Performance of a mullite reusable surface insulation system in a hypersonic stream
National Aeronautics and Space Administration, 1976 - Reusable space vehicles - 37 pages
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8-foot high-temperature structures acoustic baffles aerodynamic exposure aerodynamic heating test Aerothermal tests angle of attack bond-line temperature coating cracked cracked and flaked craters damaged areas dynamic pressure exposed to hypersonic facility figure 17 flaked with thermal flow shear forward-facing steps free-stream Mach number gaps and withstood heatup high-temperature structures tunnel hypersonic flow infrared radiometer Langley 8-foot high-temperature Langley Research Center mullite insulation mullite panel MULLITE REUSABLE SURFACE mullite TPS NASA NASA TN number of 4.6 omniweave gap filler panel holder panel surface panel was designed particle impact Posttest present tests primary structure represent a portion Reusable Surface Insulation shown in figure Space Shuttle Stiffener Stringer surface temperature history temperature distribution test 13 test panel test stream tests were conducted thermal and structural thermal cycles Thermal Protection Thermal Protection Systems Thermal response thermocouples tile gap tile surface total temperature unit Reynolds number wind tunnel withstood the flow woven silica fibers