Wind Tunnel Tests of the NASA Shuttle External Tank SLA/SOFI Panels at Mach Numbers from 0.60 to 1.50.
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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A test was conducted to determine whether exposure of the Super Light AblatorSpray-on-Foam Insulation SLASOFI 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
- Adhesives, Seals and Binders
- Unmanned Spacecraft