THE INVISCID FLOW OF REACTING AND RADIANT AIR PAST A HYPERSONIC BLUNT BODY,

Abstract

The inviscid hypersonic flow around an arbitrary blunt body of revolution has been formulated for machine computation. The highly accurate streamtube continuity method was extended to cover the case of chemically reacting and thermally radiating optically thin air, when the flow is in complete thermodynamic and chemical equilibrium. An extension to the case of opaque air is also given for the special case of a spherical nose of unit surface emissivity. The present schem calculates the flow field well into the pure supersonic region at which point currently existing techniques, such as the method of characteristics, can be applied. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 15, 1960
Accession Number
AD0438261

Entities

People

  • Haim Kennet

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Blunt Bodies
  • Bodies
  • Chemical Equilibrium
  • Computations
  • Continuity
  • Emissivity
  • Flow
  • Flow Fields
  • Hypersonic Flow
  • Inviscid Flow
  • Method Of Characteristics
  • Revolutions

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight