Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel
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摘要: 以钝化锥导乘波体为研究对象，开展了高焓激波风洞测热试验以及高温化学非平衡气动加热数值验证，对乘波布局滑翔飞行器前缘线和下壁面热流分布特征进行了研究。结果表明：乘波布局飞行器表面热流主要集中于头部驻点及其附近的前缘小范围区域内；在0°~6°的迎角范围内，迎角的改变基本不会对前缘线热流产生太大影响，但会导致下壁面热流明显增加；而侧滑角即使在0°~4°的范围内变化，也将导致前缘线迎风一侧热流明显增加。Abstract: 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.
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Key words:
- waverider /
- real gas effect /
- aero-heating /
- high enthalpy wind-tunnel test /
- numeri-cal simulation
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图 6 不同迎角时前缘线热流分布
Figure 6. The aero-heating distribution along the leading edge at different attack angles
图 7 不同迎角时下壁面中线热流分布
Figure 7. The aero-heating distribution along the center line of the lower surface with different attack angles
图 8 不同迎角时下壁面x1截面热流分布
Figure 8. The aero-heating distribution at the x1 cross section with different attack angles
图 9 不同迎角时下壁面x2截面热流分布
Figure 9. The aero-heating distribution at the x2 cross section with different attack angles
图 10 不同迎角时下壁面x3截面热流分布
Figure 10. The aero-heating distribution at the x3 cross section with different attack angles
图 13 不同侧滑角时前缘线热流分布
Figure 13. The aero-heating distribution along the leading edge with different sideslip angles
图 14 不同侧滑角时下壁面中线热流分布
Figure 14. The aero-heating distribution along the center line of the lower surface with different sideslip angles
图 15 不同测滑角时下壁面x1截面热流分布
Figure 15. The aero-heating distribution at the x1 cross section with different sideslip angles
图 16 不同测滑角时下壁面x2截面热流分布
Figure 16. The aero-heating distribution at the x2 cross section with different sideslip angles
图 17 不同侧滑角时下壁面x3截面热流分布
Figure 17. The aero-heating distribution at the x3 cross section with different sideslip angles
图 11 α=0°和8°时驻点热流云图
Figure 11. The aero-heating contours around the stagnation point when α=0° and 8°
图 18 β =0°和8°的驻点热流云图
Figure 18. The aero-heating contours around the stagnation point when β =0° and 8°
表 1 来流条件
Table 1. Flow condition
Parameters Value Ma 11.6 p/Pa 118 T/K 436 cN 0 cO 0.1588 cN2 0.7454 cO2 0.0528 cNO 0.0430 cNO+ 0 ce- 0 
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