A Method of Characteristics Computer Program for Three-Dimensional Supersonic Internal Flows

Abstract

The reference-plane method of characteristics is applied to the computation of the supersonic flow in a three-dimensional (3-D) channel such as a propulsion nozzle. The fluid is assumed to be an inviscid ideal gas and the flow is assumed to be shock-free, although it can be rotational. Both the basic equations and the numerical procedures are described, as is the computer program, which was written in FORTRAN IV language for the IBM 370/165 computer. The validity of the computer program was established by computing, in various ways, an axisymmetric nozzle flow as a three-dimensional flow; the numerical results are in good agreement with the results from a well-established computer program for axisymmetric flow.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1979
Accession Number
ADA063518

Entities

People

  • W. C. Armstrong

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Cartesian Coordinates
  • Computational Fluid Dynamics
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Differential Equations
  • Engineering
  • Equations
  • Equations Of Motion
  • Flow Fields
  • Mach Number
  • Method Of Characteristics
  • Networks
  • Operating Systems
  • Three Dimensional
  • United States

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Computer Science.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight