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基于大涡模拟(Large Eddy Simulation)方法,结合高阶TCD/WENO混合格式,对2.5Ma超声速激波/边界层干扰诱导的微楔和微叶片两种微涡流发生器控制进行了数值模拟。数值结果表明:从边界层厚度与分离区大小及结构变化均说明两种涡流发生器对激波边界层分离起到明显抑制作用。对于微楔式涡流发生器,入射激波对微楔尾涡压缩作用明显,使流向涡对的卷吸加强,从而增加边界层内外流体能量交换。微叶片式涡流发生器的控制机理与微楔相似,但其涡对在尾部较远处易破裂,会影响内外流体之间的能量交换。
Based on the Large Eddy Simulation method and the high-order TCD / WENO hybrid scheme, the numerical simulation of two micro vortex generators with micro-wedges and micro-vanes induced by 2.5Ma supersonic shock wave / boundary layer interference was carried out. The numerical results show that both eddy current generators can significantly suppress the shock boundary layer separation from the thickness of the boundary layer and the size and structure of the separation zone. For the micro-wedge vortex generator, the incident shock has a significant effect on the compression of the micro-weddock eddy so that the entrainment of the flow vortex pairs is strengthened and the energy exchange between the fluid inside and outside the boundary layer is increased. The control mechanism of the micro-vortex vortex generator is similar to that of the micro-wedge, but its vortex pair is easy to break away from the tail and affects the energy exchange between the inner and outer fluids.