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  • Other Sources  (6)
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  • 1
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    Navier-Stokes computations of a prolate spheroid at angle of attack (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 986-993
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The 3-D Euler and Navier-Stokes calculations for aircraft components (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An explicit multistage Runge-Kutta type of time-stepping scheme is used for solving transonic flow past a transport type wing/fuselage configuration. Solutions for both Euler and Navier-Stokes equations are obtained for quantitative assessment of boundary layer interaction effects. The viscous solutions are obtained on both a medium resolution grid of approximately 270,000 points and a find grid of 460,000 points to assess the effects of grid density on the solution. Computed pressure distributions are compared with the experimental data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 571-579
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Recent advances in Runge-Kutta schemes for solving 3-D Navier-Stokes equations (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A thin-layer Navier-Stokes has been developed for solving high Reynolds number, turbulent flows past aircraft components under transonic flow conditions. The computer code has been validated through data comparisons for flow past isolated wings, wing-body configurations, prolate spheroids and wings mounted inside wind-tunnels. The basic code employs an explicit Runge-Kutta time-stepping scheme to obtain steady state solution to the unsteady governing equations. Significant gain in the efficiency of the code has been obtained by implementing a multigrid acceleration technique to achieve steady-state solutions. The improved efficiency of the code has made it feasible to conduct grid-refinement and turbulence model studies in a reasonable amount of computer time. The non-equilibrium turbulence model of Johnson and King has been extended to three-dimensional flows and excellent agreement with pressure data has been obtained for transonic separated flow over a transport type of wing.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 1: Sessions 1-6; p 207-221
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Prediction of separated transonic wing flows with nonequilibrium algebraic turbulence model (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 28; 1426-143
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Prediction of separated transonic wing flows with a non-equilibrium algebraic model (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A nonequilibrium algebraic turbulence model, which is based on the turbulence closure scheme of Johnson and King (1985), is proposed to predict separated transonic wing flows. The influence of history effects are modeled by solving a partial differential equation for the maximum total Reynolds shear stress, which is then used to scale the eddy viscosity of an algebraic model. The turbulence model is implemented in a three-dimensional, Reynolds-averaged Navier-Stokes code. Comparisons with experimental data are presented which show clearly that the nonequilibrium type of turbulence model is essential for accurate prediction of transonic separated flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0558
    Format: text
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  • 6
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    Development of an efficient multigrid code for 3-D Navier-Stokes equations (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A multigrid acceleration technique has been developed to solve the three-dimensional Navier-Stokes equations efficiently. An explicit multistage Runge-Kutta type of time-stepping scheme is used as the basic algorithm in conjunction with the multigrid scheme. Solutions for flow over a finite wing have been obtained on extremely fine meshes in order to achieve grid convergence of the solutions. Present solutions indicate that the number of multigrid cycles required to achieve a given level of convergence does not increase with the number of mesh points employed, making it a very attractive scheme for fine meshes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 89-1791
    Format: text
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