimnm vertical tail drag H76-11029 TAKEOFF BOBS Community noise caused by snail aircraft and noise of stall aircraft in takeoff configuration A76-10094 TABDEH ilHG AIBCBAFT Aerodynamic characteristics of a tandem ving configuration of a Bach number of 0.30 [HASA-TH-I-72779] H76-10066 TABGBI BBOHB AIBCBAH Composite maneuver augmentation (CCHB1) for fighter aircraft preliminary design study [AD-A011772] H76-11086 TECBB010GT ASSESSHBIt Technological progress in aircraft construction Russian bock A76-10155 The revolution in production processes A76-10714 Concorde now /The Sholto Douglas Memorial lecture/ development testing and prognosis for implementation A76-11100 The present outlook for aerostatic technigues A76-12516 TBCBBOLOGI TBABSFBB • Possible applicaticns of soaring technology to drag reduction in powered general aviation aircraft H76-11028 TECHHOLOGT DTILIZATIOI State of development and effectiveness of flying cranes in the GDB A76-10838 Prospective development of helicopter cranes for higher load levels A76-10839 Experience in the use of helicopters in industrial operations 476-10840 TETBBBBD BillOOHS FOBAL-S, the analysis and design of a high altitude airship fuel cell powered, propeller driven tethered balloon [AD-A012292] H76-11090 TBEBBODIBARIC CIC1ES Thrust in aircraft powerplants 476-10802 THBBBODIIABIC PBOPBBTIBS Besponse of a nozzle to an entropy disturbance Example of thermodynamically unsteady aerodynamics A76-10356 TBBBSOPJ.ASTIC BBSIBS Evaluation of reinforced thermoplastic composites and adhesives [AD-A011407] B76-11257 TBIB AIBFOILS Forces on onstaggered airfoil cascades in unsteady in-phase motion with applications to harmonic oscillation A76-10359 TBIB 8IB6S Hnmeric calculation of unsteady forces over thin pointed wings in sonic flov A76-10351 Influence of the initial values on the camber, tvist, planform, and wave-drag coefficient of the absolutely optimum thin-section delta wing in supersonic flow A76-11868 A general aerodynamic approach to the problem of decaying or growing vibrations of thin, flexible wings with supersonic leading and trailing edges and no side edges H76-10097 side-slipping airfoils in transonic flow wake vorticity of side-slipping slender thin wings at transonic speeds [DG1B-PAPBB-72-127] B76-11051 TBBBB DIBEBSIOB1L FLOB Calculation of three-dimensional compressible laminar and turbulent boundary layers. Calculation of three-dimensional compressible boundary layers on arbitrary wings B76-10010 A comparison of a shock-capturing technique with experimental data for three-dimensional internal flows H76-10028 numerical methods for the calculation of three-dimensional nozzle exhaust flov fields N76-10030 A three-dimensional solution of flows over wings with leading edge vortex separation B76-10044 IBEDST Propulsive effects due to flight through turbulence A76-11233 Thrust performance of isolated 36-chute suppressor plug nozzles with and without ejectors at Bach numbers from 0 to 0.45 [NASA-TH-I-3298] H76-10126 TBBOST AOGBEHTATIOB Experimental investigation of oscillatory jet-flow effects V/STOL aircraft A76-10343 Flow visualization studies of the IFV-12A CAD-A010794] N76-10078 TBBOST BBASOBBHEBT Thrust in aircraft poverplants A76-10842 The Dolphin airship vith undulating drive - Ondnlators vith rigid or elastic blade with different nndnlator diameter at rest and during circular running A76-10845 TBBOST TBCTOB C01TBOL In-flight thrust vector control H76-10139 1ILTIHG BOTOBS Optimal control alleviation of tilting proprotor gust response [8ASA-TH-X-62494] B76-10995 TIBB DBPBBDBBCE Time dependent fuel injectors [AIAA PAPEB 75-1305] A76-10284 Time-dependent transonic flov solutions for axial turbomachinery B76-10027 TIP SPEED Bedesigned rotor for a highly loaded, 1800 ft/sec tip speed compressor fan stage 1: Aerodynamic and mechanical design [HASA-CB-134835] 876-10133 TITABIOfl ALLOTS Titanium alloy castings for aircraft parts A76-10513 A-25 TOBSIOIU TIBBAHOI SUBJECT INDBI iOBSXOBU VIBBHXOB A Method for analyzing the stability of a ving in flight A76-10701 TOiBD BODIES Feasibility study of helicopter-towed air cushion logistic vehicles [ip-i011803] B76-11317 TBAILII6 BD6BS Asymptotic theory cf two-dimensional trailing-edge flows H76-10015 A general aerodynamic approach to the problem of decaying or growing vibrations of thin, flexible wings with supersonic leading and trailing edges and no side edges H76-10097 TB1ILIB6-BDG1 FLIPS Experimental studies of flow separation and stalling on two-dimensional airfoils at lov speeds. Phase 2: Studies mth Fouler flap extended [NJSA-CB-1PABIS, P. Computational aspects of the prediction of multidimensional transonic flons in tarbomachinery B76-10026 SPBBB. «. Actual design criteria in mechanical engineering [ICAF-DOC-794J S76-11

Aeronautical Engineering: A special bibliography with indexes, supplement 67, February 1976

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