钝化前缘对栅格翼激波干扰与热流分布的影响  

Influence of Blunt Leading Edge on Shock-Shock Interaction and Heat Flux Distribution of Grid Fin

作　　者：张亮[1] 王淑华[1] 姜贵庆[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《宇航学报》2010年第2期324-328,共5页Journal of Astronautics

摘　　要：采用数值模拟与工程计算相结合的方法对高超音速栅格翼进行了研究,分析了在高超音速情况下,栅格翼激波干扰对前缘钝度的敏感性以及对栅格翼热流分布产生的影响。结果表明:在同等栅格间距下,产生激波干扰的第三临界马赫数随栅格翼前缘钝度的增大而增加,传统的尖前缘栅格翼理论不适用于钝化前缘外形。另外,激波干扰在栅格翼表面会产生局部的高热流区域,但此热流峰值与前缘驻点相比仍然较低,因此对栅格翼热防护无额外影响。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 math 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.

关 键 词：栅格翼 数值模拟 高超音速 激波干扰 热流 

分 类 号：O354.4[理学—流体力学] V211.3[理学—力学]