Aerothermal and structural performance of a cobalt-base superalloy thermal protection system at Mach 6.6 |
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8-foot high-temperature structures acoustic baffles aerodynamic heating Aerothermal 1145 aerothermal performance aerothermal tests allowed for thermal angle of attack arcing bolted cooling corrugation-stiffened skin corrugations deflectometer differential pressure drag support frequencies Glasrock high-temperature structures tunnel hot gas flow hypersonic inconel foil insulation packages L-shaped clip Langley 8-foot high-temperature Langley Research Center leading edge Leading-edge fairing locations metallic thermal protection mounted NASA TN obtained panel holder Panel skin panel surface preheat prevent hot gas psi kPa psi radiant and aerothermal radiant lamps seam welded shingle-slip joint supports shown in figure side-edge seals skin and supports spot welded static-load deflection stream streamwise stiffeners structural integrity subjected to 32 support brackets temperature distributions temperature histories temperature time histories test panel test series thermal analysis thermal cycle thermal expansion thermal insulation thermal protection system thermocouple titanium sheet TPS cavity TPS was subjected U.S. Customary Units unit Reynolds number vehicle primary structure wind tunnel