ANALYSIS OF THREE-DIMENSIONAL SCRAMJET EXHAUST NOZZLE FLOW FIELDS BY A NEW SECOND-ORDER METHOD OF CHARACTERISTICS,

Abstract

In this paper a new second-order numerical method of characteristics for calculation of three-dimensional steady supersonic flow is described. The method has been programmed for the CDC 6500 and IBM 7094 computers. Numerical results have been obtained which verify the second order numerical accuracy and the numerical stability of the scheme. In addition, computed results for an axisymmetric nozzle are compared with the solution obtained using a two independent variable method of characteristics program and the two results are found to be in good agreement. The numerical solution for the flow in a representative three-dimensional nozzle is presented. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1969
Accession Number
AD0685981

Entities

People

  • H. Doyle Thompson
  • Jason Hoffman
  • V. H. Ransom

Organizations

  • Purdue University

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Agreements
  • Air Force
  • Axisymmetric
  • Computers
  • Exhaust Nozzles
  • Flow
  • Flow Fields
  • Method Of Characteristics
  • New York
  • Nozzles
  • Supersonic Flow
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow