| 向树红,张敏捷,童靖宇,李海波,朱云飞,杨艳静,崔丽娟.高超声速飞行器主动式气膜冷却防热技术研究[J].装备环境工程,2015,12(3):1-7. XIANG Shu-hong,ZHANG Min-jie,TONG Jing-yu,LI Hai-bo,ZHU Yun-fei,YANG Yan-jing,CUI Li-juan.Research on Active Film Cooling and Heat-proof Scheme for Hypersonic Vehicles[J].Equipment Environmental Engineering,2015,12(3):1-7. |
| Objective To put forward a new approach of active thermal protection system termed as film cooling for future hypersonic vehicles (Mach 20 flow) and validate its performance by CFD. Methods By solving Reynolds-averaged Navier–Stokes equations, the finite-rate chemical reaction model with Park-I 5 components (N2, O2, N, O, NO) 17 equations was used to investigate the real gas effect. For the typical blunt body, a numerical study of the effectiveness of film cooling was presented for Mach 20 flow at 30 km, with the special designed micro inject hole located at the stagnation point. Results The reduction of heat flux on the isothermal wall (300 K) with film cooling at the vicinity of the hole could be as much as 90% compared to that without film cooling, and the covering area of the coolant flow could be 10 times larger than the out area of the hole. Conclusion The study showed promising prospect of film cooling for heat proof of future hypersonic vehicles. |
