摘要
Long-range aerodynamic heating is a key scientific problem. In this paper, the cone-derived waverider is designed firstly and then the characteristics of the heat flux distribution along the leading edge and on the lower surface of the waverider are studied by means of the high enthalpy wind tunnel test and the high temperature chemical non-equilibrium aerodynamic heating numerical calculation. Results show that: The high heat flux mainly concentrates on the small region around the stagnation point and the change of angle of attack (0°~6°) does not have an obvious effect on the high heat flux region at the leading edge, but it induces a significant increase of the heat flux on the lower surface. In addition, the change of the sideslip angle (0°~4°) has a significant effect on the heat flux at the leading edge, so it is not recommended to fly with a large sideslip angle.
| 投稿的翻译标题 | Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel |
|---|---|
| 源语言 | 繁体中文 |
| 页（从-至） | 52-57 |
| 页数 | 6 |
| 期刊 | Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics |
| 卷 | 33 |
| 期 | 4 |
| DOI | |
| 出版状态 | 已出版 - 1 8月 2019 |
关键词
- Aero-heating
- High enthalpy wind-tunnel test
- Numeri-cal simulation
- Real gas effect
- Waverider