Wind Tunnel Tests of the Space Shuttle External Tank Insulation Material at Elevated Heat Flux Conditions

摘要

Wind tunnel tests of the space shuttle External Tank Foam Insulation were conducted in the von Karman Gas Dynamics Facility Tunnel C. The tests were conducted in two entries. On the first entry, Tunnel C was run at Mach 4 with a total temperature of 1030-1150 F and a total pressure which varied from 30-180 psia. Cold wall heating rates were changed by varying the wedge angle and by adding and removing a shock generator or a cylindrical protuberance. The second entry was conducted at Mach 10 with a total temperature of 1140 F and a total pressure of 1750 psia. Selected results from both entries are presented to illustrate the test techniques and typical data obtained. (Author)