Abstract
This paper reviews recent applications of trajectory-based analysis to the aerodynamic heating environment for some entry capsules, specifically MUSES-C, Stardust, and Pioneer-Venus probes. In order to explain unexpected problems observed during the entry flight of Pioneer-Venus and Galileo probe, this analysis method solves thermochemical nonequilibrium flowfield by the computational fluid dynamics code that is coupled loosely with the ablation module and radiation module along the entry trajectory. The effect of early transition of boundary layer due to ablation products gas is also considered in this approach. The assessment of this analysis method and the difficulty of reproducing thermal response of ablator are reviewed.
