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Multigrid for hypersonic viscous two- and three-dimensional flowsThe use of a multigrid method with central differencing to solve the Navier-Stokes equations for hypersonic flows is considered. The time-dependent form of the equations is integrated with an explicit Runge-Kutta scheme accelerated by local time stepping and implicit residual smoothing. Variable coefficients are developed for the implicit process that remove the diffusion limit on the time step, producing significant improvement in convergence. A numerical dissipation formulation that provides good shock-capturing capability for hypersonic flows is presented. This formulation is shown to be a crucial aspect of the multigrid method. Solutions are given for two-dimensional viscous flow over a NACA 0012 airfoil and three-dimensional viscous flow over a blunt biconic.
Document ID
19910056123
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Turkel, E.
(Tel Aviv University Israel)
Swanson, R. C.
(Tel-Aviv Univ. Ramat-Aviv, Tel-Aviv, Israel)
Vatsa, V. N.
(NASA Langley Research Center Hampton, VA, United States)
White, J. A.
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-1572
Meeting Information
Meeting: AIAA Computational Fluid Dynamics Conference
Location: Honolulu, HI
Country: United States
Start Date: June 24, 1991
End Date: June 27, 1991
Accession Number
91A40746
Distribution Limits
Public
Copyright
Other

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