Transonic Flow Computations with Separate Treatment of the Subsonic and Supersonic Regions.

Abstract

The report outlines a method for the computation of transonic flow fields in which one applies a finite element approach to the subsonic region, and the method of characteristic for the supersonic region and matches the two results at the sonic line and at the shock. The equations for the subsonic region can be obtained from Bateman's extremum principle. In each iteration step a preliminary location of the sonic line and of the shock is obtained. A new iteration step computes for this approximation of the sonic line and the given profile contour an exact supersonic flow field, and in addition, still from the supersonic region, the changes which occur in this field at the current sonic line and at the current shock location, if one changes the shape of the sonic line in a systematic manner. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1980
Accession Number
ADA090327

Entities

People

  • Karl G. Guderley

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Applied Mathematics
  • Computations
  • Coordinate Systems
  • Differential Equations
  • Dynamics
  • Equations
  • Flow
  • Flow Fields
  • Government Procurement
  • Governments
  • Grids
  • Mass Flow
  • Mathematics
  • Method Of Characteristics
  • Two Dimensional
  • Universities

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Dynamics.

Technology Areas

  • Hypersonics