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  • AERODYNAMICS  (16)
  • Aerodynamics  (1)
  • 1
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    Navier-Stokes simulation of flow through a highly contoured subsonic diffuser (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The flow through a highly offset subsonic diffuser with cross-sectional profiles that varied from rectangular at the duct entrance to circular at the engine face was numerically simulated. A multizonal approach combined with a two-grid topology was used to represent both the internal and external flowfields, and an implicit, approximately-factored, partially flux-split finite-difference algorithm was used to solve the three-dimensional thin-layer Navier-Stokes equations. The computed static pressures along the inlet wall and total pressures on the engine face were compared with experimental data. In addition, the overall flowfield within the duct was examined in detail. Good agreement is shown between experiment and computations, with the limiting factor being the lack of a reliable turbulence model for internal flow problems.
    Keywords: AERODYNAMICS
    Type: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 34; 473-483
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  • 2
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    Bleed-boundary conditions for numerically simulated mixed-compression supersonic inlet flow (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: A numerical study was performed to investigate boundary conditions for bleed openings that are needed in the numerical simulation of critical flow through turbojet inlets with bleed. Nine different boundary conditions (BCs) were devised and examined. Of the BCs examined, three were able to stabilize the terminal shock near the inlet's throat. This numerical study was based on the ensemble-averaged, unsteady, three-dimensional, compressible Navier-Stokes equations closed by the Baldwin-Lomax algebraic turbulence model. Solutions to the Navier-Stokes equations were obtained by using a hybrid implicit-explicit method (Beam and Warming/MacCormack). The multiblock grid system used in the solution procedure was generated by solving a set of elliptic partial differential equations. Solutions obtained were compared with available experimental data.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 4, Ju
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  • 3
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    Calculation of external-internal flow fields for mixed-compression inlets (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    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: Computer Methods in Applied Mechanics and Engineering (ISSN 0045-7825); 64; 21-37
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  • 4
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    Navier-Stokes solutions for mixed compression axisymmetric inlet flow with terminal shock (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 4
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  • 5
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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
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  • 6
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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
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  • 7
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    Laminar flow past a sphere at high Mach number. (1966)
    In:  Other Sources
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    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
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  • 8
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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
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  • 9
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    Computation of flow around a circular cylinder in a supercritical regime (1985)
    In:  Other Sources
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    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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  • 10
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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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