Extension of Multigrid Methodology to Supersonic/Hypersonic 3-D Viscous Flows

Abstract

A multigrid acceleration technique developed for solving the three dimensional Navier-Stokes equations for subsonic/transonic flows has been extended to supersonic/hypersonic flows. An explicit multistage Runge Kutta type of time-stepping scheme is used as the basic algorithm in conjunction with the multigrid scheme. Solutions have been obtained for a blunt conical frustum at Mach 6 to demonstrate the applicability of the multigrid scheme to high speed flows. Computations have also been performed for a generic High-Speed Civil Transport configuration designed to cruise at Mach 3. These solutions demonstrate both the efficiency and accuracy of the present scheme for computing high-speed viscous flows over configurations of practical interest.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1991
Accession Number
ADA240396

Entities

People

  • Eli Turkel
  • J. S. Abolhassani
  • Veer N. Vatsa

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Boundary Layer
  • Computational Fluid Dynamics
  • Equations
  • Experimental Data
  • Flow Visualization
  • Fluid Dynamics
  • Hypersonic Flow
  • Mach Number
  • Navier Stokes Equations
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Steady State
  • Three Dimensional
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics