高超音速后掠激波与边界层干扰流场特性  

SURFACE FEATURE IN HYPERSONIC SWEPT SHOCK AND BOUNDARY LAYER INTERACTION

作　　者：王世芬[1] 王宇[1] 刘鹏[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《航空学报》1993年第9期A449-A454,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金

摘　　要：应用表面油流和液晶温度显示，表面热流率的压力测量四种测试技术，在Ｍａ∞＝７．８、单位长度雷诺数Ｒｅ∞＝３．５×１０＾７／ｍ条件下，研究了３０°迎角尖前缘翼面诱导激波和湍流边界层干扰流场特性，结果表明，表面流动是准锥型；在强相互作用下，流动发生了二次分离和再附，导致表面油流线的流向角、温度、热流率和压力分布均出现明显的凹坑。Experimental investigation of surface features in a swept shock turbulent boundary layer interaction induced by a sharp fin at angle of attack of 30 ° is performed using surface oil-dot visualization, liquid crystal surface thermography, surface heat transfer and pressure measurements. The nominal test condition is free stream Mach number of 7.8, unit Reynolds number of 3.5× 107 / m. The study shows that the surface flow is quasi-conical. There are both secondary separation and attachment in the strong interaction. The streak deflection, surface heat transfer and pressure distributions show distinct dip associated with secondary separation.

关 键 词：激波 边界层 干扰 高超音速流动 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]