Space Shuttle Integrated Vehicle Aerodynamic Interference Heating Test (NASA JSC Test IH-97)

Abstract

Wind tunnel tests were conducted on the 0.0175 scale 60-OTS integrated Space Shuttle Vehicle in the von Karman Gas Dynamics Facility Tunnel A. The objectives were to obtain heating data in locations where developmental flight instrumentation (DFI) had been placed on the full scale vehicle and to obtain validation data for the aeroheating design methodology. Data were obtained over the Mach range of 2.25 to 4.00 at free stream unit Reynolds numbers of 3.7 x 10.6 to 5.7 x 10.6 per foot. Model attitude was varied over the range +5 to -5 degrees angle of attack and +6 to -6 degrees angle of side slip.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA128063

Entities

People

  • Kenneth W. Nutt
  • William K. Crain

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Human Systems
  • Weapons Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Boundary Layer
  • Digital Data
  • Engineering
  • Equations
  • Gas Dynamics
  • Heat Energy
  • Heat Transfer
  • Heat Transfer Coefficients
  • Mach Number
  • Measurement
  • Photography
  • Reynolds Number
  • Standards
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Software Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers