摘要: A series of wind tunnel tests have been performed on an aerospike-protected missile dome at a Mach number of 6 to obtain quantitative surface pressure and temperature-rise data, as well as qualitative flow visualization data. Thes... 展开
| 作者 | L. D. Huebner A. M. Mitchell E. J. Boudreaux | ||
|---|---|---|---|
| 原报告号 | N20040111232 | 总页数 | 11 |
| 主办者 | National Aeronautics and Space Administration | ||
| 报告分类号 | [51A - Aerodynamics , 84E - Space Launch Vehicles & Support Equipment , 75 - Missile Technology ] | ||
| 报告类别/文献类型 | NASA / NTIS科技报告 | ||
| 关键词 | Aerospike engines Angle of attack Calibration Computational fluid dynamics Flow visualization Guided missiles Hypersonic vehicles Mach number Missiles Reynolds number Test facilities Wind tunnel tests | ||
