Entry Heating and Thermal Protection: Technical Papers from the AIAA 17th Aerospace Sciences Meeting, January 1979, and the AIAA 14th Thermophysics Conference, June 1979, Subsequently Revised for this VolumeWalter B. Olstad, American Institute of Aeronautics and Astronautics |
Contents
Methods for Predicting OffStagnationPoint Flowfields for Planetary | 26 |
Nonequilibrium Radiative Heating of a Jovian Entry Body | 83 |
Probe at High Altitudes | 104 |
Copyright | |
11 other sections not shown
Common terms and phrases
ablation absorption AIAA analysis angle approximately assumed atomic average base body boundary layer calculations carbon Center chemical coefficient compared comparison computed considered constant convective correlation coupled density determined developed distance distribution edge effects electron energy enthalpy entry environment equations equilibrium experimental experiments factor Figure flight flow flowfield front function given graphite heat flux heating rates higher hydrogen included increase injection Journal Jovian limit lower Mach number mass material measured method NASA NLTE obtained Orbiter panel parameter peak predicted present pressure probe radiation radiative heating radius ratio region relatively represents shape shock layer shock tube shown in Fig shows solutions Space species spectral stagnation point surface Table temperature theory thermal thickness tion transfer transition transport turbulent uncertainties vapor wall wave