NUMERICAL SOLUTIONS FOR SUPERSONIC FLOW OF AN IDEAL GAS AROUND BLUNT TWO-DIMENSIONAL BODIES

Abstract

The method described is an inverse one; the shock shape is chosen and th olution oceeds downstream to a body. Bodies blunter an circular cylinders are readily accessible, and any adiabatic index can be chosen. The lower limit to the free-stream Mach number available in any case is determined by the extent of the subsonic field, which in turn depends upon the body shape. Some discussion of the stability of the numerical processes is given. A set of solutions for flows about circular cylinders at several Mach numbers and several values of the adiabatic index is included. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1961
Accession Number
AD0260540

Entities

People

  • Franklyn B. Fuller

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Flow
  • Fluid Flow
  • Free Stream
  • Gas Flow
  • Mach Number
  • Shape
  • Supersonic Flow
  • Two Dimensional

Fields of Study

  • Mathematics
  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers