摘要
At high altitude, the flow field of hypervelocity reentry vehicle is in a strong state of thermochemical nonequilibrium. In the present study, calculations of hypersonic flow fields over three typical blunt-cone vehicles of twenty-one cases are carried out by using three-dimensional Navier-Stokes equations with gas molecular vibrational excitations and chemical reactions. The computed aeroheating environments are in good agreement with experiment results and flight data, and these aerothermodynamics predictions are useful for achieving successful early thermal protection system (TPS) designs of the entry vehicle.
| 源语言 | 英语 |
|---|---|
| 主期刊名 | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference |
| 出版状态 | 已出版 - 2009 |
| 活动 | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, 德国 期限: 19 10月 2009 → 22 10月 2009 |
出版系列
| 姓名 | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference |
|---|
会议
| 会议 | 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference |
|---|---|
| 国家/地区 | 德国 |
| 市 | Bremen |
| 时期 | 19/10/09 → 22/10/09 |
指纹
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Li, X., & Wang, B. G. (2009). CFD prediction of hypersonic blunt-cone configurations of multiple cases. 在 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 文章 2009-7385 (16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference).