Convergence acceleration of an aeroelastic navier-stokes solver

Shigeru Obayashi; Guru P. Guruswamy

Convergence acceleration of an aeroelastic navier-stokes solver

Research output: Contribution to conference › Paper › peer-review

Abstract

New capabilities have been added to a Navier-Stokes solver to perform steady-state simulations more efficiently. The flow solver for solving the Navier-Stokes equations is completely rewritten with a combination of the LU-SGS (Lower-Upper factored Symmetric Gauss-Seidel) implicit method and the modified HLLE (Harten-Lax-van Leer-Einfeldt) upwind scheme. A pseudo-time marching method is used for the directly coupled structural equations to improve overall convergence rates for static aeroelastic analysis. Results are demonstrated for transonic flows over rigid and flexible wings.

Original language	English
Publication status	Published - 1994
Externally published	Yes
Event	AIAA Fluid Dynamics Conference, 1994 - Colorado Springs, United States Duration: 1994 Jun 20 → 1994 Jun 23

Other

Other	AIAA Fluid Dynamics Conference, 1994
Country/Territory	United States
City	Colorado Springs
Period	94/6/20 → 94/6/23

ASJC Scopus subject areas

Aerospace Engineering
Engineering (miscellaneous)

Cite this

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title = "Convergence acceleration of an aeroelastic navier-stokes solver",

abstract = "New capabilities have been added to a Navier-Stokes solver to perform steady-state simulations more efficiently. The flow solver for solving the Navier-Stokes equations is completely rewritten with a combination of the LU-SGS (Lower-Upper factored Symmetric Gauss-Seidel) implicit method and the modified HLLE (Harten-Lax-van Leer-Einfeldt) upwind scheme. A pseudo-time marching method is used for the directly coupled structural equations to improve overall convergence rates for static aeroelastic analysis. Results are demonstrated for transonic flows over rigid and flexible wings.",

author = "Shigeru Obayashi and Guruswamy, {Guru P.}",

note = "Funding Information: The first author?s work was supported by National Aeronautics and Space AdministrationNASA Grant NCC 2-605. The computer time was partly provided by Numerical Aerodynamic Simulator (NAS) program located at the NASA Ames Research Center. Publisher Copyright: {\textcopyright} 1994 by the American Institute of Aeronautics and Astronautics, Inc.; AIAA Fluid Dynamics Conference, 1994 ; Conference date: 20-06-1994 Through 23-06-1994",

year = "1994",

language = "English",

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T1 - Convergence acceleration of an aeroelastic navier-stokes solver

AU - Obayashi, Shigeru

AU - Guruswamy, Guru P.

N1 - Funding Information: The first author?s work was supported by National Aeronautics and Space AdministrationNASA Grant NCC 2-605. The computer time was partly provided by Numerical Aerodynamic Simulator (NAS) program located at the NASA Ames Research Center. Publisher Copyright: © 1994 by the American Institute of Aeronautics and Astronautics, Inc.

PY - 1994

Y1 - 1994

N2 - New capabilities have been added to a Navier-Stokes solver to perform steady-state simulations more efficiently. The flow solver for solving the Navier-Stokes equations is completely rewritten with a combination of the LU-SGS (Lower-Upper factored Symmetric Gauss-Seidel) implicit method and the modified HLLE (Harten-Lax-van Leer-Einfeldt) upwind scheme. A pseudo-time marching method is used for the directly coupled structural equations to improve overall convergence rates for static aeroelastic analysis. Results are demonstrated for transonic flows over rigid and flexible wings.

AB - New capabilities have been added to a Navier-Stokes solver to perform steady-state simulations more efficiently. The flow solver for solving the Navier-Stokes equations is completely rewritten with a combination of the LU-SGS (Lower-Upper factored Symmetric Gauss-Seidel) implicit method and the modified HLLE (Harten-Lax-van Leer-Einfeldt) upwind scheme. A pseudo-time marching method is used for the directly coupled structural equations to improve overall convergence rates for static aeroelastic analysis. Results are demonstrated for transonic flows over rigid and flexible wings.

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T2 - AIAA Fluid Dynamics Conference, 1994

Y2 - 20 June 1994 through 23 June 1994

ER -

Convergence acceleration of an aeroelastic navier-stokes solver

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ASJC Scopus subject areas

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