CALCULATION OF SUPERSONIC FLOW AROUND AXISYMMETRIC FLARES

Abstract

A machine program for the computation of supersonic flow around an axisymmetric flare is described. The computation consists of the following parts: (1) The oblique shock problem in which upstream flow properties vary with position. (2) Calculation of the initial shock angle at the compression corner. (3) Insertion of characteristics for uniformity of mesh size.

Document Details

Document Type
Technical Report
Publication Date
May 21, 1958
Accession Number
AD0263103

Entities

People

  • H.e. Wohlwill

Organizations

  • TRW Inc.

Tags

DTIC Thesaurus Topics

  • Axisymmetric
  • Compression
  • Computations
  • Flow
  • Fluid Flow
  • Gas Flow
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow