COMPARISON OF EQUILIBRIUM AND FROZEN FLOW PROPERTIES OF AIR IN A HYPERSONIC WIND TUNNEL.

Abstract

A hypersonic true temperature wind tunnel using air as the working gas at supply temperatures from 2000 K to 8000 K, and supply pressures of 5 to 150 atmospheres, is analyzed to show the effects of nonequilibrium flow on the sizing of the tunnel components. It was found that nonequilibrium flow requires the use of larger nozzles and more pumping capacity than is needed for equivlanet equilibrium conditions. The methods used and the results obtained are described in some detail. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 18, 1965
Accession Number
AD0483832

Entities

People

  • Arthur F. Moore

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Atmospheres
  • Buildings And Structures
  • Flow
  • Hypersonic Wind Tunnels
  • Nonequilibrium Flow
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

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