Numerical Study of Supersonic Flows Using Different Techniques.

Abstract

The purpose of this work was to obtain the solution to three supersonic flow problems using three different numerical techniques. First, a shock/boundary layer problem is solved using MacCormack's explicit technique. Then, using the same technique a shrouded rocket nozzle problem is solved. These two problems showed that the explicit scheme required many minutes of computer time to solve. In order to explore more efficient codes to solve the shroud problem, space marching algorithms were studied. A space marching algorithm using flux-splitting in the streamwise direction was applied to an approximate form of the Navier-Stokes equation. Flux-splitting combined with a global interation approach should allow the shroud problem to be solved with a space marching algorithm. The flux-splitting code was applied to two supersonic flow problems and very good results were obtained. (Author) (Theses).

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1986
Accession Number
ADA179113

Entities

People

  • Gary W. Huband

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Engineering
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Gas Turbine Nozzles
  • Navier Stokes Equations
  • Rocket Nozzles
  • Shock Waves
  • Steady State
  • Supersonic Flow
  • Three Dimensional
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Space
  • Space - Hall-Effect Thruster