Heat-Transfer Tests of the NASA/Rockwell International Space Shuttle Orbiter (OH-84B), IH-102, and OH-105)

Abstract

Heat transfer tests were conducted on two 0.0175 scale and one 0.04 scale models of the space shuttle orbiter using the thin-skin thermocouple technique. Data were recorded at Mach numbers 3 and 4 in the AEDC-VKF Supersonic Wind Tunnel A and at Mach 8 in the Hypersonic Tunnel B. Ten model configurations were tested including each orbiter model and the two 0,0175 scale models integrated with the external tank and both solid rocket boosters. The objective of the test was to obtain heating data in regions of the orbiter where no previous data exist or where data extrapolation was not feasible. The model angle of attack ranged from -40 to 40 degrees with yaw angles varying from -15 to 10 degrees.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1979
Accession Number
ADA083142

Entities

People

  • A. C. Mansfield
  • G. L. Dommerman
  • K. W. Nutt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Booster Rocket Engines
  • Data Reduction
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Photographs
  • Photography
  • Scale Models
  • Space Shuttles
  • Supersonic Wind Tunnels
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster