Wind Tunnel Tests of Space Shuttle Solid Rocket Booster Insulation Material in the Aerothermal Tunnel C.

Abstract

For these wind tunnel tests, conducted in the von Karman Gas Dynamics Facility Tunnel C, the tunnel was run at Mach 4 with a total temperature of 1100-1440 F and a total pressure of 100 psia. Cold wall heating rates were changed by varying the test article support wedge angle. Selected results are presented to illustrate the test techniques and typical data obtained.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1982
Accession Number
ADA130031

Entities

People

  • A. S. Hartman
  • K. W. Nutt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Booster Rocket Engines
  • Boundary Layer
  • Cameras
  • Data Reduction
  • Gas Dynamics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Measurement
  • Photographs
  • Plastic Explosives
  • Space Shuttles
  • Test Facilities
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster