Influence of blunt leading edge on shock-shock interaction and heat flux distribution of grid fin

被引：0
|
作者：
Zhang L. [1 ]
Wang S.-H. [1 ]
Jiang G.-Q. [1 ]
机构：
[1] China Academy of Aerospace Aerodynamics
来源：
Yuhang Xuebao/Journal of Astronautics | 2010年 / 31卷 / 02期
关键词：
Grid fin; Heat flux; Hypersonic; Numerical simulation; Shock-shock interaction;
D O I：
10.3873/j.issn.1000-1328.2010.02.004
中图分类号：
学科分类号：
摘要：
Numerical simulation and engineering prediction methods were applied to investigate the influence of leading edge bluntness on the shock-shock interaction of hypersonic grid fin, besides, the heat flux distribution caused by the shock-shock interaction was also studied. Results showed that the third critical mach number, which defines the end of shock-shock interaction, increases with the leading edge bluntness when the space length between grid fin is fixed , and the traditional theory developed for the grid fin with sharp leading edge is invalid for blunt leading one. On the other hand, as a result of the shock-shock interaction, there is a region with high heat flux locally. Nevertheless, the peak value is much low compared with the stagnation, so it does not have additional influence on the thermal protection.
引用
收藏
页码：324 / 328
页数：4
相关论文
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