Abstract: In order to investigate the flow separation control mechanism and the flow characteristics induced by vortex generator jet and shock/boundary layer interaction，based on the large eddy simulation method，combined with high order WENO/TCD hybrid scheme，the flow separation control by vortex generator jet has been simulated under the condition of Ma=2.5. The results show that the vortex generator jet suppresses the boundary layer separation，compared with the case without control，the pressure recovery coefficient increases from 85.9 to 94.6% with jet control. The wake of the jet locates mainly in a circular zone，in this area，the incident shock interacted with the horseshoe vortices under the barrel shock and the vortex pipe and shear vortex above the barrel shock，which makes the wake to be compressed by the shock. Meanwhile，due to the shock，the vortices interact with each other including extrustion and coalescence and form many small streamwise tubes，which entangle the high speed main stream into the boundary layer and increase the energy of boundary layer and suppress the flow separation finally.

Key words: Supersonic；Vortex generator jet；Flow separation control；Large eddy simulation

摘要： 为了研究射流涡发生器对激波边界层作用所诱导的流动分离控制机理及其流场特性，基于大涡模拟(Large eddy simulation)方法和高阶TCD/WENO混合格式，对来流马赫数Ma=2.5情况下，平板上射流涡发生器对激波与边界层相互作用所诱导流场进行了数值模拟。结果表明，射流涡发生器对激波边界层的流体分离有一定的抑制作用，与无控制情况相比，射流作用下进出口总压恢复系数由85.9%提高到94.6%。射流尾涡主要集中于一环状区域内，在该区域内，入射激波与马蹄涡、桶形激波上方的涡管以及剪切涡相互作用，导致整体尾流被激波往下压缩。同时在激波的压缩下，各涡之间相互缠绕、挤压合并，形成多个流向小涡结构，将边界层外的高速流体卷入边界层内，从而增加边界层底层能量，达到抑制流动分离的目的。

关键词: 超声速；射流涡发生器；流动分离控制；大涡模拟