Wind Tunnel Tests of the NASA Shuttle External Tank SLA/SOFI Panels at Mach Numbers from 0.60 to 1.50.

Abstract

A test was conducted to determine whether exposure of the Super Light Ablator/Spray-on-Foam Insulation (SLA/SOFI) to the STS-1 launch trajectory dynamic pressures would produce additional cracks or cause separations from the cryogenic tank. Low-speed movies and stereo-photography were used to record the effects of the tunnel flow at free-stream Mach numbers from 0.60 to 1.50. Four configurations were tested in the Propulsion Wind Tunnel (16T) during the period from March 20 through 21, 1981. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1981
Accession Number
ADA114678

Entities

People

  • R. G. Meyer

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Cameras
  • Dynamic Pressure
  • Engineering
  • Free Stream
  • Instrumentation
  • Mach Number
  • Measurement
  • Photographs
  • Photography
  • Plastic Explosives
  • Stagnation Temperature
  • Standards
  • Static Pressure
  • Test Facilities
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Fluid Dynamics.
  • Surface Coatings Technology.

Technology Areas

  • Microelectronics