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
ablation AIAA AIAA Paper analysis angle of attack approximately boundary boundary-layer calculated calorimeter carbon carbon-carbon catalytic centerline coefficient comparison concept configuration correlation eddy viscosity edge effects enthalpy entry heating environment equations equilibrium factor flight data flow flowfield forebody freestream fuselage gage Galileo Probe gap heating gap width gradient heat flux heat shield Heat Transfer heating rates HRSI interface inviscid kg probe laminar layer loads Mach number mass loss rate material measured meteoroid NASA nonequilibrium nose cap obtained panel particle payload predictions present pressure primary shield radiation radiative recombination region reinforced carbon-carbon Reynolds number secondary shield shock shown in Fig solar solutions Space Shuttle Orbiter spacecraft spallation stagnation point STARPROBE structure STS-2 flight superalloy surface temperature thermal protection system thermocouple thickness tile gap tion trajectory turbulent values vehicle velocity viscous shock-layer wind-tunnel windward