中文摘要：

采用数值模拟的方法研究了超音速流动中斜坡型、双排斜坡型和分裂斜坡型三种不同微尺度涡流发生器诱导的尾迹涡耗散过程和发展轨迹,并对比分析了不同结构涡流发生器布置对激波边界层干涉的控制作用效果。研究结果表明,研究的三种涡流发生器结构诱导的逆旋涡之间具有相互弱化作用。双排斜坡型涡流发生器诱导的逆旋涡之间的弱化作用最强,斜坡型涡流发生器次之,分裂斜坡型涡流发生器诱导的逆旋涡之间的弱化趋势最弱,涡量更易在下游边界层中得到保持。涡流发生器产生的逆旋涡在互相诱导的作用下逐渐向远离壁面边界层的方向移动,分裂斜坡型和双排斜坡型涡流发生器的尾迹涡远离壁面的运动轨迹均较斜坡型涡流发生器的尾迹涡更为平缓。双排斜坡型涡流发生器的尾迹涡远离壁面的趋势更显著弱于分裂斜坡型涡流发生器,有利于保持尾迹涡在边界层内部,提升边界层的抗分离能力。在两种因素综合作用下,双排斜坡型涡流发生器对激波边界层相互作用具有最优的控制效果,分裂斜坡型涡流发生器的控制效果次之。

英文摘要：

The dissipation and trajectory of vortex induced by three micro-vortex generators,including micro-ramp,double rows of micro-ramp and split micro-ramp,are investigated in this paper.The effects of these three different micro-vortex generator configurations on shock-wave/boundary-layer control in supersonic flow are also discussed by numerical methods.Numerical results reveal that the vortices induced by the vortex generators are weakened by each other along with the increasing of the streamwise distance.The weakened effect of the vortices induced by double rows of micro-ramp is the strongest,and the effect of vortices induced by split micro-ramp is the slightest that causes the dissipation of these vortices is the poorest among these three conditions.The vortices induced by these vortex generators move far away from the wall boundary layer with the increase of streamwise location.The results indicate that the vortices induced by double rows of micro-ramps rises at the weakest trend after separating from the vortex generators,it is conducive to remain the vortices in the boundary layer and enhance the ability of the boundary layer to resist separation.In the combined effects of the two factors,the double rows of micro-ramps have the best control effect on the shock wave/boundary layer interaction among the three configurations.And the effect of the split micro-ramp is better than that of the micro-ramp.