Abstract: The mechanisms of boundary layer separation caused by Shock /Boundary layer Interaction (SWBLI) in scramjet inlet and its control with Magnetohydrodynamics (MHD) were investigated numerically with a three dimensional CFD code, within which HLLE schemes, LU-SGS method, sst-kω turbulence model and multiblock structure grid were used. The results show that the numerical wall pressure agrees well with the experimental data, and the height of separation zone in the shoulder of scramjet inlet occupies 1/3 size of the throat height. With MHD accelerating the boundary layer, the separation in the scramjet inlet is eliminated, and the total pressure recovery coefficient is increased from 0.502 to 0.56, the flow field distortion parameter at the scramjet inlet throat zone is decreased by 18.6%.

Key words: Hypersonic inlet； MHD flow control; Shock wave boundary layer interaction; Boundary layer separation; Numerical simulation

摘要： 采用空间HLLE格式、时间LU-SGS推进、sst-kω湍流模型、多块结构网格程序,对磁流体动力学(Magnetohydrodynamic:MHD)控制高超声速二维进气道边界层分离进行了数值研究。研究发现,不施加控制时,数值模拟得到的壁面静压和实验结果符合良好,进气道喉道处分离区占据喉道高度的1/3左右。通过施加MHD控制,消除了进气道内部的边界层分离,总压恢复系数从0.502提高到0.56,喉道处流场畸变系数减小了18.6%。

关键词: 高超声速进气道;MHD 流动控制;激波-边界层相互作用;边界层分离;数值仿真