Computation of three Dimensional Viscous Compressible Flow at Hypersonic Velocity.

Abstract

A numerical method to solve the perfect gas Navier-Stokes equations for hypersonic flows past three-dimensional blunt bodies has been developed. The numerical method uses flux-splitting and shock-fitting with an implicit Gauss-Seidel line-relaxation procedure to accelerate convergence. The technique has been used to solve the flow field over a spherically blunted biconic and the X24C-10D hypersonic research vehicle. The method has been shown to reduce the number of iterations required to achieve convergence of a typical problem by a factor of about one hundred over an explicit method. The scheme also shows a potential advantage over approximately factored implicit methods. The key advantage of this technique is that the low number of iterations required for convergence does not increase as mesh resolution is refined. Keywords: Hypersonic vehicles; Algorithms; Numerical methods and procedures; Three dimensional flow; Viscous flow; Compressible flow.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1986
Accession Number
ADA174968

Entities

People

  • Graham V. Candler
  • Robert W. Maccormack

Organizations

  • Stanford University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Bodies
  • Boundary Layer
  • Bow Shock
  • Computational Fluid Dynamics
  • Computational Science
  • Computations
  • Difference Equations
  • Heat Transfer
  • Hypersonic Vehicles
  • Layers
  • Mach Number
  • Navier Stokes Equations
  • Pressure Distribution
  • Shock Waves
  • Temperature Gradients
  • Three Dimensional
  • Vehicles

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics