Abstract
A unified CFD method is developed that integrates numerical methods for solving specific problems related to aerodynamic heating phenomena and ablative heatshield. Using this unified CFD code, trajectory-based analysis on the aerodynamic heating environment for the MUSES-C super-orbital reentry capsule is conducted. Converged solutions can be obtained by loosely coupling CFD code and CMA code within a few iterations. The results show that the wall surface temperature in the downstream region is significantly elevated by the effect of turbulence due to ablation product gas. Wall temperature as well as the recession rate at the stagnation point along the entry trajectory is found to duplicate well with the existing predictions.
| Original language | English |
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| Publication status | Published - 2001 Dec 1 |
| Event | 39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: 2001 Jan 8 → 2001 Jan 11 |
Other
| Other | 39th Aerospace Sciences Meeting and Exhibit 2001 |
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| Country/Territory | United States |
| City | Reno, NV |
| Period | 01/1/8 → 01/1/11 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering