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  • AERODYNAMICS  (12,790)
  • 1
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    Astronautics and aeronautics, 1969 Chronology on science, technology, and policy (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Statistical mechanics for wall shear turbulence in Couette flow based on Brownian motion and comparison with stochastic theory based on Navier-Stokes equation
    Keywords: AERODYNAMICS
    Type: NASA-SP-4014
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  • 2
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    Aeronautical Engineering A special bibliography with indexes, supplement 7 (1971)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - July 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(07)
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  • 3
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    Analytic Methods in Aircraft Aerodynamics (1970)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: Analyses of aircraft aerodynamic characteristics
    Keywords: AERODYNAMICS
    Type: NASA-SP-228 , A Symposium Held at Ames Research Center; Oct 28, 1969 - Oct 30, 1969; MOFFETT FIELD, CA; United States
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  • 4
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    Aeronautical Engineering - A special bibliography with indexes /supplement 1/ (1971)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: Annotated reference bibliography on aeronautical engineering documents
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(01)
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  • 5
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    The National and International Significance of the Lunar Exploration Program (1963)
    In:  Other Sources
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    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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  • 6
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    Aeronautical engineering - A special bibliography, supplement 2 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - Jan. 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(02)
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  • 7
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    Hypersonic aerodynamics test facility using the external propulsion accelerator (1995)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The use of the External propulsion Accelerator (EPA) for launching models of hypersonic aerodynamic configurations into an instrumented ballistic range is discussed. The aerodynamic model is encased inside an axisymmetric projectile designed to be accelerated to high speed in the EPA. Accelerator lengths required to achieve hypersonic speeds are estimated to vary from 10 meters for Mach 7, 40 meters for Mach 10, 150 meters for Mach 15, and 700 meters for Mach 30, assuming a limit of 50,000 g's acceleration. For a model span of 10 cm to 25 cm, the launch tube diameters are 40 cm and 100 cm, respectively. Using this EPA launcher will enable exact simulation of hypersonic flight in ground facilities where both the gas composition and pressure can be controlled in the ballistic range.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 95-6138 , AIAA, Aerospace Planes and Hypersonics Technologies Conference; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States|; 5 p.
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  • 8
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    Overview of supersonic laminar flow control research on the F-16XL ships 1 and 2 (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: NASA is directing research to develop technology for a high-speed civil transport. Supersonic laminar flow control has been identified as a program element, since it offers significant drag-reduction benefits and is one of the more promising technologies for producing an economically viable aircraft design. NASA is using two prototype F-16XL aircraft to research supersonic laminar flow control. The F-16XL planform is similar to design planforms of high-speed civil transports. The planform makes the aircraft ideally suited for developing technology pertinent to high-speed transports. The supersonic laminar flow control research programs for both aircraft are described. Some general results of the ship-1 program demonstrate that significant laminar flow was obtained using laminar flow control on a highly swept wing at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 921994 , ; 14 p.|SAE, Aerotech ''92 Conference; Oct 05, 1992 - Oct 08, 1992; Anaheim, CA; United States
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  • 9
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    Perspectives on hypersonic viscous flow research (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Issues and advances in current hypersonic flow research perceived to be of interest in theoretical fluid/gas dynamics are reviewed. Particular attention is given to the hypersonic aircraft as waverider, computational methods and theoretical development in the study of viscous interaction, and boundary-layer instability and transition studies. In the present framework the study of viscous hypersonic flow faces transition problems of two kinds which represent the two major areas of current research: the turbulence transition in the high Re range and the transition to the free-molecule limit.
    Keywords: AERODYNAMICS
    Type: In: Annual review of fluid mechanics. Vol. 25 (A94-10885 01-34); p. 455-484.
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  • 10
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    Identification of aerodynamic coefficients using computational neural networks (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 16; 6; p. 1018-1025.
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  • 11
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    Development of the wake behind a circular cylinder impulsively started into rotatory and rectilinear motion (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The temporal development of a 2D viscous incompressible flow generated by a circular cylinder started impulsively into steady rotatory and rectilinear motion is studied by integration of a velocity/vorticity formulation of the governing equations, using an explicit finite-difference/pseudo-spectral technique and an implementation of the Biot-Savart law. Results are presented for a Reynolds number of 200 (based on the cylinder diameter 2a and the magnitude U of the rectilinear velocity) for several values of the angular/rectilinear speed ratio alpha = omega(a)/U (where omega is the angular speed) up to 3.25. Several aspects of the kinematics and dynamics of the flow not considered earlier are discussed. For higher values of alpha, the results indicate that for Re = 200, vortex shedding does indeed occur for alpha = 3.25. However, consecutive vortices shed by the body can be shed from the same side and be of the same sense, in contrast to the nonrotating case, in which mirror-image vortices of opposite sense are shed alternately on opposite sides of the body. The implications of the results are discussed in relation to the possibility of suppressing vortex shedding by open or closed-loop control of the rotation rate.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics (ISSN 0022-1120); p. 449-484.
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  • 12
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    A time-accurate high-resolution TVD scheme for solving the Navier-Stokes equations (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A total variation diminishing (TVD) scheme has been developed and incorporated into an existing time-accurate high-resolution Navier-Stokes code. The accuracy and the robustness of the resulting solution procedure have been assessed by performing many calculations in four different areas: shock tube flows, regular shock reflection, supersonic boundary layer, and shock boundary layer interactions. These numerical results compare well with corresponding exact solutions or experimental data.
    Keywords: AERODYNAMICS
    Type: Computers & Fluids (ISSN 0045-7930); 22; 5-Apr; p. 517-528.
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  • 13
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    Viscous and inviscid instabilities of a trailing vortex (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The linear stability of the trailing line vortex model of Batchelor (1964) is studied using a spectral collocation and matrix eigenvalue method. The entire unstable region in the swirl/axial wavenumber parameter space is mapped out for various azimuthal wavenumbers for both the inviscid and viscous stability problem. The results of the study provide a direct numerical validation of the large-azimuthal-wavenumber asymptotic analysis of Leibovich and Stewartson (1983). It is shown that accurate results are obtained up to azimuthal wavenumbers of 10,000 and greater, and the agreement with the asymptotic theory is excellent.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics (ISSN 0022-1120); p. 91-114.
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  • 14
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    Exploratory study of wall pressure fluctuations in a Mach 5, sharp fin-induced turbulent interaction (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 9 Se; 2188-219
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  • 15
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    A new approach for the calculation of transitional flows (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: In spite of many attempts at modeling natural transition, it has not been possible to predict the streamwise intensities. A procedure is developed which incorporates some results of linear stability theory into one-equation and stress model formulations. The stresses resulting from fluctuations in the transitional region have turbulent, laminar (nonturbulent) and large eddy components. Comparison with Schubauer and Klebanoff's experiments have shown that the nonturbulent and large eddy components have a large influence on the streamwise intensities and little influence on the shear stress. Finally, predictions of the one-equation model were as good as those obtained by the stress model.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2669 , AIAA Applied Aerodynamics Conference; Jun 22, 1992 - Jun 24, 1992; Palo Alto, CA; United States
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  • 16
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    Numerical simulations of upstream blocking, columnar disturbances, and bores in stably stratified shear flows over an obstacle (1994)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A two-dimensional, nonhydrostatic, elastic numerical model has been used to study the generation of gravity waves for a stably stratified shear flow over an obstacle. When a low-level wind shear is included in the simulation, we find that the predictions for noticeable upstream effects based on Froude number for a uniform flow are no longer accurate. Upstream effects are encountered in the form of upstream propagating columnar disturbances and internal bores away from the obstacle. The limited parameter space studies conducted in this study suggest that the ratio of the shear depth to the obstacle heigh (d/H), the obstacle aspect ratio (H/L), and the Froude number (U/NH) are instrumental in determining the strength and the existence of these upstream disturbances. Thus, the present theoretical and empirical understanding of the importance of the Froude number for determining the nature of upstream effects should be modified substantially to include additional nondimensional parameters when shear is present.
    Keywords: AERODYNAMICS
    Type: Monthly Weather Review (ISSN 0027-0644); 122; 11; p. 2506-2529
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  • 17
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    Aerothermodynamic heating due to shock wave/laminar boundary-layer interactions in high-enthalpy hypersonic flow (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The interaction between a swept shock wave and a laminar boundary layer was investigated experimentally in high-enthalpy hypersonic flow. The effect of high-temperature, real gas physics on the interaction was examined by conducting tests in air and helium. Heat transfer measurements were made on the surface of a flat plate and a shock-generating fin using thin-film resistance sensors for fin incidence angles of 0, 5, and 10 deg at Mach numbers of 6.9 in air and 7.2 in helium. The experiments were conducted in the NASA HYPULSE expansion tube, an impulse-type facility capable of generating high-enthalpy, high-velocity flow with freestream levels of dissociated species that are particularly low. The measurements indicate that the swept shock wave creates high local heat transfer levels in the interaction region, with the highest heating found in the strongest interaction. The maximum measured heating rates in the interaction are order of magnitude greater than laminar flat plate boundary layer heating levels at the same location.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3135 , AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 12 p.
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  • 18
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    Flow field measurements in a crossing shockwave turbulent boundary layer interaction at Mach 3 (1993)
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    Publication Date: 2019-08-28
    Description: An experimental study has been conducted to examine the flow field of the 3D crossing shock wave/turbulent boundary layer interaction. A symmetric pair of 9-deg fins were used to generate the crossing shocks. The incoming boundary layer was developed on the tunnel sidewall and thus was relatively thick, 0.49 arcsec, and suited for pitot probe surveys. The test conditions were a nominal Mach number of 3 and unit Reynolds number of 1.2 x 10 exp 7/ft. The measurements obtained included surface oil flow visualizations, surface static pressures, and boundary layer pitot pressure profiles. The results showed that downstream of the crossing shock intersection, the stagnation pressure losses were significant and the stagnation pressure profiles were highly nonuniform. Despite the severe shock disturbances, the law of the wall and the law of the wake were found to give relatively good agreement with the experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3434 , In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-47201 19-02); p. 290-300.
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  • 19
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    Nonequilibrium effects on the aerothermodynamics of transatmospheric and aerobraking vehicles (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A 3D CFD algorithm is used to study the effect of thermal and chemical nonequilibrium on slender and blunt body aerothermodynamics. Both perfect gas and reacting gas air models are used to compute the flow over a generic transatmospheric vehicle and a proposed lunar transfer vehicle. The reacting air is characterized by a translational-rotational temperature and a vibrational-electron-electronic temperature and includes eight chemical species. The effects of chemical reaction, vibrational excitation, and ionization on lift-to-drag ratio and trim angle are investigated. Results for the NASA Ames All-body Configuration show a significant difference in center of gravity location for a reacting gas flight case when compared to a perfect gas wind tunnel case at the same Mach number, Reynolds number, and angle of attack. For the same center of gravity location, the wind tunnel model trims at lower angle of attack than the full-scale flight case. Nonionized and ionized results for a proposed lunar transfer vehicle compare well to computational results obtained from a previously validated reacting gas algorithm. Under the conditions investigated, effects of weak ionization on the heat transfer and aerodynamic coefficients were minimal.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2837 , AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 11 p.
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  • 20
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    Monte Carlo simulation of radiating reentry flows (1993)
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    Publication Date: 2019-08-28
    Description: The Direct Simulation Monte Carlo (DSMC) method is applied to a radiating, hypersonic, axisymmetric flow over a blunt body in the near continuum regime. The ability of the method to predict the flowfield radiation and the radiative heating is investigated for flow over the Project Fire II configuration at 11.36 kilometers per second at an altitude of 76.42 kilometers. Two methods that differ in the manner in which they treat ionization and estimate electronic excitation are employed. The calculated results are presented and compared with both experimental data and solutions where radiation effects were not included. Differences in the results are discussed. Both methods ignore self absorption and, as a result, overpredict measured radiative heating.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2809 , AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 13 p.
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  • 21
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    Line relaxation methods for the solution of 2D and 3D compressible flows (1993)
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    Publication Date: 2019-08-28
    Description: An implicit finite element based algorithm for the compressible Navier-Stokes equations is outlined, and the solution of the resulting equation by a line relaxation on general meshes of triangles or tetrahedra is described. The problem of generating and adapting unstructured meshes for viscous flows is reexamined, and an approach for both 2D and 3D simulations is proposed. An efficient approach appears to be the use of an implicit/explicit procedure, with the implicit treatment being restricted to those regions of the mesh where viscous effects are known to be dominant. Numerical examples demonstrating the computational performance of the proposed techniques are given.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3366 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 2 (A93-44994 18-34); p. 743-750.
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  • 22
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    It's time to go supersonic (1993)
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    Publication Date: 2019-08-28
    Description: An overview is presented of the most compelling technological and economic arguments for NASA's agressive coordination of an SST-development program that would enlist all available U.S. aerospace industry resources. Attention is given to the minimization of upper atmosphere pollution through the use of low-NO(x) emission combustors and the reduction of sonic boom through wing/fuselage optimization. It is projected that a successful SST program would boost U.S. civil aircraft market share to nearly 80 percent; this represents the creation of 140,000 new jobs.
    Keywords: AERODYNAMICS
    Type: Air & Space (ISSN 0886-2257); 8; 2; p. 54, 55.
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  • 23
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    Effect of nose shape on three-dimensional streamlines and heating rates (1993)
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 1; p. 69-78.
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  • 24
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    Effects of Goertler vortices, wall cooling and gas dissociation on the Rayleigh instability in a hypersonic boundary layer (1993)
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    Publication Date: 2019-08-28
    Description: In a hypersonic boundary layer over a wall of variable curvature, the region most susceptible to Goertler vortices is the temperature adjustment layer sitting at the edge of the boundary layer. This temperature adjustment layer is also the most dangerous site for Reyleigh instability. We investigate how the existence of large amplitude Goertler vortices affects the growth rate of Rayleigh instability. The effects of wall cooling and gas dissociation on this instability are also studied. We find that all these mechanisms increase the growth rate of Rayleigh instability and are therefore destabilizing.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics (ISSN 0022-1120); p. 503-525.
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  • 25
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    Monte Carlo simulation of entry in the Martian atmosphere (1993)
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 7; 2; p. 228-232.
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  • 26
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    New approach for the calculation of transitional flows (1993)
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 4; p. 629-636.
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  • 27
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    Interaction strength and model geometry effects on the structure of crossing-shock wave/turbulent boundary-layer interactions (1993)
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    Publication Date: 2019-08-28
    Description: The flowfield structure of a range of symmetric crossing-shock wave/turbulent boundary-layer interactions of varying strength is presented. The test geometry, consisting of a symmetric pair of opposing sharp fins at angle of attack, alpha, mounted to a flat plate, is studied experimentally for a range of alpha from 7 to 15 degrees at Mach numbers of 3 and 4. Results reveal that the basic flowfield shock structure remains similar in nature over the range of interaction strengths examined, with the only changes being in the scale and location of the various features present. The separated flow regions are classified as being either completely or partially separated, the completely separated case being the one in which the entire incoming boundary layer separates from the plate surface. For the current experiments, all but the weakest of the interactions exhibited complete boundary layer separation. Finally, the effects of model geometry are analyzed by comparing data for shock generators of varying lengths, with the results showing no evidence of upstream influence due to the shock generator trailing edges.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0780 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 13 p.
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  • 28
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    Estimation of unsteady lift on a pitching airfoil from wake velocity surveys (1993)
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    Publication Date: 2019-08-28
    Description: The results of a joint experimental and computational study on the flowfield over a periodically pitched NACA0012 airfoil, and the resultant lift variation, are reported in this paper. The lift variation over a cycle of oscillation, and hence the lift hysteresis loop, is estimated from the velocity distribution in the wake measured or computed for successive phases of the cycle. Experimentally, the estimated lift hysteresis loops are compared with available data from the literature as well as with limited force balance measurements. Computationally, the estimated lift variations are compared with the corresponding variation obtained from the surface pressure distribution. Four analytical formulations for the lift estimation from wake surveys are considered and relative successes of the four are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0437 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 15 p.
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  • 29
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    Adaptive remeshing for three-dimensional compressible flow computations (1992)
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    Publication Date: 2019-08-28
    Description: A practical solution algorithm for steady 3D Euler flows is presented. This algorithm employs coupling of a surface triangulator, an automatic tetrahedral mesh generator, an unstructured grid flow solver, and an error estimation procedure. The performance of the method is illustrated using a shock interaction problem in high Mach number flow over a swept circular cylinder.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics (ISSN 0021-9991); 103; 2; p. 269-285.
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  • 30
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    Experimental investigation of an axisymmetric hypersonic scramjet inlet for laser propulsion (1992)
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 6; p. 1232-1238.
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  • 31
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    Evaluation and application of the Baldwin-Lomax turbulence model in two-dimensional, unsteady, compressible boundary layers with and without separation in engine inlets (1992)
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    Publication Date: 2019-08-28
    Description: The Baldwin-Lomax model is used in many CFD codes because it is quick and easy to implement. In this paper, we discuss implementing the Baldwin-Lomax turbulence model for both steady and unsteady compressible flows. In addition, these flows may be either separated or attached. In order to apply this turbulence model to flows which may be subjected to these conditions, certain modifications should be made to the original Baldwin-Lomax model. We discuss these modifications and determine whether the Baldwin-Lomax model is a viable turbulence model that produces reasonably accurate results for high speed flows that can be found in engine inlets.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-3676 , ; 10 p.|AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jul 06, 1992 - Jul 08, 1992; Nashville, TN; United States
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  • 32
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    An effective multigrid method for high-speed flows (1992)
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    Publication Date: 2019-08-28
    Description: The use is considered of a multigrid method with central differencing to solve the Navier-Stokes equations for high speed flows. The time dependent form of the equations is integrated with a Runge-Kutta scheme accelerated by local time stepping and variable coefficient implicit residual smoothing. Of particular importance are the details of the numerical dissipation formulation, especially the switch between the second and fourth difference terms. Solutions are given for 2-D laminar flow over a circular cylinder and a 15 deg compression ramp.
    Keywords: AERODYNAMICS
    Type: Communications in Applied Numerical Methods (ISSN 0748-8025); 8; 9; p. 671-681.
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  • 33
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    A general explicit or semi-explicit algorithm for compressible and incompressible flows (1992)
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    Publication Date: 2019-08-28
    Description: A unified finite element algorithm is developed which is applicable to a wide range of problems of fluid mechanics without recourse to artificial, empirically determined factors. In its explicit form, the algorithm is similar to the Taylor-Galerkin scheme and is easily adopted to standard codes. The scheme proposed here possesses sufficient natural balancing diffusion and thus reduces and sometimes eliminates the need for special 'shock capturing' diffusion. The efficiency of the algorithm is demonstrated using several examples ranging from incompressible through transonic regions to supersonic flows.
    Keywords: AERODYNAMICS
    Type: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 35; 3 Au; 457-479
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    Computation of turbulent, separated, unswept compression ramp interactions (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Examination of the literature shows that the comparison between experiment and computation for highly separated unswept compression ramp flows is generally poor, irrespective of the turbulence model used. In general, the upstream influence is not correct, the wall pressure rise through separation is too steep, and the pressures under the separated shear layer are too high. In the current study, the objective is to determine if these discrepancies might be attributed more to other factors such as flowfield unsteadiness or three-dimensionality, rather than to inadequate turbulence modeling. To examine this possibility, multichannel wall pressure fluctuations were measured under the unsteady separation shock wave in a 28-deg unswept compression ramp flow at Mach 5. The results show that the large scale, low frequency separation shock unsteadiness controls the distribution of time-averaged surface properties and that neglect of the unsteadiness is probably the primary cause of the discrepancy between experiment and computation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 8 Au; 2056-206
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  • 35
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    Full Navier-Stokes analysis of an axisymmetric scramjet inlet (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 9; 6; p. 827-833.
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  • 36
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    Adaptive wall technology for three-dimensional models at high subsonic speeds and aerofoil testing through the speed of sound (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Adaptive wall research at the University of Southampton has been directed towards the development of testing techniques for use in nonporous test sections where two flexible walls are profiled in single curvature. This paper highlights the recent advances that have been made in the testing of 2D airfoils through the speed of sound and the testing of 3D models at high subsonic speeds. Techniques have been developed to accommodate the variety of flow regimes encountered in near sonic airfoil tests. The experimental evidence to date suggests that the new techniques coupled with established procedures allow airfoil data, free from top and bottom wall interference, to be gathered from adaptive flexible walled test sections throughout the entire subsonic, transonic and supersonic speed ranges. Techniques applicable to the testing of 3D models have evolved primarily from experience gained by testing sidewall mounted half-wings. Emphasis has been placed upon models with planforms similar to those of current transport wings. Techniques for high subsonic speeds have now been developed to the point where the residual levels of interference are low.
    Keywords: AERODYNAMICS
    Type: In: Wind tunnels and wind tunnel test techniques; Proceedings of the Conference, Southampton, United Kingdom, Sept. 14-17, 1992 (A94-10401 01-09); p. 42.1-42.12.
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    Vortex developments over steady and accelerated airfoils incorporating a trailing edge jet (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Computational and experimental studies are conducted to investigate the influence of a trailing edge jet on flow separation and subsequent vortex formation over steady and accelerated airfoils at high angles of attack. A computer code, employing the stream function-vorticity approach, is developed and utilized to conduct numerical experiments on the flow problem. To verify and economize such efforts, an experimental system is developed and incorporated into a subsonic wind tunnel where streamline and vortex flow visualization experiments are conducted. The study demonstrates the role of the trailing edge jet in controlling flow separation and subsequent vortex development for steady and accelerating flow at angles past the static stall angle of attack. The results suggest that the concept of the trailing edge jet may be utilized to control the characteristics of unsteady separated flows over lifting surfaces. This control possibility seems to be quite effective and could have a significant role in controlling unsteady separated flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3008 , ; 13 p.|AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
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  • 38
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    A new flux splitting scheme (1993)
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    Publication Date: 2019-08-28
    Description: A new flux splitting scheme is proposed. The scheme is remarkably simple and yet its accuracy rivals and in some cases surpasses that of Roe's solver in the Euler and Navier-Stokes solutions performed in this study. The scheme is robust and converges as fast as the Roe splitting. An approximately defined cell-face advection Mach number is proposed using values from the two straddling cells via associated characteristic speeds. This interface Mach number is then used to determine the upwind extrapolation for the convective quantities. Accordingly, the name of the scheme is coined as Advection Upstream Splitting Method (AUSM). A new pressure splitting is introduced which is shown to behave successfully, yielding much smoother results than other existing pressure splittings. Of particular interest is the supersonic blunt body problem in which the Roe scheme gives anomalous solutions. The AUSM produces correct solutions without difficulty for a wide range of flow conditions as well as grids.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics (ISSN 0021-9991); 107; 1; p. 23-39.
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  • 39
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    Strong vortex/boundary layer interactions. II - Vortices low (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: This is the second of two papers on the interaction between a longitudinal vortex pair, produced by a delta-wing at angle of attack, and a turbulent boundary layer developing on a flat plate. In the first paper only the outer parts of the vortices entered the boundary layer whereas in this paper the vortices merge with it. In the resultant interaction, the boundary layer between the vortices is kept thin by lateral divergence and a three-dimensional separation line is formed outboard of each vortex. Turbulent, momentum-deficient fluid containing longitudinal vorticity is entrained from the boundary layer along these lines and wrapped around the vortices. As a consequence, the turbulent region of the vortices increases in size and the circulation slowly decreases. It is shown that the flow near the separation line and in the vortices is complicated, and this interaction is expected to be more difficult to calculate than the first. Detailed mean flow and turbulence measurements are reported.
    Keywords: AERODYNAMICS
    Type: Experiments in Fluids (ISSN 0723-4864); 14; 6; p. 393-401.
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  • 40
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    Comparisons between DSMC and the Navier-Stokes equations for reentry flows (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A detailed comparison is made between Navier-Stokes and DSMC calculations for flows near the continuum limit to assess the accuracy of the continuum equations in this regime. Meaningful comparisons require the use of similar physical models. This necessitates the inclusion of a separate rotational energy equation and use of slip boundary conditions. Inclusion of slip boundary conditions resulted in improved agreement between surface properties. Moreover, good agreement was obtained for the various temperatures in the nonequilibrium portion of the flow field that does not contain the shock region. Departures are noted in the shock region and in regions where thermal diffusion effects are important.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2810 , ; 14 p.|AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
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  • 41
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    Aerodynamic heating in the vicinity of hypersonic, axisymmetric, shock-wave boundary-layer interactions (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Aerodynamic heating rates are calculated from time-dependent temperature measurements in the vicinity of shock-wave boundary-layer interactions due to conical compression ramps on an axisymmetric body. The data were acquired at the Ohio State University Aeronautical and Astronautical Research Laboratory and at the Air Force Flight Dynamics Laboratory at Mach numbers of 6 and 10. The model is a cylindrical body with a 10 deg conical nose. Conical ramps with half-angles of 10, 20, 25, 30, and 35 deg serve as shock-wave generators. Flowfield surveys are made in the vicinity of the ramp vertices, separation points, and reattachment points. Experimental results quantify temperature response and the resulting heat transfer rates as a function of ramp angle, Reynolds number and freestream Mach number. The temperature responses within the flowfield appear to be steady-state for all angles and all Reynolds numbers, and hence, the heat transfer rates appear to be steady-state.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-2766 , AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States|; 10 p.
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  • 42
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    A coarse-grid correction/nonlinear relaxation algorithm for the three-dimensional, compressible Navier-Stokes equations (1993)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A combined coarse-grid correction/upwind relaxation strategy to provide rapid convergence for 3D high-speed viscous flowfields is discussed an evaluated. The construction and analysis of a simple two-grid acceleration procedure based on 'hyperbolic' multigrid concepts is presented. Numerical simulations of a 2D compression-corner flowfield, a 3D crossing shock/turbulent boundary layer interaction, and a 3D scramjet inlet flowfield are presented to illustrate the benefits of the approach. Results indicate that the procedure generally converges two or more times faster than the baseline algorithm.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3317 , In: AIAA Computational Fluid Dynamics Conference, 11th, Orlando, FL, July 6-9, 1993, Technical Papers. Pt. 1 (A93-44994 18-34); p. 223-233.
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  • 43
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    A study of hypersonic swept shock wave/turbulent boundary layer interactions using a conical Navier-Stokes code (1992)
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    Publication Date: 2019-08-28
    Description: A computational study has been performed of sharp fin-induced swept shock wave/turbulent boundary layer interactions at low hypersonic Mach numbers. The objective was to determine if results obtained using a conical Navier-Stokes code, particularly the peak heating and pressure, are adequate for engineering predictions. The advantage of the conical approach is that the problem becomes two-dimensional and requires much less computational effort than a fully three-dimensional calculation. In this code, the standard Baldwin-Lomax model is used for turbulent closure and its performance is studied in some detail. To assess the approach interactive flowfields generated by unswept sharp fins at two angles of attack at each of three hyprsonic freestream Mach numbers (5, 6, 11) have been calculated and the results compared with experimental wall pressure and heat transfer data. Although the conical Navier-Stokes/Baldwin-Lomax approach is reasonably successful at Mach numbers up to 5, the performance deteriorates as the Mach number is increased. Nevertheless, the approach could be a valuable tool in preliminary parametric design studies.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-5050 , AIAA, International Aerospace Planes Conference; Dec 01, 1992 - Dec 04, 1992; Orlando, FL; United States|; 17 p.
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    Comparative study of turbulence models in predicting hypersonic inlet flows (1992)
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    Publication Date: 2019-08-28
    Description: A numerical study was conducted to analyze the performance of different turbulence models when applied to the hypersonic NASA P8 inlet. Computational results from the PARC2D code, which solves the full two-dimensional Reynolds-averaged Navier-Stokes equation, were compared with experimental data. The zero-equation models considered for the study were the Baldwin-Lomax model, the Thomas model, and a combination of the Baldwin-Lomax and Thomas models; the two-equation models considered were the Chien model, the Speziale model (both low Reynolds number), and the Launder and Spalding model (high Reynolds number). The Thomas model performed best among the zero-equation models, and predicted good pressure distributions. The Chien and Speziale models compared wery well with the experimental data, and performed better than the Thomas model near the walls.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-3098
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  • 45
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    Numerical simulations using a dynamic solution-adaptive grid algorithm, with applications to unsteady internal flows (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: An investigation into the numerical simulation of unsteady flows is undertaken using a two-stage Runge-Kutta scheme coupled with the dynamic solution-adaptive grid algorithm developed by the authors. The inviscid fluxes are described by a modified Advective Upwind Split Method to eliminate the need for artificial dissipation. A well-documented numerical example containing moving discontinuities is presented that demonstrates the ability of the coupled grid/solver scheme to accurately capture unsteady flowfield phenomena. Applications are to a typical inlet diffuser configuration at Mach 3.0 with excessive back pressure inducing inlet unstart.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2719 , AIAA Applied Aerodynamics Conference; Jun 22, 1992 - Jun 24, 1992; Palo Alto, CA; United States
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  • 46
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    Direct simulation of re-entry flows with ionization (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 6; 3 Ju; 400-404
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  • 47
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    Scramjet thrust measurement in a shock tunnel (1995)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: This note reports tests in a shock tunnel in which a fully integrated scamjet configuration produced net thrust. The experiments not only showed that impluse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number flows at such speeds.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 99; 984; p. 161-163
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  • 48
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    Hypersonic flow past open cavities (1994)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The hypersonic flow over a cavity is investigated. The time-dependent compressible Navier-Stokes equations are numerically solved. An implicit algorithm, with a subiteration procedure to recover time accuracy, is used to perform the time-accurate computations. The objective of the study is to investigate the effects of Reynolds number and cavity dimensions. The comparsion of the computations with available experimental data, in terms of time mean static pressure, heat transfer, and Mach number, show good agreement. In the computations large vortex structures, which adversely affect the cavity flow characteristics, are observed at the rear of the cavity. A self-sustained oscillatory motion occurs within the cavity over a range of Reynolds number and cavity dimensions. The frequency spectra of the oscillations show good agreement with a modified semiempirical relation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 32; 12; p. 2387-2393
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  • 49
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    Scientific Balloons (1991)
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    Publication Date: 2019-08-28
    Description: This video discusses how NASA uses large helium-filled balloons to take payloads up 25 miles to the edge of space to gather data. Balloons provide a cost effective approach to reach these heights.
    Keywords: AERODYNAMICS
    Type: NASA-TM-109907 , NONP-NASA-VT-94-23149 , ASR-258
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    A summary of the forebody high-angle-of-attack aerodynamics research on the F-18 and the X-29A aircraft (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: High-angle-of-attack aerodynamic studies have been conducted on both the F18 High Alpha Research Vehicle (HARV) and the X-29A aircraft. Data obtained include on- and off-surface flow visualization and static pressure measurements on the forebody. Comparisons of similar results are made between the two aircraft where possible. The forebody shapes of the two aircraft are different and the X-29A forebody flow is affected by the addition of nose strakes and a flight test noseboom. The forebody flow field of the F-18 HARV is fairly symmetric at zero sideslip and has distinct, well-defined vortices. The X-29A forebody vortices are more diffuse and are sometimes asymmetric at zero sideslip. These asymmetries correlate with observed zero-sideslip aircraft yawing moments.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 921996 , SAE, Aerotech ''92 Conference; Oct 05, 1992 - Oct 08, 1992; Anaheim, CA; United States|; 19 p.
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