Multigrid for Hypersonic Viscous Two- and Three-Dimensional Flows

Abstract

We consider the use of a multigrid method with central differencing to solve the Navier Stokes equation for hypersonic flows. 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 flow 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.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1991
Accession Number
ADA240707

Entities

People

  • E. Turkel
  • J. A. White
  • R. C. Swansonn
  • V. N. Vatsa

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Bow Shock
  • Computational Fluid Dynamics
  • Computational Science
  • Convection
  • Differential Equations
  • Euler Equations
  • Fluid Dynamics
  • Fluid Flow
  • Hypersonic Flow
  • Mach Number
  • Navier Stokes Equations
  • Skin Friction
  • Three Dimensional
  • Turbulent Flow
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Mathematics
  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics