Entry Vehicle Heating and Thermal Protection Systems: Space Shuttle, Solar Starprobe, Jupiter Galileo ProbePaul E. Bauer, Howard E. Collicott |
Contents
Aerothermodynamic Entry Environment | 3 |
xi | 21 |
Viscous ShockLayer Predictions for Hypersonic Laminar | 54 |
Copyright | |
30 other sections not shown
Common terms and phrases
AIAA analysis angle approximately assumed attachment body boundary boundary-layer calculated carbon carbon-carbon catalytic Center coating compared comparison components concept conducted configuration considered correlation determined developed edge effects energy entry environment equations equilibrium experiment experimental factor Figure flight data flow flowfield fuselage given heat flux heat shield Heat Transfer heating rates increase indicate insulation laminar layer loads lower mass loss material maximum measured method NASA nonequilibrium nose obtained Orbiter outer panel particle performance plane predictions present pressure primary shield probe properties radiation region relative Research response selected shock shown in Fig shows solar solutions Space Shuttle spacecraft structure surface surface temperature Table temperature thermal thermal protection thermocouple thickness tile tion trajectory turbulent values vehicle viscosity wall wing