斜激波与轴对称边界层干扰的数值模拟  

Oblique Shock Wave/Axisymmetric Boundary-Layer Interactions

作　　者：杨柳青 李沁 尤延铖 YANG Liu-qing;LI Qin;YOU Yan-cheng(School of Aerospace Engineering,Xiamen University,Xiamen 361102,China)

机构地区：[1]厦门大学航空航天学院,福建厦门361102

出　　处：《气体物理》2023年第1期36-47,共12页Physics of Gases

摘　　要：使用两方程Menter-SST模型,对来流Mach数为3时的斜激波与轴对称边界层的相互干扰现象进行了数值模拟与定性、定量分析。研究了斜楔激波发生器楔角和来流单位Reynolds数变化对干扰区流动的影响,总结了参数变化引起的流动分离变化规律;此外,还计算了与三维计算中心对称面上的入射激波等效的二维情形,并将三维结果与二维情形进行对比,对比结果显示中心对称面上的壁面压力系数、分离涡尺寸、涡量分布等与相应的二维情形存在明显差异。Menter′s SST two-equation turbulence model was used to simulate the interaction between oblique shock wave and axisymmetric boundary layer in a supersonic Mach 3 flow,and the results were analyzed qualitatively and quantitatively.The influence of the wedge angle of the shock generator and the unit Reynolds number of the inflow on the interaction was studied,and the evolution regularity of flow separation caused by parameter variation was summarized.More-over,the two-dimensional cases which are equivalent to the incident shock wave on the central symmetry plane in corresponding three-dimensional cases were also calculated,and the results were compared with the three-dimensional cases.The comparison shows that the interference between oblique shock wave and axisymmetric boundary layer is obviously different from that of two-dimensional cases in terms of wall pressure coefficient,separation vortex,vorticity distribution and so on.

关 键 词：斜激波 激波/边界层干扰 三维效应 数值模拟 参数研究 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]