凹腔超声速流场结构的试验研究  

Experimental Investigation on Supersonic Flows over Cavities

作　　者：房田文[1] 丁猛[1] 周进[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2007年第3期1-5,共5页Journal of National University of Defense Technology

基　　金：国家"863"计划资助项目(2002AA723060)

摘　　要：对超声速冷流情况下凹腔流场特性进行了试验和数值仿真研究,分析了不同构型的凹腔对超声速流场的影响。研究结果表明,在5～9范围内长深比L/D对凹腔流场结构基本没有影响;在30°～60°范围内,凹腔后壁倾角θ不会改变凹腔流场整体结构和特征,但对剪切层的空间发展和凹腔回流区结构有比较大的影响。Characteristics of supersonic cold flows over cavities were investigated experimentally and numerically, and the effects of cavities of different sizes on supersonic flow field were also analyzed. Results indicate that cavity flow structure has little relevance to L/D within the range of 5 - 9, and the ramp angle of the rear wall will not alter the overall structure of the cavity flow within the range of 300 - 600, but it can alter the development of the shear layer and the structure of the cireumfluence in cavities.

关 键 词：超声速流动 凹腔 流场结构 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]