On the Simulation of Transonic Shock-Turbulent Boundary Layer Interactions in Cryogenic or Heavy Gas Wind Tunnels,

Abstract

The role of the basic similitude parameters governing transonic normal shock-turbulent boundary layer interaction effects in cryogenic wind tunnel tests is studied theoretically for the non-separating case. Besides Mach and Reynolds number, these parameters are the wall to total temperatures ratio, specific heat ratio gamma, viscosity-temperature exponent and Prandtl number. The results show that lack of temperature ratio simulation has a significantly adverse effect on interactive skin friction and hence separation onset compared to the adiabatic free flight case; higher gamma's than air also may have some effect. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1978
Accession Number
ADA052830

Entities

People

  • George R. Inger

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Engineering
  • Flow
  • Fluid Dynamics
  • Heat Transfer
  • Prandtl Number
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Simulations
  • Skin Friction
  • Specific Heat
  • Test Facilities
  • Thermophysical Properties
  • Turbulent Boundary Layer
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.