The process of ablation for Earth atmospheric entry is simulated using a computational approach that allows thermo-chemical nonequilibrium of the flow field and ablation gases. The heat pulse into the heat shield is modeled. The flowfield and graphite heat shield are coupled through surface mass and energy balances. The surface thermochemistry involves the oxidation of graphite and allows for catalytic recombination of diatomic oxygen. Steady-state simulations are performed on a one meter nose radius sphere at an altitude of 65 km and at free-stream velocities of 8 km/s and 10 km/s. A transient simulation is performed at 65 km altitude and a free-stream velocity of 10 km/s.
|Original language||English (US)|
|State||Published - 1993|
|Event||AIAA 28th Thermophysics Conference, 1993 - Orlando, United States|
Duration: Jul 6 1993 → Jul 9 1993
|Other||AIAA 28th Thermophysics Conference, 1993|
|Period||7/6/93 → 7/9/93|
Bibliographical noteFunding Information:
This work is supported in part by the following grants: NASA-Langley Grant NCC1-140 and NASA Grant NAGW-1331 to the Mars Mission Research Center at North Carolina State University. Computer time was provided by the North Carolina Supercomputing Center.
© 1993 by the American Institute of Aeronautics and Astronautics, Inc.