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  • 11
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    Numerical studies of unsteady transonic flow over oscillating airfoil (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A finite difference solution to the Navier-Stokes equations combined with a time varying grid generation technique was used to compute unsteady transonic flow over an oscillating airfoil. These computations were compared with experimental data (obtained at Ames Research Center) which form part of the AGARD standard configuration for aeroelastic analysis. A variety of approximations to the full Navier-Stokes equations was used to determine the effect of frequency, shock wave motion, flow separation, and airfoil geometry on unsteady pressures and overall air loads. Good agreement is shown between experiment and theory with the limiting factor being the lack of a reliable turbulence model for high Reynolds number, unsteady transonic flows.
    Keywords: AERODYNAMICS
    Type: AGARD Transonic Unsteady Aerodyn. and its Aeroelastic Appl.; 22 p
    Format: text
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  • 12
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    Calculation of external-internal flow fields for mixed-compression inlets (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Supersonic inlet flows with mixed external-internal compressions were computed using a combined implicit-explicit (Beam-Warming-Steger/MacCormack) method for solving the three-dimensional unsteady, compressible Navier-Stokes equations in conservation form. Numerical calculations were made of various flows related to such inlet operations as the shock-wave intersections, subsonic spillage around the cowl lip, and inlet started versus unstarted conditions. Some of the computed results were compared with wind tunnel data.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88362 , A-86409 , NAS 1.15:88362
    Format: application/pdf
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  • 13
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    Three-dimensional shock-wave/boundary-layer interactions with bleed through a circular hole (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computations were performed to study three-dimensional (3-D), shock-wave/boundary-layer interactions on a flat plate in which fluid in the boundary layer was bled through a circular hole into a plenum to control shock-wave induced separation. Results are presented which show the details of the 3-D flowfield about the bleed hole and how bleed-hole placement relative to shock-wave impingement affect upstream, spanwise, and downstream influence lengths. This study revealed an underlying mechanisms by which bleed holes can affect shock-wave/boundary-layer interactions. This investigation is based on the ensemble-averaged, "full-compressible" Navier-Stokes equations closed by the Baldwin-Lomax turbulence model. Solutions to these equations were obtained by an implicit finite-volume method based on the partially-split, two-factored algorithm of Steger.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 92-3084
    Format: text
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  • 14
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    Laminar flow past a sphere at high Mach number. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Laminar hypersonic flow past sphere based on constant-density approximation, solving Navier- Stokes equations and comparing with values of shock Reynolds number
    Keywords: AERODYNAMICS
    Format: text
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  • 15
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    Laminar flow past a sphere at high mach number (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Hypersonic viscous flow past sphere
    Keywords: AERODYNAMICS
    Type: NASA-CR-64595
    Format: application/pdf
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  • 16
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    Computation of flow around a circular cylinder in a supercritical regime (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Compressible flows around a circular cylinder in a supercritical regime at Mach number 0.3 have been calculated by using the Beam-Warming-Steger scheme based on the full Navier-Stokes equations with improved accuracy. The flow patterns are visualized extensively to observe the characteristics in this regime. The computations show that the flow at certain Reynolds numbers in a supercritical regime becomes rather steady and irregular with small drag coefficients. This may correspond to the experimental observations that the Strouhal number can not be measured clearly at a certain Reynolds number range in the supercritical regime.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1660
    Format: text
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  • 17
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    Random response of rectangular panels to the pressure field beneath a turbulent boundary layer in subsonic flows (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The response of a rectangular panel under the excitation of a turbulent boundary layer with a zero longitudinal mean pressure gradient in a subsonic flow was studied in detail. The method of normal mode was used together with the technique of spectral analysis. Both simply supported and clamped edge conditions of a panel were considered, and the displacement power spectral density of the panel response was computed. The results for the clamped edge panel compare favorably with existing data. Charts of structural acceptance, which provide a framework for estimating the response of other rectangular panels, are presented, and the physical significances of structural acceptances discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6970 , A-4382
    Format: application/pdf
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  • 18
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    Pressure-fluctuation inputs and response of panels underlying attached and separated supersonic turbulent boundary layers (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented for an investigation of surface pressure fluctuations and response of panels underlying attached and separated turbulent boundary layers and shock waves. Tests conducted at transonic and supersonic Mach numbers to 3.6 to study the pressure fields. Assorted fixed edge flat panels were tested at Mach numbers from 1.6 to 3.6 in attached and completely separated flow fields, and also in mixed flow with a step-induced shock wave oscillating on the panels. The surface pressure fluctuations are described in terms of broadband rms, spectral density, and spatial correlation information. The effectiveness of parameters for scaling the pressure fluctuations is also illustrated. Measurements of the amplitude and strain response of the panels are compared with response computations by the normal mode method of analysis.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-62189
    Format: application/pdf
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  • 19
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    Static and dynamic stability analysis of the space shuttle vehicle-orbiter (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The longitudinal static and dynamic stability of a Space Shuttle Vehicle-Orbiter (SSV Orbiter) model is analyzed using the FLEXSTAB computer program. Nonlinear effects are accounted for by application of a correction technique in the FLEXSTAB system; the technique incorporates experimental force and pressure data into the linear aerodynamic theory. A flexible Orbiter model is treated in the static stability analysis for the flight conditions of Mach number 0.9 for rectilinear flight (1 g) and for a pull-up maneuver (2.5 g) at an altitude of 15.24 km. Static stability parameters and structural deformations of the Orbiter are calculated at trim conditions for the dynamic stability analysis, and the characteristics of damping in pitch are investigated for a Mach number range of 0.3 to 1.2. The calculated results for both the static and dynamic stabilities are compared with the available experimental data.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TP-1179 , A-7217
    Format: application/pdf
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  • 20
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    Numerical simulation of three-dimensional supersonic inlet flow fields (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Supersonic inlet flows with mixed external-internal compressions of an axisymmetric inlet model were computed using a combined implicit-explicit (Beam-Warming-Steger/MacCormack) method for solving the three-dimensional unsteady, compressible Navier-Stokes equations in conservation form. Numerical calculations were made of various flows typically found in supersonic inlets such as shock-wave intersections, flow spillage around the cowl lip, shock-wave/boundary-layer interactions, control of shock-induced flow separation by means of boundary layer bleed, internal normal (terminal) shocks, and the effects of flow incidence. Computed results were compared with available wind tunnel data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0160
    Format: text
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