Supersonic and Subsonic Wind Tunnel Heat-Transfer Measurements in the Base Cavity Region of the Shuttle Solid Rocket Booster during Simulated Reentry.

Abstract

Tests were conducted on the aft section of the Space Shuttle Solid Rocket Booster at Mach numbers 3.75 and 0.5 at selected angles of attack from 90-180 deg simulating reentry attitudes. The tests wre conducted in the AEDC Supersonic Wind Tunnel A to obtain heat-transfer coefficients in the base cavity region. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1982
Accession Number
ADA125499

Entities

People

  • K. W. Nutt
  • W. R. Hawkins

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Booster Rocket Engines
  • Boundary Layer
  • Coefficients
  • Data Reduction
  • Free Stream
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Mach Number
  • Measurement
  • Research Facilities
  • Rockets
  • Test Facilities
  • Uncertainty
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Rocket Propulsion.

Technology Areas

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