A trajectory-based analysis on the aerodynamic heating environment for the Stardust Sample Return Capsule is carried out. The 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. Converged solutions are obtained within a few iterations. The present results are compared with that obtained by Olynick et al. Moreover, possible turbulence effect due to ablation product gas is considered. It is found that the calculated heat transfer rates with ablation become comparable with those obtained by Olynick et al., although the wall temperatures are lower than that of Olynick et al. at the higher altitude. The convective heat transfer rate in the downstream region is elevated by the turbulence effect, while the turbulence is found to have a minor effect on the radiative heat transfer rate along the wall surface. It is indicated that the higher heat flux due to turbulence in the downstream region results in the amount of recession that is comparable with that at the stagnation point. However, the calculated amount of recession is at most only 6.3% of the initial ablator thickness which is about 1/3 of that given by Olynick et al.
|出版ステータス||Published - 2002 12 1|
|イベント||40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States|
継続期間: 2002 1 14 → 2002 1 17
|Other||40th AIAA Aerospace Sciences Meeting and Exhibit 2002|
|Period||02/1/14 → 02/1/17|
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