Aerodynamic heating in large cavities in an array of RSI [reusable surface insulation] tiles
L. Roane Hunt, United States. National Aeronautics and Space Administration, Langley Research Center
National Aeronautics and Space Administration, 1977 - Crafts & Hobbies - 36 pages
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20 MW Semi-Elliptical 8-foot high-temperature structures aerodynamic exposure Aeronaut aerothermal testing Ames 20 MW angle of attack beneath the tile boundary layer cavity floor cavity heating rates Charred Nomex/RTV bond closed cavity flow covered with SIP displacement thick double lost-tile cavities double-tile cavity downstream wall dynamic pressure edge of tile eroded figure 13 floor of cavity flow separation free shear layer free-stream Mach number high-temperature structures tunnel Hypersonic Langley 8-foot high-temperature Langley Research Center layers of RTV location Q maximum surface temperature mullite tile NASA TN Nomex SIP normal surface heating number of 6.6 number per meter open cavity flow primary structure radiant heating reference 11 Reynolds number Riemann Zeta Function RSI surrounding RSI tile separated flow attached shear stress shuttle entry single-tile cavity space shuttle strain isolator stream structural skin surface insulation RSI temperature histories tests were conducted thermocouple tile array Turbulent Flow