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  • Chemistry  (17,814)
  • AERODYNAMICS  (805)
  • 1980-1984  (13,976)
  • 1960-1964  (4,643)
  • 1981  (7,224)
  • 1980  (6,752)
  • 1963  (4,643)
Collection
Keywords
Publisher
Years
  • 1980-1984  (13,976)
  • 1960-1964  (4,643)
Year
  • 1
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    The National and International Significance of the Lunar Exploration Program (1963)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Review of steps taken by nasa toward landing a man on the moon
    Keywords: AERODYNAMICS
    Type: Advancees in the Astronautical Sciences: Manned Lunar Flight; 10; 11-20
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    NASA TECHNICAL REPORTS
  • 2
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    Current developments lighter than air systems (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Lighter than air aircraft (LTA) developments and research in the United States and other countries are reviewed. The emphasis in the U.S. is on VTOL airships capable of heavy lift, and on long endurance types for coastal maritime patrol. Design concepts include hybrids which combine heavier than air and LTA components and characteristics. Research programs are concentrated on aerodynamics, flight dynamics, and control of hybrid types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84744 , NAS 1.15:84744
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  • 3
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    Experimental investigation of the flow on the suction side of a thin Delta wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Surface oil flow patterns were photographed and pressure distribution measurements were carried out on a sharp edged delta wing of aspect ratio lambda = 1.0 in order to determine the influence of Reynolds number and of vortex breakdown on the flow on the suction side of the wing. The formation of the secondary vortex occurs due to separation of a laminar boundary layer in the front part of the wing and due to separation of a turbulent boundary layer in the rear part of the wing. In the case of turbulent separation, the secondary separation line is closer to the wing leading edge than in the laminar case. The position of the transition depends on the Reynolds number and on the angle of incidence. The breakdown of a vortex above the wing leads to a kink in the secondary separation line.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75897
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  • 4
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    The influence of a high pressure gradient on unsteady velocity perturbations in the case of a turbulent supersonic flow (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The amplification or reduction of unsteady velocity perturbations under the influence of strong flow acceleration or deceleration was studied. Supersonic flows with large velocity, pressure gradients, and the conditions in which the velocity fluctuations depend on the action of the average gradients of pressure and velocity rather than turbulence, are described. Results are analyzed statistically and interpreted as a return to laminar process. It is shown that this return to laminar implies negative values in the turbulence production terms for kinetic energy. A simple geometrical representation of the Reynolds stress production is given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75236 , AAF-NT-79-10 , Colloq. d''Aerodynamique Appl.; Nov 07, 1978 - Nov 09, 1978; Marseille; France|Jul 01, 1979
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  • 5
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    Unsteady effects of a control surface in two dimensional subsonic and transonic flow (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The experimental results of steady and unsteady pressure measurements, carried out in subsonic and transonic flow on a 16 percent relative thickness supercritical aerofoil, equipped with a trailing edge flap involving 25 percent of the chord, in a sinusoidal motion are given. These experimental results are compared with those obtained by various methods of steady and unsteady inviscid flow calculations. Some calculation results in which viscous effects have been taken into account, for both steady and unsteady flows, are also presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75775 , AGARD-CP-262
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  • 6
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    On the swelling of rolled up vortex surfaces and the breakdown of the vortex core for slender wings (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Simplified models of the vortex distribution over cylindrical surfaces are developed. The effect of a change of vortex strength was analyzed quantitatively by menas of potential theory. The considerable bulging of the cylindrical vortex sheet as a consequence of the change of the vortex strength is discussed. The coiling-up of the vortices rotation in opposite directions over the cylindrical surface renders the condition for instability and the subsequent large spreading of the vortex core. These processes occur without a positive pressure gradient being necessary in the field of flow surrounding the coiled up vortex sheet.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75862
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  • 7
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    Investigations regarding the drag characteristics of flow-disturbing bodies which are arranged in line and attached to the wall (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The flow characteristics of rectangular bodies mounted on the base area of a rectangular closed wind tunnel are investigated. As many as four bodies are mounted in line with equal distances between successive bodies. The Mach number of the flowing air is in the range from 0.1 to 0.5. Total and individual drag values could be charged within a wide range by a suitable selection of the distance between successive bodies.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75788
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  • 8
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 3: Aerodynamics and Structures Session (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Advanced rotorcraft technology and tilt rotor aircraft were discussed. Rotorcraft performance, acoustics, and vibrations were discussed, as was the use of composite materials in rotorcraft structures. Rotorcraft aerodynamics, specifically the aerodynamic phenomena of a rotating and the aerodynamics of fuselages, was discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84147 , Dec 02, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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  • 9
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    The aerodynamics of small Reynolds numbers (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic characteristics of wing model gliders and bird wings in particular are discussed. Wind tunnel measurements and aerodynamics of small Reynolds numbers are enumerated. Airfoil behavior in the critical transition from laminar to turbulent boundary layer, which is more important to bird wing models than to large airplanes, was observed. Experimental results are provided, and an artificial bird wing is described.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75816 , Jahrbuch 1953 der Wiss. Ges. fuer Luftfahrt E. V. mit den Vortraegen der WGL-Tagung in Goettingen; May 26, 1953 - May 29, 1953; Braunschweig; Germany
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  • 10
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    Separation behavior of boundary layers on three-dimensional wings (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An inverse boundary layer procedure for calculating separated, turbulent boundary layers at infinitely long, crabbing wing was developed. The procedure was developed for calculating three dimensional, incompressible turbulent boundary layers was expanded to adiabatic, compressible flows. Example calculations with transsonic wings were made including viscose effects. In this case an approximated calculation method described for areas of separated, turbulent boundary layers, permitting calculation of this displacement thickness. The laminar boundary layer development was calculated with inclined ellipsoids.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75877
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  • 11
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    Study of the vortex conditions of wings with large sweepback by extrapolation of the Jones method (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The pockets of separation originating on the leading edges are surrounded by vortex sheets. Their configuration and intensity were determined by four conditions with the JONES approximation, which is itself corrected by a simple logic. Field pressures and stresses were computed for different cases and are compared with test results (pure deltas, swallow tails, truncations, strakes, ducks, fuselage).
    Keywords: AERODYNAMICS
    Type: NASA-TM-75863 , Symp. of Appl. Aerodynamics; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 12
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    Lee side flow for slender delta wings of finite thickness (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An experimental and theoretical investigation carried out to determine the lee side flow field over delta wings at supersonic speeds is presented. A theoretical method to described the flow field is described, where boundary conditions as a result of the experimental study are needed. The computed flow field with shock induced separation is satisfactory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75753 , ILR-23
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  • 13
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    A finite element method for the computation of transonic flow past airfoils (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A finite element method for the computation of the transonic flow with shocks past airfoils is presented using the artificial viscosity concept for the local supersonic regime. Generally, the classic element types do not meet the accuracy requirements of advanced numerical aerodynamics requiring special attention to the choice of an appropriate element. A series of computed pressure distributions exhibits the usefulness of the method.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75749 , MBB-UFE-1352-0
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  • 14
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    Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A numerically generated orthogonal coordinate system (with the body surface and shock wave as opposite boundaries) was applied with a time asymptotic method to obtain steady flow solutions for axisymmetric inviscid flow over several blunt bodies including spheres, paraboloids, ellipsoids, hyperboloids, hemisphere cylinders, spherically blunted cones, and a body with a concavity in the stagnation region. Comparisons with experimental data and with the results of other computational methods are discussed. The numerically generated orthogonal coordinate system is described and applications of the method to complex body shapes, particularly those with concave regions, are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1619 , L-13353
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  • 15
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 1: Executive Summary (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This presentation provides an overview of the NASA Rotorcraft Program as an introduction to the technical sessions of the Advanced Rotorcraft Technology Workshop. It deals with the basis for NASA's increasing emphasis on rotorcraft technology, NASA's research capabilities, recent program planning efforts, highlights of its 10-year plan and future directions and opportunities.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84149 , Dec 03, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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  • 16
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    Characteristics of Flow Past Fuselages and Wing-Fuselage Systems of Gliders (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The results are presented for visualization tests and measurements of the velocity field in diffusion regions (with a positive pressure gradient) for fuselages and transition regions between the wing and the fuselage. Wind tunnel and flight tests were performed. Specific emphasis was placed on examining the secondary flow influencing separation acceleration and the influence of the geometrical form of the wing fuselage system manifested by the occurrence of secondary flows of various types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75401
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  • 17
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    Discussion of test results in the design of laminar airfoils for competition gliders (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The deformation of flow in the boundary layer and the local separation of a laminar layer (laminar bubbles) from various airfoils were investigated. These phenomena were classified and their influence is discussed. Various aerodynamic characteristics are discussed and the principles for prescribing pressure distribution to attain a high value of c sub z max with a possibly low drag coefficient are described.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75402
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  • 18
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    Highly separated transonic flows (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Attention is given to the wind tunnel, to photographic visualization of the flow, and to measurements by pressure probes, hot wire anemometry and laser anemometry. The simultaneous use of different means of measurement provided a good description of the phenomenon, and indicated the existence of shocks and their stability, as well as the existence of the bubble, its dimensions, and in particular, the reattachment of its front. The results show that the bursting (or transition) of the bubble front is produced at an unstable position and creates a point of turbulent intensity which diffuses over the entire height of the flow.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75874 , NT80-18 , Colloq. Aerodyn. Appl.; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 19
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    Comparison of aerodynamic coefficients obtained from theoretical calculations wind tunnel tests and flight tests data reduction for the alpha jet aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods by which aerodynamic coefficients are determined and discussed. These include: calculations, wind tunnel experiments and experiments in flight for various prototypes of the Alpha Jet. A comparison of obtained results shows good correlation between expectations and in-flight test results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75237 , AGARD-CP-187 , Meeting of the Flight Mech. Panel; Jun 09, 1975 - Jun 13, 1975; Valloire; France
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  • 20
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    Boundary layer control by means of suction (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The process of boundary layer control by means of suction is described. Its historical development is briefly traced, and its application to airfoils and diffusers is discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75502
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  • 21
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 4: Flight Control Avionics Systems and Human Factors (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Helicopter user needs, technology requirements and status, and proposed research and development action are summarized. It is divided into three sections: flight dynamics and control; all weather operations; and human factors.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84146 , Dec 02, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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  • 22
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 2: Operators' Views (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: A special panel of helicopter users give presentations in 12 basic areas of helicopter applications. Development of the helicopter and the needs for future growth are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84148 , Dec 02, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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  • 23
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    Experimental investigation of a transonic potential flow around a symmetric airfoil (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Experimental flow investigations on smooth airfoils were done using numerical solutions for transonic airfoil streaming with shockless supersonic range. The experimental flow reproduced essential sections of the theoretically computed frictionless solution. Agreement is better in the expansion part of the of the flow than in the compression part. The flow was nearly stationary in the entire velocity range investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76676 , REPT-10/1971
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  • 24
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    Transonic small disturbances equation applied to the solution of two-dimensional nonsteady flows (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Transonic nonsteady flows are of large practical interest. Aeroelastic instability prediction, control figured vehicle techniques or rotary wings in forward flight are some examples justifying the effort undertaken to improve knowledge of these problems is described. The numerical solution of these problems under the potential flow hypothesis is described. The use of an alternating direction implicit scheme allows the efficient resolution of the two dimensional transonic small perturbations equation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75795
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  • 25
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    Works on theory of flapping wing (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: It is shown mathematically that taking account of the boundary layer is the only way to develop a theory of flapping wings without violating the basic observations and mathematics of hydromechanics. A theory of thrust generation by flapping wings can be developed if the conventional downstream velocity discontinuity surface is replaced with the observed Karman type vortex streets behind a flapping wing. Experiments show that the direction of such vortices is the reverse of that of conventional Karman streets. The streets form by breakdown of the boundary layer. Detailed analysis of the movements of certain birds and insects during flight 'in place' is fully consistent with this theory of the lift, thrust and drag of flapping wings. Further directions for research into flight with flapping wings are indicated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75750
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  • 26
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    Transonic wing DFVLR-F4 as European test model (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: A transonic wing, the DFVLR-F4 was designed and tested as a model in European transonic wind tunnels and was found to give performance improvements over conventional wings. One reason for the improvement was the reduction of compression shocks in the transonic region as the result of improved wing design.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75752
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  • 27
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    Reduction of profile drag by blowing out through peg holes in areas of streamline separation bubbles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Streamline separation bubbles on aircraft profiles and fuselages were investigated. The additional drag was examined in relation to increased angle of incidence and unusually high wall sheer stress. A reduction of the separation bubble and a decrease in drag is obtained with pneumatic turbulators that blow ram air out of 0.6mm pilot tubes at a distance of 16 mm. The pneumatic models are implemented at various positions and are found to be effective after the position of separation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76603 , DGLR-80-103 , Symp. on Aerodynamischen Widerstand; Nov 25, 1980 - Nov 26, 1980; Cologne; Germany
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  • 28
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    The elaboration of a new family of helicopter blade profiles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An airfoil family of helicopter rotor blades was designed. Three airfoils with thickness to chord ratios of 12, 9, and 7% were designed. Their improved performance in two dimensional rotor mockup wind tunnel tests led to testing of the tapered blades on four bladed rotors in a wind tunnel and flight tests on the Dauphin series of helicopters, confirming the expected gains.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75907
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  • 29
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    An explanation of the instability of the free vortex cores occurring over delta winds with raised edges (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: By rolling up the surfaces of discontinuity originating from the leading edge of delta wings, free vortex cores are formed above the wing. In case of greater angles of incidence, the flow in these vortex cores shows an instability which abruptly produces strong turbulence. In the present paper an explanation is given of this instability being a "frictionless instability" of the vortex core flow by increasing helical interference vortices. The occurring vortex core flows are calculated and investigated for stability by means of a stability criterion concerning flows with helical streamlines given by H. Ludwieg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75861
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  • 30
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    Flow and Acoustic Properties of Low Reynolds Number Underexpanded Supersonic Jets (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Jet noise on underexpanded supersonic jets are studied with emphasis on determining the role played by large scale organized flow fluctuations in the flow and acoustic processes. The experimental conditions of the study were chosen as low Reynolds number (Re=8,000) Mach 1.4 and 2.1, and moderate Reynolds number (Re=68,000) Mach 1.6 underexpanded supersonic jets exhausting from convergent nozzles. At these chosen conditions, detailed experimental measurements were performed to improve the understanding of the flow and acoustic properties of underexpanded supersonic jets.
    Keywords: AERODYNAMICS
    Type: NASA-CR-169257 , NAS 1.26:169257
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  • 31
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    Three-dimensional separated flows past ground vehicles (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The separated flow past a thick body is calculated using a theoretical model based on a discrete wake-vortex representation. Rehbach's unsteady inviscid scheme (1977) was used in the three-dimensional analysis. The obstacle is represented by singularities, and the wake is modeled by vortex particles emitted at the separation line. Calculated results for an axisymmetric body are compared with flow visualization results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75899 , Colloq. d''Aerodynamique Appl.; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 32
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    Experimental study of the interaction between the wing of a subsonic aircraft and a nacelle of a high by-pass ratio engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The oncoming of a new generation of subsonic transport aircraft (with supercritical wing and high by-pass ratio turbofans) led to an experimental study of wing nacelle jet pylon interference in transonic flow. To this end, a test set-up was developed at the ONERA S3Ch wind tunnel. The nacelle models represent a turbofan by means of two compressed air jets. The scale is 1/18.5. The nacelles are fixed on a thrust balance measuring afterbody thrust and discharge coefficients. The wing is located between the sidewalls of the test section. Pressures are measured through 456 holes located on 8 airfoils. Drag coefficient of the wing is obtained by wake survey. The following parameters can vary (1) wing/nacelle position; (2) upstream Mach number (from 0.3 to 0.8); (3) jet pressure ratio; (4) with/without pylon and (5) type of nacelle. Wing nacelle interference can be studied by means of total thrust drag analysis as a functon of the various parameters. The test set-up is described and examples of results are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76606 , May 05, 1980 - May 07, 1980; Munich; Germany
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  • 33
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    Entry heating and thermal protection (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: The book provides a documentation of progress in entry heating and thermal protection as related to two very challenging and very dissimilar applications, viz., the Jovian atmospheric probe as a key element of the Galileo mission, and the Space Shuttle. The Jovian atmospheric probe presents what might be the ultimate challenge in terms of the severity of entry. Success of the Galileo probe depends upon a design based on computational analysis largely unverified by experiment. Topics of interest include methods for predicting off-stagnation-point flowfields for planetary entry probes, modeling of radiative heating in base region of Jovian entry probe, gas heating with pressure gradients for the Space Shuttle, external tank laminar and rarefied aeroheating, and a study of the aerothermal entry environment for the Galileo probe.
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 34
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    2nd Manned Space Flight Meeting (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Second manned space flight meeting
    Keywords: AERODYNAMICS
    Type: Manned Space Flight Meeting; Apr 22, 1963 - Apr 24, 1963; Dallas, TX; United States
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  • 35
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    Aeroelasticity matters: Some reflections on two decades of testing in the NASA Langley transonic dynamics tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Testing of wind-tunnel aeroelastic models is a well established, widely used means of studying flutter trends, validating theory and investigating flutter margins of safety of new vehicle designs. The Langley Transonic Dynamics Tunnel was designed specifically for work on dynamics and aeroelastic problems of aircraft and space vehicles. A cross section of aeroelastic research and testing in the facility since it became operational more than two decades ago is presented. Examples selected from a large store of experience illustrate the nature and purpose of some major areas of work performed in the tunnel. These areas include: specialized experimental techniques; development testing of new aircraft and launch vehicle designs; evaluation of proposed "fixes" to solve aeroelastic problems uncovered during development testing; study of unexpected aeroelastic phenomena (i.e., "surprises"); control of aeroelastic effects by active and passive means; and, finally, fundamental research involving measurement of unsteady pressures on oscillating wings and control surface.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83210 , Intern. Symp. on Aeroelasticity; 5-7 Oct. 1980 - 1 Oct. 1981; Nuremberg; Germany
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    Some observations on supersonic wing design (1980)
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    Publication Date: 2019-07-27
    Description: The paper presents a brief review on the development of supersonic wing design. Attention is given to linearized aerodynamic theory, emphasizing equations for drag and ratios of slopes and Mach lines. Diagrams that depict conditions for minimum drag as well as the effects of fore-and-aft dimension of wings and Mach numbers on areas of lateral entrainment are presented.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-3040 , The evolution of aircraft wing design; March 18, 19, 1980; Dayton, OH
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    NASA research related to sailplane airfoils (1981)
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    Publication Date: 2019-07-13
    Description: The theoretical methods and experimental facilities at the NASA Langley Research Center have been employed to conduct investigations of sailplane airfoils. The unique and powerful capabilities of the Eppler Program have been used to design and analyze many airfoils and to smooth several Wortmann airfoils. Wind-tunnel investigations of two sailplane airfoils have been conducted in the Langley low-turbulence pressure tunnel. A procedure for sailplane performance improvement has been outlined.
    Keywords: AERODYNAMICS
    Type: National Convention; Jan 14, 1981 - Jan 18, 1981; Phoenix, AZ
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    Treatment of conical and nonconical supersonic flows by an implicit marching scheme applied to the full potential equation (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An aerodynamic prediction technique based on the full potential equation in conservation form is developed for the treatment of supersonic flows. This technique bridges the gap between simplistic linear theory methods and complex Euler solvers. A novel local density linearization concept and a second order accurate retarded density scheme, both producing the correct artificial viscosity, are introduced in developing an implicit marching scheme for solving the scalar potential. Results for conical flows over delta wings and a wing-body combination and for non-conical flows over bodies of revolution at angles of attack are compared with Euler and nonconservative full potential calculations and experimental data. The present formulation requires an order of magnitude less computer time and significantly less computer memory over Euler codes and exhibits a considerable improvement in computational efficiency and generality over an existing nonconservative full potential code.
    Keywords: AERODYNAMICS
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 39
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    Experimental and numerical studies of the incompressible viscous flow over a two-dimensional airfoil (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Physical and numerical experiments for the low Reynolds number flow over a two-dimensional NACA 66(3)-018 airfoil have been performed. Pressure distributions and smoke flow photographs have been obtained for a Reynolds number based on airfoil chord and free-stream conditions of approximately 40,000 at angles of attack of 0 and 6 deg, and for a Reynolds number based on airfoil chord and free-stream conditions of approximately 400,000 at angles of attack of 0 and 12 deg in a low turbulence wind tunnel. Finite difference numerical experiments, using an approximate factorization method, have been obtained for a Reynolds number of 40,000 at angles of attack of 0 and 6 deg. Although the comparison of the wind tunnel and computer results is encouraging, further studies of this type are clearly necessary.
    Keywords: AERODYNAMICS
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 40
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    Numerical simulation of reentry flow around the Shuttle Orbiter including real gas effects (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The flight environment of a reentry vehicle is predicted from the numerical solution of fluid dynamics equations for the region between the blunt nose and the swept wings. The inviscid portion of the shock layer is modeled by the Euler equations, but the laminar viscous flow adjacent to the wall is modeled by the approximate parabolic Navier-Stokes equations. The approximations made to the axial gradients of pressure and diffusive fluxes enable the coupled inviscid and viscous equations to be solved efficiently along the body axis. The equilibrium air aftbody code contains significant improvements over its predecessor which only considers a perfect gas model and noncircular configurations. The inclusion of numerical damping either explicitly or implicitly has extended its capabilities for predicting flow field around a winged configuration at higher Machs and greater angles of attack. The results are obtained on the cylindrical coordinates and satisfactory for the Shuttle Orbiter at a free-stream Mach number of 22 and an angle of attack of 40 deg. Also discussed are the inviscid formulation and its application for wind-tunnel conditions.
    Keywords: AERODYNAMICS
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 41
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    Analysis and computation of three-dimensional flow in strongly curved ducts (1981)
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    Publication Date: 2019-07-13
    Description: Numerical solutions are presented for three-dimensional laminar and turbulent flow in curved ducts of rectangular cross section and significant curvature. The analysis is based on a primary-secondary velocity decomposition in a given coordinate system, and leads to approximate governing equations which correct an a priori inviscid solution for viscous effects, secondary flows, total pressure distortion, heat transfer, and internal flow blockage and losses. Solution of the correction equations is accomplished as an initial-value problem in space using an implicit forward-marching technique. The overall solution procedure requires significantly less computational effort than Navier-Stokes algorithms. The present solution procedure is effective even with the extreme local mesh resolution which is necessary to resolve near-wall sublayer regions in turbulent flow calculations. Computed solutions for both laminar and turbulent flow compare very favorably with available analytical and experimental results.
    Keywords: AERODYNAMICS
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 42
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    Multigrid simulation of asymptotic curved-duct flows using a semi-implicit numerical technique (1981)
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    Publication Date: 2019-07-13
    Description: Asymptotic flows inside curved ducts of rectangular as well as polar cross section are analyzed using the Navier-Stokes equations in terms of the axial velocity and vorticity and the cross-flow stream function. Numerical solutions of the three second-order coupled elliptic partial differential equations governing this flow are obtained efficiently using the coupled alternating-direction implicit (ADI) method as well as the multigrid strongly-implicit (SI) scheme. For the flow configuration studied, the ADI method is found to be more sensitive to the time steps used than is the SI scheme. Use of the multigrid-coupled-strongly-implicit (MG-SI) scheme makes it possible to efficiently obtain fine-grid solutions for configurations having strong secondary flow. It is shown that, for this asymptotic curved-duct flow, the similarity parameter of significance is the Dean's number K rather than the Reynolds number Re. Results are obtained for curved ducts with square cross sections for K up to 900, which here corresponds to Re = 9,000 for this internal flow configuration.
    Keywords: AERODYNAMICS
    Type: Computers in flow predictions and fluid dynamics experiments; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 43
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    Longitudinal afterbody grooves and shoulder radiusing for low-speed bluff body drag reduction (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new low-speed drag reduction approach is proposed which employs longitudinal surface V-shaped grooves cutting through the afterbody shoulder region. The test Reynolds number range was from 20,000 to 200,000 based on undisturbed free-stream flow and a body diameter of 6.08 cm. The V-grooves are shown to be most effective in reducing drag when the afterbody shoulder radius is zero. Reductions in drag of up to 33% have been measured for this condition. For large shoulder radius, the grooves are only effective at the lower Reynolds numbers of the test.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 81-WA/FE-5 , Winter Annual Meeting; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 44
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    Mixed spectral/finite difference approximations for slightly viscous flows (1981)
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    Publication Date: 2019-07-13
    Description: A numerical scheme is presented, which employs a standard finite difference approximation for the viscous terms in high Reynolds number flows, and resorts to pseudo-spectral methods for the advection terms to greatly reduce the major source of numerical error without dramatically increasing computational cost. The spectral/finite difference (SFD) method evaluates the advection term and second-order differences to evaluate the diffusion term. The fully finite difference (FFD) method with second-order central differences on both terms is also used. The SFD method can handle strong shocks and can outperform the FFD method at moderate viscosity.
    Keywords: AERODYNAMICS
    Type: In: International Conference on Numerical Methods in Fluid Dynamics; Jun 23, 1980 - Jun 27, 1980; tanford; US
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  • 45
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    Direct numerical simulations of turbulent shear flows (1981)
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    Publication Date: 2019-07-13
    Description: Numerical simulations of wakes of axisymmetric bodies and of turbulent mixing layers are reported. The flows were assumed to be statistically homogeneous in the mean flow direction, in concert with experimental data and the self-similarity theorem. The nonlinear Navier-Stokes equations were solved by a pseudo-spectral numerical method using a 32 x 32 x 33 point grid and an algorithm for fast Fourier transforms and inverse transforms. Leapfrog time differencing was employed on nonlinear terms and time differencing on viscous terms. Towed wakes and wakes behind a self-propelled body were simulated, showing that the towed wakes exhibited a proper temporal behavior after an initial period of adjustment, including the development of a kurtosis near the wake edge, which is experimentally verifiable. The mixing-layer simulation displayed the laboratory demonstrated presence of large scale features such as vortex cores, while the lateral coherence was weak.
    Keywords: AERODYNAMICS
    Type: In: International Conference on Numerical Methods in Fluid Dynamics; Jun 23, 1980 - Jun 27, 1980; tanford; US
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    Trends and pacing items in computational aerodynamics (1981)
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    Publication Date: 2019-07-13
    Description: A perspective is presented of trends in computational aerodynamics, and of important technology development items that pace future advanced applications. From a survey of AIAA Journal papers published during the past two decades, the growth trends and the progressively increasing emphasis on code development for viscous, compressible, turbulent flow are illustrated. These trends are reflected in the chronology of introduction by the aerospace industry of new computational methods in aircraft design. Key pacing items outlined are: automatic grid generation for nonlinear inviscid computations; advanced computers, improved efficiency of numerical methods, and improved turbulence models for Reynolds-averaged Navier-Stokes computations; advanced computers, time-dependent three-dimensional law-of-the-wall, code development, improved efficiency of numerical methods, and improved subgrid-scale turbulence modeling for large eddy simulations.
    Keywords: AERODYNAMICS
    Type: In: International Conference on Numerical Methods in Fluid Dynamics; Jun 23, 1980 - Jun 27, 1980; tanford; US
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    International Conference on Numerical Methods in Fluid Dynamics, 7th, Stanford University, Stanford and Moffett Field, CA, June 23-27, 1980, Proceedings (1981)
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    Publication Date: 2019-07-13
    Description: Topics discussed include polygon transformations in fluid mechanics, computation of three-dimensional horseshoe vortex flow using the Navier-Stokes equations, an improved surface velocity method for transonic finite-volume solutions, transonic flow calculations with higher order finite elements, the numerical calculation of transonic axial turbomachinery flows, and the simultaneous solutions of inviscid flow and boundary layer at transonic speeds. Also considered are analytical solutions for the reflection of unsteady shock waves and relevant numerical tests, reformulation of the method of characteristics for multidimensional flows, direct numerical simulations of turbulent shear flows, the stability and separation of freely interacting boundary layers, computational models of convective motions at fluid interfaces, viscous transonic flow over airfoils, and mixed spectral/finite difference approximations for slightly viscous flows.
    Keywords: AERODYNAMICS
    Type: International Conference on Numerical Methods in Fluid Dynamics; Jun 23, 1980 - Jun 27, 1980; tanford; US
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  • 48
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    Conditional sampling technique to test the applicability of the Taylor hypothesis for the large-scale coherent structures (1980)
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    Publication Date: 2019-07-13
    Description: Comparisons of the distributions of large scale structures in turbulent flow with distributions based on time dependent signals from stationary probes and the Taylor hypothesis are presented. The study investigated an area in the near field of a 7.62 cm circular air jet at a Re of 32,000, specifically having coherent structures through small-amplitude controlled excitation and stable vortex pairing in the jet column mode. Hot-wire and X-wire anemometry were employed to establish phase averaged spatial distributions of longitudinal and lateral velocities, coherent Reynolds stress and vorticity, background turbulent intensities, streamlines and pseudo-stream functions. The Taylor hypothesis was used to calculate spatial distributions of the phase-averaged properties, with results indicating that the usage of the local time-average velocity or streamwise velocity produces large distortions.
    Keywords: AERODYNAMICS
    Type: In: EUROMECH 132; Colloquium on Hot-Wire, Hot-Film Anemometry and Conditional Measurements; Jul 02, 1980 - Jul 04, 1980; Rhone; France
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    Flow visualization using a computerized data acquisition system (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A computer-driven traversing mechanism combined with mass data storage, data reduction programs, and general-purpose graphics programs permits a visualization of complex flows. A unique seven-hole probe is used which permits reasonably accurate measurements of all average flow properties if the local flow angle does not exceed 80 degrees. A description is given of the wake of a lifting canard surface as this wake passes over a wing. The flow includes concentrated and dissipating vortices, large regions of reduced total pressure, and local flow angles up to 60 deg. All these features can be clearly seen and accurately located in the graphical output.
    Keywords: AERODYNAMICS
    Type: In: International Symposium on Flow Visualization; Sep 09, 1980 - Sep 12, 1980; Bochum
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    An experimental study of separated flow on a finite wing (1981)
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    Publication Date: 2019-07-13
    Description: The flow field associated with the formation of a mushroom shaped trailing edge stall cell on a low-aspect-ratio (AR = 4.0) wing was investigated in a series of low speed wind tunnel tests (Reynolds number based on 15.2 cm chord = 480,000). Flow field surveys of the separation bubble and wake of a partially stalled and fully stalled wing were completed using a hot-wire probe, a split-film probe, and a directional sensitive pressure probe. A new color video display technique was developed to display the flow field survey data. Photographs were obtained of surface oil flow patterns and smoke flow visualization
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1882 , Atmospheric Flight Mechanics Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
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    Interaction of compressor rotor blade wake with wall boundary layer/vortex in the end-wall region (1981)
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    Publication Date: 2019-07-13
    Description: This paper reports the experimental study of the three-dimensional characteristics of the mean velocity of the rotor wake inside the annulus- and hub-wall boundary layers. The measurements were taken with a rotating three-sensor hot wire behind the rotor. This set of measurements probably represents the first set of comprehensive measurements taken inside the annulus- and hub-wall boundary layers. The wake was surveyed at several radial locations inside the boundary layer region and at several axial locations. Interaction of the wake with the annulus-wall boundary layer, secondary flow, tip-leakage flow, and the trailing vortex system results in slower decay and larger width of the wake. The presence of a strong vortex and its merger with the wake is also observed. The end-wall boundary layers and the secondary flow were found to have a substantial effect on both the decay characteristics and the profile of the wake. These and other measurements are reported and interpreted in this paper.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 81-GR/GT-1 , International Symposium on Applications of Fluids Mechanics and Heat Transfer to Energy and Environmental Problems, University of Patras; Jun 29, 1981 - Jul 03, 1981; Patras; Greece
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    Airframe effects on top-mounted inlet systems for VSTOL fighter aircraft (1981)
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    Publication Date: 2019-07-13
    Description: Inlet flow-field and compressor-face performance data were obtained for a 0.095-scale model of a VSTOL fighter-attack aircraft configuration with twin top-mounted inlets. Tests were conducted at Mach numbers from 0.6 to 2.0 and at angles of attack and sideslip up to 27 deg and 12 deg, respectively. The effects of inlet location, wing leading-edge extension planform area, canopy-dorsal integration, and variable incidence canards were determined. The results show that distortion at the compressor face when maneuvering is relatively low (20% or less) at Mach numbers up to 0.9. However, at Mach numbers of 1.2 and above, maneuverability may be restricted because of high distortion or low pressure recovery (80% or less) or both.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2631 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
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    Low speed testing of the inlets designed for a tandem-fan V/STOL nacelle (1981)
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    Publication Date: 2019-07-13
    Description: An approximately 0.25 scale model of a tandem fan nacelle, designed for a subsonic V/STOL aircraft, was tested in a Lewis wind tunnel. Model variables included long and short aft inlet cowls and the addition of exterior strakes to the short inlet cowl. Inlet pressure recoveries and distortion were measured at pitch angles to 40 deg and at combinations of pitch and yaw to 30 deg. Airspeeds covered a range to 135 knots (69 m/sec). The short aft inlet with added strakes had the best aerodynamic performance and is considered suitable for the intended V/STOL application.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2627 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
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    Analysis of data from a wind tunnel investigation of a large-scale model of a highly maneuverable supersonic V/STOL fighter - STOL configuration (1981)
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    Publication Date: 2019-07-13
    Description: The surface pressure and thermal characteristics of a large-scale model of a highly maneuverable supersonic fighter with STOL capability are described. The 7.28 m span model is powered by two J-97 turbojets, operated at 9340 N thrust. It combines upper-surface and spanwise blowing to augment the lift characteristics over a wide angle-of-attack range. The most significant feature of the fighter's flow field is the leading edge vortex that forms at low alphas, grows stronger, and moves inboard as alpha is increased. Upper surface blowing enhanced the lift on the wing in both stalled and unstalled areas significantly, while generating only a modest aft shift in the center of pressure. Lift gains were greatest at high alphas and with the flap deflected. Spanwise blowing was most significant at angles-of-attack greater than 8 deg, when the jet strengthened the vortex. The 1100 F spanwise blowing jet mixed very rapidly with the wing flow field, creating a maximum temperature rise of only 300-350 F. A comparison of small-scale and large-scale model wing pressure characteristics showed similar trends created by upper surface blowing, while spanwise blowing characteristics differed considerably. Force data correlated well with semi-empirical predictions for gross thrust coefficients less than 1.0.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2620 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
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    Finite element analyses of plane thermal entry-length flows (1981)
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    Publication Date: 2019-07-13
    Description: It is pointed out that the design of actively cooled engine and airframe structures for hypersonic flight requires strong interaction between fluid, thermal, and structural analyses. Research programs are being conducted to develop an integrated thermal-structural analysis capability based upon the finite element method. In connection with these programs, a finite element engineering approach has been developed based upon a number of assumptions customarily used in practical heat transfer analysis. An evaluation is conducted of the finite element engineering approach for entry-length flows. The evaluation makes use of an analysis of plane thermal entry-length flows by a finite element approach utilizing mean fluid temperatures with a convection coefficient. Another analysis is based on a finite element continuum approach, taking into account the rigorous momentum, mass, and energy equations of viscous, incompressible flow. The engineering approach was found to give excellent agreement with the rigorous continuum approach for Peclet number values not less than 100.
    Keywords: AERODYNAMICS
    Type: In: International Conference on Finite Elements in Flow Problems; Jun 10, 1980 - Jun 13, 1980; Alberta; Canada
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    An experimental study of the flow in a wing with a partial span drooped leading edge (1981)
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    Publication Date: 2019-07-13
    Description: The flow field produced by a low aspect ratio wing (AR = 3.0) with a partial span leading edge droop was investigated in a series of low speed wind tunnel tests (Reynolds number based on 17.8 cm chord = 560,000). Photographs were obtained of surface oil flow patterns over an angle of attack range of alpha = 0 to 29 deg. Flow field surveys of the partially stalled wing at alpha = 25 deg were completed using a hot-wire probe, a split-film probe and a Conrad probe. The flow field survey data was presented using a color video display. The data indicated regions of apparent reversed flow in the separation region behind the wing and indicated the general cross-sectional shape of the separated wake flow.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1665 , American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Conference; Aug 11, 1981 - Aug 13, 1981; Dayton, OH
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    Development and validation of the V/STOL aerodynamics and stability and control manual (1981)
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    Publication Date: 2019-07-13
    Description: A V/STOL Aerodynamics and Stability and Control Manual was developed to provide prediction methods which are applicable to a wide range of V/STOL configurations in hover and transition flight, in and out of ground effect. Propulsion-induced effects have been combined with unpowered aerodynamics in a buildup of total forces and moments for the jet-lift concept, so that total aerodynamics can be used to predict aircraft stability, control, and flying qualities characteristics. Results of longitudinal aerodynamic predictions have been compared with test data, and indicate that the methods are fast, inexpensive, and within the desired accuracy for the objective preliminary design stage.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2611 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
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    Preflight reentry heat transfer analysis of Space Shuttle (1981)
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    Publication Date: 2019-07-13
    Description: Preflight predictions of the structural temperature distributions during entry are compared with data from the initial Shuttle flight. Finite element thermal analysis programming was used to model the heat flow on Shuttle structures and actual gas properties of air were employed in the analyses of aerodynamic heating. Laminar, separated, and turbulent heat fluxes were calculated for varying locations on the craft using velocity-attitude and angle-of-attack projections taken from the nominal STS-1 trajectory. Temperature time histories of the first flight are compared with laminar and turbulent flow assumptions and an unpredicted rapid cooling 1800 sec into entry is credited to inaccurate assumptions of structural heat dissipative properties or flow conditions in that time phase of the flight; additional discrepancies in descriptions of heating of the upper fuselage are attributed to a lack of knowledge of the complex flow patterns existing over that area of the Shuttle body.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2382 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
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    Propfan installation aerodynamics of a supercritical swept wing transport configuration (1981)
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    Publication Date: 2019-07-13
    Description: A semispan model with a powered propeller has been tested to provide data on the installation drag penalty of advanced propfan-powered transports designed to cruise at a Mach number of 0.8. These tests, conducted in 14-foot and 11-foot transonic wind tunnels, are a part of a NASA program to develop efficient, high-speed propellers for more fuel-efficient commercial transports for the 1990s and beyond. The model is instrumented for measuring propeller forces, wing/nacelle forces and moments, and pressure distributions over the wing and nacelle. The body in these tests was nonmetric, being connected to the wing by an RTV seal at the wing/body juncture. Tests were run at angles of attack from -3 to +5 deg over the Mach number range 0.6 to 0.85 at a Reynolds number of about 9,000,000. Results of these tests indicate that the nacelle interference drag can be quite large relative to an uninstalled nacelle. However, the losses due to the nacelle were reduced to acceptable levels by changes to the wing leading edge and nacelle intersection. The propeller slipstream causes substantial changes in the wing span load distribution indicating that twist modifications are needed to recover a more favorable span load distribution.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1563 , Joint Propulsion Conference; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO
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    Development of the ARIES parachute system (1981)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The design and testing of a two-stage parachute system to recover a space telescope weighing up to 2000 pounds is described. The system consists of a 15-ft dia ribbon parachute reefed to 50% for 10 seconds and a 73-ft dia paraform or cross second stage reefed to 10% for 10 seconds. The results of eight drop tests and one operational rocket launched flight and recovery are presented. A successful operational recovery of a 1600-lb NASA space telescope was conducted. The payload was launched by a second stage Minuteman rocket to an altitude of about 300 miles above sea level.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84082 , DE81-012161 , SAND-81-0208C , CONF-811002-1 , AIAA Aerodyn. Decelerator and Balloon Technol. Conf.; Oct 21, 1981 - Oct 23, 1981; San Diego, CA; United States
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  • 61
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    Correlation of transonic-cone Preston-tube data and skin friction (1981)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The distribution of Preston tube pressures within turbulent boundary layers along the surface of a sharp-nosed, ten degree cone was correlated with theoretical values of turbulent skin friction for freestream Mach numbers less than one. The mini-basic computer code, the Wu and Lock computer code, and the STAN-5 computer code were used to analyze the data and to solve the boundary layer conservation equations. The skin friction which results from using Preston tube pressures in the correlation equation, has a rms error of 1.125 percent. It was found that the effective center of the probe is not a constant but increases as the surface distance increases. For a specified unit Reynolds number, the effective center of the probe decreases as the Mach number increases. The variation of the fluid (air) properties across the face of the probe may be neglected for subsonic flows. The possible transverse errors caused by the use of the concept of a virtual origin for the turbulent boundary layer were investigated and found to be negligible.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165065
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    Computational methods for internal flows with emphasis on turbomachinery (1981)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Current computational methods for analyzing flows in turbomachinery and other related internal propulsion components are presented. The methods are divided into two classes. The inviscid methods deal specifically with turbomachinery applications. Viscous methods, deal with generalized duct flows as well as flows in turbomachinery passages. Inviscid methods are categorized into the potential, stream function, and Euler aproaches. Viscous methods are treated in terms of parabolic, partially parabolic, and elliptic procedures. Various grids used in association with these procedures are also discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-82764 , E-1085 , The ASME Winter Ann. Meeting; Nov 15, 1981 - Nov 20, 1981; Washington, DC; United States
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  • 63
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    Three-dimensional periodic disturbances acting upon airfoils in cascade (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A theory is developed for three-dimensional periodic gusts interacting with loaded airfoils. The unsteady disturbances are linearized with respect to the mean potential flow of the airfoils. The vorticity transport equation is then integrated analytically in a Lagrangian form. The vorticity vector shows strong variations in its magnitude and wavelength as it interacts with the flowfield of a lifting airfoil. The streamwise component of the vorticity increases significantly with flow acceleration and flow turning. For simplicity the rectangular fan approximation is used and a single Helmholtz-like equation is derived to characterize the unsteady 3D flowfield. This is a new and significant result. The present theory is first applied to symmetric airfoils.
    Keywords: AERODYNAMICS
    Type: International Symposium on Aeroelasticity in turbomachines; Sep 08, 1980 - Sep 12, 1980; Lausanne; Switzerland
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  • 64
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    Boundary layer development on turbine airfoil suction surfaces (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The results of a study supported by NASA under the Energy Efficient Engine Program, conducted to investigate the development of boundary layers under the influence of velocity distributions that simulate the suction sides of two state-of-the-art turbine airfoils, are presented. One velocity distribution represented a forward loaded airfoil ('squared-off' design), while the other represented an aft loaded airfoil ('aft loaded' design). These velocity distributions were simulated in a low-speed, high-aspect-ratio wind tunnel specifically designed for boundary layer investigations. It is intended that the detailed data presented in this paper be used to develop improved turbulence model suitable for application to turbine airfoil design.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 81-GT-204 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
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  • 65
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    Solution of plane cascade flow using improved surface singularity methods (1981)
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    Publication Date: 2019-07-13
    Description: A solution method has been developed for calculating compressible inviscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method's capabilities are presented.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 81-GT-169 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
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  • 66
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    A quasi-three-dimensional blade surface boundary layer analysis for rotating blade rows (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A quasi-three-dimensional approximation has been developed for a blade boundary layer which involves the calculation of the effect of nonzero pressure gradients, turbulent flow, and blade twist, but includes only a simple coupling between streamlines. The resulting set of equations is solved using Keller's box scheme. The solution scheme is checked against available incompressible flow solutions and then applied to a NASA low aspect ratio transonic compressor stage for which extensive experimental and computational data are available. It is found that the three-dimensional boundary layer separates significantly sooner and has a much larger influence on rotor performance than would be expected from a two-dimensional analysis.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 81-GT-126 , Gas Turbine Conference and Products Show; Mar 09, 1981 - Mar 12, 1981; Houston, TX
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  • 67
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    On the convergence of unsteady generalized aerodynamic forces (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Variations in generalized forces calculated by different computer programs are traced to improper mathematical modeling techniques. Comparisons of generalized forces calculated by three theoretical methods are presented to illustrate difficulties involved in obtaining prediction convergence for increasing wave number. Use of a sufficiently dense chordwise paneling arrangement, in finite panel methods, results in predictions that are essentially identical to predictions of converged solutions. Procedural modifications are suggested for application in finite panel methods to increase prediction accuracy and reduce computer usage costs.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-0647 , Conference on Structures, Structural Dynamics and Materials; Apr 06, 1981 - Apr 08, 1981; Atlanta, GA
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  • 68
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    Analysis of turbulent boundary layer on cascade and rotor blades of turbomachinery (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The momentum integral technique for predicting the boundary layer growth in three-dimensional flow has been extended to include the entrainment equation as the closure model. The numerical solution is compared with the cascade, inducer, compressor, and fan rotor blade data from various sources. The agreement is found to be excellent in all cases, with the exception of the separated flow. Both the momentum thickness and the limiting streamline angle predicted from this analysis compare well with the measured data for a rotor blade. The technique is extremely useful in engineering design, analysis, and performance prediction.
    Keywords: AERODYNAMICS
    Type: International Symposium on Air Breathing Engines; Feb 16, 1981 - Feb 22, 1981; Bangalore; India
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  • 69
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    Flow separation in inlets at incidence angles (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Wind-tunnel pressure data and flow pictures obtained for two two-dimensional inlet models have been examined to study the internal flow structure and separation at large incidence angles. The inlet models were 12-in. high (diffuser exit height) and had internal contraction ratio of 1.21 and 1.17. They were tested at low forward speeds over a wide range of throat Mach numbers (inlet mass flow rates) and angles of incidence. Characteristic features of the internal flow such as a drastic change of pressure gradient near the highlight, local separation bubbles and shock/boundary-layer interactions have been indicated and discussed. For a few specific cases, the experimental surface pressure distributions have been compared with theoretical predictions.
    Keywords: AERODYNAMICS
    Type: International Symposium on Air Breathing Engines; Feb 16, 1981 - Feb 22, 1981; Bangalore; India
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  • 70
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    Perturbation of transonic flow with shocks (1981)
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    Publication Date: 2019-07-13
    Description: A general formulation of the perturbation problem is studied, and a new approach, perturbation sequence expansion, is introduced for handling shock disturbances. The method is applied to unsteady effects, three-dimensional corrections to axisymmetric and two-dimensional flows, and wind tunnel corrections. The perturbation equations are nonlinear and can be solved by shock capturing methods.
    Keywords: AERODYNAMICS
    Type: Symposium on Numerical and Physical Aspects of Aerodynamic Flows; Jan 19, 1981 - Jan 21, 1981; Long Beach, CA
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  • 71
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    Basic advances in the finite-volume method for transonic potential flow calculations (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The finite-volume method of Jameson and Caughey provides a framework within which it is possible to calculate transonic potential flows about essentially arbitrary geometrical configurations. Improvements designed to increase the accuracy of the basic scheme and its consistency in the far field will be described. These include the incorporation of an artificial viscosity which maintains the formal second-order accuracy of the scheme in supersonic zones, and a modification of the flux balances to allow the free-stream conditions to satisfy the difference equations identically. Results of calculations illustrating the importance of these effects will be presented.
    Keywords: AERODYNAMICS
    Type: Symposium on Numerical and Physical Aspects of Aerodynamic Flows; Jan 19, 1981 - Jan 21, 1981; Long Beach, CA
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  • 72
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    Progress on interacting boundary-layer computations at high Reynolds number (1981)
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    Publication Date: 2019-07-13
    Description: The purpose of this paper is to review progress made in the solution of the interacting boundary-layer equations for subsonic flow. The interrelationship of triple deck theory and the interacting boundary-layer approach is discussed with emphasis placed on the development of efficient and reliable algorithms for the solution of the interacting boundary-layer equations. Example studies are presented for laminar and turbulent finite flat plate flow, laminar flow past a flat plate with a separation causing depression, and laminar and turbulent flow past a blunt based trailing edge.
    Keywords: AERODYNAMICS
    Type: Symposium on Numerical and Physical Aspects of Aerodynamic Flows; Jan 19, 1981 - Jan 21, 1981; Long Beach, CA
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  • 73
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    Large-eddy breakup scheme for turbulent viscous drag reduction (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A concept for reducing turbulent skin friction drag by altering/controlling the large coherent eddy structures within the turbulent boundary layer is proposed. Results of an ongoing experimental and numerical investigation to develop large-eddy breakup devices (LEBU devices) are presented and indicate that the average skin friction drag downstream of the LEBU devices is reduced by up to 24% compared to 'undisturbed' flat plate levels; device drag requires further reduction before net drag reductions can be realized. Future work is discussed and will focus on reducing device drag by taking advantage of the unsteady 'freestream' ahead of the LEBU devices.
    Keywords: AERODYNAMICS
    Type: Symposium on Viscous flow drag reduction; Nov 07, 1979 - Nov 08, 1979; Dallas, TX
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  • 74
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    Factors Influencing the Predicted Performance of Advanced Propeller Designs (1981)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The assumptions on which conventional propeller aerodynamic performance analyses are based can be seriously violated when advanced high speed propellers are analyzed. Studies were performed using a lifting line representation for the propeller to determine the sensitivity of predicted propeller performance to various assumptions in the analysis. Items studied include the method of determining blade section lift and the effects of blade section drag, camber and blade sweep. The effects of nonuniform flow into the propeller and compressibility were also studied. Comparisons of analytical and experimental results are presented to demonstrate the overall validity of the results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-82676 , E-942 , AIAA PAPER 81-1564 , Joint Propulsion Conf.; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO; United States
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  • 75
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    Development of a nonlinear vortex method (1981)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Progress is reported in the development of reliable nonlinear vortex methods for predicting the steady and unsteady aerodynamic loads of highly sweptback wings at large angles of attack. Abstracts of the papers, talks, and theses produced through this research are included. The modified nonlinear discrete vortex method and the nonlinear hybrid vortex method are highlighted.
    Keywords: AERODYNAMICS
    Type: NASA-CR-164351
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  • 76
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    Computation of supersonic turbulent flows over an inclined ogive-cylinder-flare (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A supersonic turbulent flow over an ogive-cylinder-flare has been solved numerically. Initially, the parabolized Navier-Stokes equations are solved for the ogive cylinder back to a location upstream of the shock-wave and boundary-layer interaction. Then, the time-dependent Navier-Stokes equations with a thin-layer approximation are solved for the remaining cylinder-flare portion. Results for a Mach number of 2.9 and a unit Reynolds number of 11.42 x 10 to the 6th/m are obtained for angles of attack alpha = 0, 4, and 8 deg. Good agreement has been found between computed and experimental results of the surface pressure on the ogive-cylinder portion, and for the interaction region at alpha = 0 and 4 deg. The role of circumferential communication in a three-dimensional shock-wave and boundary-layer interaction flow field is discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1410 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 77
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    Nonreflecting far-field boundary conditions for unsteady transonic flow computation (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The approximate nonreflecting far-field boundary condition, as proposed by Engquist and Majda, is implemented in the computer code LTRAN2. This code solves the implicit finite-difference representation of the small disturbance equations for unsteady transonic flows about airfoils. The nonreflecting boundary condition and the description of the algorithm for implementing these conditions in LTRAN2 are discussed. Various cases are computed and compared with results from the older, more conventional procedures. One concludes that the nonreflecting far-field boundary approximation allows the far-field boundary to be located closer to the airfoil; this permits a decrease in the computer time required to obtain the solution through the use of fewer mesh points.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1393 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 78
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    Investigation of transonic flow in a cascade using an adaptive mesh (1980)
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    Publication Date: 2019-07-13
    Description: The solution of two-dimensional full potential equation for the analysis of steady transonic flow through cascades is investigated. Finite element method is employed in the analysis. Accuracy and efficiency of the obtained numerical solutions are discussed in terms of the employed computational grid. Accurate modeling of subsonic and supersonic flow regions together with the shock is discussed. The choice of artificial viscosity and relaxation factors are examined and related to the design of a computational grid. Shock capturing and shock fitting procedures are compared for improved accuracy and efficiency. Numerical results include cascades of Gostelow and NACA 0012 airfoils.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1430 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 79
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    Prediction and measurement of turbulent aerodynamic trailing edge flows (1980)
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    Publication Date: 2019-07-13
    Description: A viscous-inviscid interaction algorithm is developed for prediction of two-dimensional mean and fluctuating velocity distributions in the wake immediately downstream of an airfoil trailing edge. A composite pressure field is defined, and a Poisson equation solved for transverse pressure variations. A parabolized form of the time-averaged steady Navier-Stokes equations are solved in conjunction with a viscous-augmented two-dimensional inviscid potential flow analysis. A tensor constitutive equation is employed to predict Reynolds stress distributions from solutions of a turbulence kinetic energy two equation closure model. Numerical predictions compared favorably with detailed experimental data for mean and fluctuating velocities, and Reynolds shear stress distributions, in the trailing edge region of a NACA 63-012 airfoil.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1395 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 80
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    Analysis of nonlifting and lifting airfoils in transonic flow by parametric differentiation (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A method is presented which allows one to solve nonlinear transonic flow problems by analyzing a sequence of linear equations. The small disturbance formulation of steady transonic flow over airfoils is linearized by considering the perturbations due to small changes in airfoil thickness ratio and angle of attack. Repeatedly incrementing those parameters results in a series of nonlinear solutions and cumulatively determines the effects of large changes in airfoil geometry. Successive line overrelaxation is used to solve the associated linear equations and is coupled with predictor-corrector methods to yield series of nonlinear solutions. Computed pressure distributions on biconvex airfoils show good agreement with experimental data and other transonic prediction methods. Possible extensions to unsteady and/or three-dimensional transonic flow problems are briefly discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1394 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 81
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    Complete viscous flowfield solutions about a blunt parabolic body in a supersonic stream (1980)
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    Publication Date: 2019-07-13
    Description: A hybrid computational technique which splits the flowfield into inviscid and viscous regions is used to investigate the complete flowfield about axisymmetric parabolic blunt bodies in a supersonic stream. The solutions are carried out on the CDC CYBER-203 computer which, with its extensive memory, allows for the use of a large number of finite-difference mesh points, allowing resolution of important flowfield features. A range of freestream Mach number of 2-5 and a range of Re number based on nose radius of 500-125,000 was run for a sonic corner body. Contour plots of density, pressure, and Mach number, velocity vector plots, and surface distributions of pressure, heat transfer, and shear stress are presented. Also, correlations of the downstream extent of the base recirculation region with Re number based on nose radius are given.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1351 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 82
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    Zero-length, slotted-lip inlet for subsonic military aircraft (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Zero-length, slotted-lip inlet performance and associated fan blade stresses were determined during model tests using a 20-inch diameter fan simulator in the NASA-LeRC 9- by 15-foot low-speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. Inlet configurations having contraction ratios of 1.2 and 1.3 satisfied all critical low-speed inlet operating requirements for a fixed horizontal nacelle and tilt-nacelle-type subsonic V/STOL aircraft, respectively. Relative to a conventional axisymmetric tilt-nacelle inlet, the zero-length, slotted-lip inlet has a 27-percent smaller inlet lip contraction ratio, an 83-percent shorter total length, and a 5-percent smaller maximum cowl diameter.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1245 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 83
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    Study of cooling air inlet and exit geometries for horizontally opposed piston aircraft engines (1980)
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    Publication Date: 2019-07-13
    Description: A semispan wing and nacelle of a typical general aviation twin-engine aircraft was tested to evaluate the cooling capability and drag of several nacelle shapes; the nacelle shapes included cooling air inlet and exit variations. The tests were conducted in the Ames Research Center's 40- by 80-Foot Wind Tunnel. It was found that the cooling air inlet geometry of opposed piston engine installations has a major effect on inlet pressure recovery, but only a minor effect on drag. Exit location showed a large effect on drag, especially for those locations on the sides of the nacelle where the suction characteristics were based on interaction with the wing surface pressures.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1242 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 84
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    An experimental investigation of endwall profiling in a turbine vane cascade (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Measurements of surface static pressures, flow total pressure loss, and exit air angle were obtained for two linear cascades to establish the effects of endwall profiling. Testing was conducted at an isentropic exit Mach number of 0.85. One cascade was fabricated with planar endwalls while the other had one planar and one profiled endwall. Both cascades utilized the same high pressure turbine inlet guide vane section. It was found that in terms of full passage loss the profiled endwall cascade has the superior performance. The secondary loss results obtained are reasonably well predicted by correlations developed from incompressible flow testing of similar configurations. Inviscid flow and boundary layer calculations are compared with the test data, and overall, the agreement is found to be good. Use of the results for design purposes is briefly discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1089 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 85
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    Comparison between optical measurements and a numerical solution of the flow field within a transonic axial-flow compressor rotor (1980)
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    Publication Date: 2019-07-13
    Description: A comparison between numerical and experimental results is presented for the flowfield within a transonic axial-flow compressor rotor. The rotor was tested at design speed and a wide open throttle discharge condition. The relative tip Mach number was 1.4. A laser anemometer system was used to measure velocity and flow angle upstream, within, and downstream of the rotor. A holographic interferometer was used to visualize the rotor shock system near the tip. The computational procedure solves the full three-dimensional Euler equations using a time-marching technique. Shock location and shape determined from the two optical systems are compared. Calculated relative Mach number and flow angle contours, shock locations, and shock strength are compared to values measured with the laser anemometer.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1078 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 86
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    Modern fluid dynamics of subsonic and transonic flight (1980)
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    Publication Date: 2019-07-13
    Description: The paper discusses a number of factors, termed research drivers, which are expected to provide much of the stimulus for research in the subsonic and transonic flight regimes in the coming decade. The research drivers discussed comprise the need for energy efficiency, new and improved facilities, better instrumentation, more capable and efficient computers, theoretical methodology refinements, increased use of optimization techniques, and military requirements. Illustrations of advances in aircraft aerodynamics at subsonic and transonic speeds are presented, along with a discussion of future research opportunities and trends. Particular attention is given to airfoil and basic fluids research designed to reduce skin-friction drag.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0861 , International Meeting and Technical Display on Global Technology 2000; May 06, 1980 - May 08, 1980; Baltimore, MD
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  • 87
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    Control of forebody vortex orientation to alleviate side forces (1980)
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    Publication Date: 2019-07-13
    Description: The paper deals with the salient phenomena of three-dimensional symmetric and asymmetric separated flows about typical forbodies at high angles of attack. Particular consideration is given to pressure, forces, and laser vapor screen measurements carried out on a 5-deg semiangle cone in a Mach 0.6 flow under turbulent conditions and supportive tests using a 16-deg semiangle tangent ogive.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0183 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 88
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    Computation of three-dimensional viscous supersonic flow in inlets (1980)
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    Publication Date: 2019-07-13
    Description: A new approach has been developed for the computation of the three-dimensional viscous supersonic flow with embedded subsonic regions adjacent to solid boundaries and is applied to a mixed-compression supersonic inlet typical of current designs. The approach uses a reduced form of the three-dimensional Navier-Stokes equations so that the resultant equations can be treated as an initial boundary value problem and thus be solved by non-iterative forward marching in space. The numerical procedure utilizes an efficient consistently-split linearized block implicit technique to solve the finite difference analogues to the set of governing partial differential equations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0194 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 89
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    Influence of nonequilibrium radiation on heating of an ablating Jovian entry probe (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The influence of non-local thermodynamic equilibrium (NLTE) radiative transfer on the entire shock-layer flow phenomena around a Jovian entry body is investigated. The flow in the shock layer is assumed to be viscous, axisymmetric, laminar, and in chemical equilibrium. The entry body considered is a 35-deg hyperboloid and the results have been obtained for the peak heating entry conditions. The results indicate that the radiative heating of the entry body is significantly higher under NLTE conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0356 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 90
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    Experimental investigation of the asymmetric body vortex wake (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An experimental investigation of the asymmetric body vortex wake of a circular cylinder in high subsonic flow is presented. Laser velocimeter, force and moment, and surface hot wire measurements were obtained for a freestream Mach number of 0.6 and Reynolds number (based on body diameter) of 0.62 x 10 to the 6th. Two component laser velocimeter measurements were made at three body cross-flow planes, x/d = 4, 8, and 12, and angles of attack of 25, 35, and 45 deg. Laser vapor screen photographs were also obtained at these body stations and angles of attack. Surface hot wire measurements were used to determine if any vortex switching occurred at various angles of attack of the body. The laser velocimeter measurements are related to the vapor screen photographs and side force measurements. These results show that more than one asymmetric body vortex wake configuration can exist for the same angle of attack and body roll angle.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0174 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 91
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    Implicit computations of unsteady transonic flow governed by the full-potential equation in conservation form (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An alternating-direction implicit algorithm is presented for solving the conservative, full-potential equation for unsteady, transonic flow. A new development is the time-linearization of the density function. This linearization reduces the solution process from one of solving a system of two equations at each mesh point to one of solving a single equation. Two sample cases are computed. First, a one-dimensional traveling shock wave is computed and compared with the analytic solution. Second, a two-dimensional case is computed of a flow field that results from a thickening and subsequently thinning airfoil. The resulting flow field, which includes a traveling shock wave, is compared to the flow field obtained from the low-frequency, small-disturbance, transonic equation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0150 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 92
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    Simulated transonic flows for aircraft with nacelles, pylons, and winglets (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A computational method which simulates transonic flow about wing-fuselage configurations has been extended to include the treatment of multiple body and non-planar wing surfaces. The finite difference relaxation scheme is characterized by a modified small disturbance flow equation and multiple embedded grid system. Wing-body combinations with as many as four nacelles/pods, four pylons, and wing-tip-mounted winglets can be analyzed. A scheme for modeling inlet spillage and engine exhaust interference effects has been included. Computed results are correlated with experimental data for three transport configurations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0130 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 93
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    Calculation of inlet flow fields by an implicit technique (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Two-dimensional inlet flow fields in a supersonic free stream are calculated by an implicit, shock-capturing, finite-difference method. The Euler equations are subjected to a general curvilinear transformation and a body-fitted coordinate system is employed. The method is used to solve supercritical, critical, and subcritical flow fields which are simulated by prescribing appropriate conditions at the inlet outflow boundary. Results are presented for a drooped-cowl inlet.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0031 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 94
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    Flight-measured effects of boattail angle and Mach number on the nozzle afterbody flow of a twin-jet fighter (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The paper presents the flight-measured nozzle afterbody surface pressures and engine exhaust nozzle pressure-area integrated axial force coefficients on a twin-jet fighter for varying boattail angles. The objective of the tests was to contribute to a full-scale flight data base applicable to the nozzle afterbody drag of advanced tactical fighter concepts. The data were acquired during the NASA F-15 Propulsion/Airframe Interactions Flight Research Program. Nozzle boattail angles from 7.7 deg to 18.1 deg were investigated. Results are presented for cruise angle of attack at Mach numbers from 0.6 to 2.0 at altitudes from 20,000 to 45,000 feet. The data show the nozle axial force coefficients to be a strong function of nozzle boattail angle and Mach number.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0110 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 95
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    Experimental and analytical comparison of aerodynamic characteristics of a forward-control missile (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Comparisons of analytical and experimental aerodynamic data for canard controlled missile configurations are presented. Recently, techniques to estimate the longitudinal, directional and lateral aerodynamic characteristics for cruciform missiles have been developed. Nielsen Engineering and Research, Inc. (NEAR, Inc.), supported by various governmental agencies, has been the originator of many of these new computational techniques. Two of these are major computer programs currently being implemented by several research organizations. Predicted data from these two programs are compared with experimental data recently obtained at the NASA Langley Research Center Unitary Plan wind tunnel facility. Comparisons cover the supersonic Mach number regime of 1.60 to 3.50, angles-of-attack from 0 to 20 degrees and roll angles of 0, 26.57 and 45 degrees. Major emphasis is on the roll characteristics due to aileron with limited longitudinal and directional characteristics addressed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0374 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 96
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    Transonic swept-wing analysis using asymptotic and other numerical methods (1980)
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    Publication Date: 2019-07-13
    Description: The paper presents asymptotic methods for high-aspect-ratio wings in transonic flow developed for straight unyawed wings and for oblique wings. They show that the three-dimensional mixed-flow calculations may be reduced to solving a set of two-dimensional problems at each span station; the development of this theory and the related computational studies are reviewed. Differences between the piloted (oblique) wing, the swept-back wing, and the swept-forward-wing in the induced upwash are discussed; examples of similarity solutions are demonstrated for high subcritical and slightly supercritical component flows, and comparisons made with relaxation solutions of a full potential equation. The examples include oblique and symmetric swept wings, and the adequacy of the existing full-potential computer code is examined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0342 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 97
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    Blade loading and spanwise effects on the near and far wake characteristics of a compressor rotor blade (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An experimental investigation of the blade loading and spanwise effects on the rotor wake is presented. The investigation was limited to a study of a low subsonic and incompressible wake flow found downstream of a lightly loaded rotor. Measurements were made with a tri-axial hot wire probe mounted in the stationary frame of reference at six radial and nine axial positions. At each measurement location, the rotor was run at different operating conditions to discern the effects of blade loading on the wake. Near and far wake measurements are given, including mean velocity and turbulence intensity characteristics. The loading and spanwise effects on rotor wake characteristics were found to be substantial.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0201 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 98
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    Boundary-layer transition on a 10-deg cone - Wind tunnel/flight correlation (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Boundary-layer transition location measurements were made on a 10-deg sharp cone in 23 wind tunnels of the US and Europe and in flight. The data were acquired at subsonic, transonic, and supersonic Mach numbers over a range of unit Reynolds numbers to obtain an improved understanding of wind tunnel flow quality influence. Cone surface microphone measurements showed Tollmien-Schlichting waves present. Transition location defined by pitot probe measurements showed transition Reynolds number to be correlatable to cone surface disturbance amplitude within + or - 20 percent for the majority of tunnel and flight data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0154 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 99
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    Propeller slipstream/wing interaction in the transonic regime (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An inviscid model for the interaction between a thin wing and a nearly uniform propeller slipstream is presented. The model allows the perturbation velocities due to the interaction to be potential although the undisturbed slipstream velocity is rotational. A finite difference scheme is used to solve the governing equation. Numerical examples indicate that the slipstream has a strong effect on the aerodynamic properties of the wing section within the slipstream and lesser effects elsewhere. The slipstream swirling motion strongly affects the wing load distribution, however, its effect on the wing's total lift and wave drag is small. The axial velocity increment in the slipstream has a small effect on the wing lift, however, it causes a large increase in wave drag.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0125 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 100
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    Forebody and base region real-gas flow in severe planetary entry by a factored implicit numerical method. I - Computational fluid dynamics (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new code for the simulation of full (forebody and base region) flowfields about bluff bodies in the hypersonic regime of severe planetary entry is described. The present 'maximally conservative, maximally differenced' formulation of the unsteady compressible Navier-Stokes equations for 2-D axisymmetric 3-D flow is contrasted for stability with previous formulations of Viviand, Kutler, et al, and Thomas and Lombard. Discrete metric relations peculiar to the axisymmetric finite volume formulation are presented along with a general discussion of their relations to and consequences of failure to close computational cells. A computational mesh of curvilinear coordinate topology singular in the flow regime is presented that permits aligned capturing of the major physical features of the complex flowfield.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0065 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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