THE HYPERSONIC APPROXIMATION FOR THE SHOCK STRUCTURE OF A PERFECT GAS WITH THE SUTHERLAND VISCOSITY LAW

Abstract

The classical Navier-Stokes treatment of the shock wave strucure is investigated for a perfect gas with constant specific heats. The viscosity of the gas is presribed according to the Sutherland law. he Prandtl number is 3/4. The limiting forms of the solution as the upstream flow Mach number approaches infinity, with all other parameters held fixed, is studied. two distinct asymptotic seies are found for the portions of the shok adjacent to the uniform regions upstrem and downstream of the shok and these expansions re matched in an intermediate region of common validity. The leading terms of a uniformly valid expansion are otained by combining elements from both expansions. Special attention s given to the entropy and the entropy production rate in the shock wave. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1962
Accession Number
AD0275884

Entities

People

  • William B. Bush

Organizations

  • California Institute of Technology

Tags

DTIC Thesaurus Topics

  • Mach Number
  • Physical Properties
  • Prandtl Number
  • Production
  • Production Rate
  • Shock
  • Shock Waves
  • Specific Heat
  • Viscosity
  • Waves

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Mechanics and Fluid Dynamics.
  • Statistical inference.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow