Wind Tunnel Tests of Elevon Gap Heating on the Space Shuttle Orbiter (OH-107)

Abstract

Tests were conducted in the AEDC/VKF Hypersonic Wind Tunnel (B) to obtain heat-transfer rate measurements in the elevon/elevon and elevon/fuselage gap areas of the Space Shuttle Orbiter. Data were obtained at Mach 8 over a Reynolds number range from 0.5 to 3.7 million per foot. Angles of attack of 30, 35, and 40 deg were run for yaw angles of 0 and 1 deg.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1981
Accession Number
ADA107287

Entities

People

  • D. W. Stallings

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Boundary Layer
  • Control Systems
  • Engineering
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Measurement
  • Research Facilities
  • Reynolds Number
  • Space Shuttles
  • Test Facilities
  • Uncertainty
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering.
  • Fluid Dynamics.

Technology Areas

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