微涡流发生器对激波边界层作用诱导的流体分离控制  

FLOW SEPARATION CONTROL OF SHOCK WAVE AND BOUNDARY LAYER BY MVGs

作　　者：薛大文[1,2] 陈志华[2] 孙晓晖 

机构地区：[1]浙江海洋学院海运与港航建筑工程学院,舟山316022 [2]南京理工大学瞬态物理重点实验室,南京210094 [3]上海宇航系统工程研究所,上海201109

出　　处：《工程力学》2016年第7期227-233,共7页Engineering Mechanics

基　　金：国家自然科学基金面上项目(11272156);浙江海洋学院科研启动项目(21188006915)

摘　　要：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 large eddy simulation method, combined with high order WENO/TCD hybrid scheme, flow separation control by micro-ramp and micro-vanes was simulated under the condition of Ma=2.5. The simulated results of the boundary layer thickness, the size and strucaare of the separation zone reveal that the micro vortex generators suppress the boundary layer separation. For the micro-ramp vortex generator, the incident shock compresses the wake of micro-ramp, which enhances the strength of streamwise vortex and makes the energy change between the boundary layer and out flow. The control mechanism of the micro-vanes is similar with micro-ramp, but the vortex pair can break easily in the downstream, which may affect the energy change between the boundary layer and out flow.

关 键 词：超声速流动 流动分离 大涡模拟 流动控制 微涡流发生器 

分 类 号：O357.41[理学—流体力学]