SHOCK PROFILES IN HYPERSONIC FLOW OF A RELAXING GAS ABOUT A WEDGE,

Abstract

A small-perturbation technique is used to give the change in the shock inclination on a thin wedge in steady, two-dimensional, hypersonic flow. This change in shock angle is due to either dissociation or a lagging vibrational heat capacity in the flow behind the bow shock-wave. The problem is solved by transferring the physical domain into a 'piston' plane with one less space dimension. The resulting unsteady, one-dimensional problem is solved here. A general result is obtained giving the shock perturbation as a function of the unperturbed-flow parameters, body shape and equilibrium conditions behind the shock. An expression for the final shock inclination is given in closed form. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1961
Accession Number
AD0608879

Entities

People

  • Frederick R. Dressler

Organizations

  • Cornell University College of Engineering

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Bow Shock
  • Dissociation
  • Flow
  • Heat Capacity
  • Hypersonic Flow
  • Perturbations
  • Physical Properties
  • Shock
  • Shock Waves
  • Two Dimensional
  • Waves

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris