Abstract: In order to study characteristics of curved backswept compression corner shock wave/turbulent boundary layer interactions between the forebody compression shock wave of inward turning inlet and the boundary layer of the body， inward turning inlet with rectangular capture line and straight bus cone is simplified. The simplified model is researched by numerical simulation method. The characteristics of the uncoupled and coupled curved swept compression corner shock/turbulent boundary layer are analyzed. The results show that the separation zone formed by the uncoupled model is machete-shaped， and the maximum value of the separation zone is located at the position y=-0.19H， （H is the height of the rectangular capture line），and the interaction with variable sweep angle no longer conforms to the quasi-conical similarity. The separation zone formed by the coupled model is a symmetric crescent-shaped， and the maximum value of the separation zone is located at the position y=0. And low-momentum fluid accumulates in the center of the inlet. Compared with uncoupled， the maximum value of the separation zone increased by 51%， and the boundary layer thickness of inlet exit increases. It is also found that the influence range of the coupling effect is limited. In the flow interval of |y|>0.6H at the leading edge of the compression corner， it is basically unaffected by the coupling effect.

Key words: Inlet;Shock wave;Turbulence boundary layer;Interaction;Separation zone;Coupling effect;Variable backward sweep

摘要： 为研究内转式进气道前体压缩激波与机体边界层之间的弯曲后掠压缩拐角激波/湍流边界层干扰现象，对矩形捕获型线、直母线圆锥基准流场生成的内转式进气道压缩型面进行简化，并利用数值仿真方法对简化模型进行计算，分析并对比了非耦合和耦合情况下弯曲后掠压缩拐角激波/湍流边界层干扰特性。结果表明：非耦合模型所形成的分离区呈弯刀形，分离区的最大值位于靠近侧壁面处（y=-0.19H），（H为矩形捕获型线的高度），且此种变后掠角干扰不再符合锥形相似特性；耦合情况下所形成的分离区呈对称月牙状，分离区最大值位置为对称面位置（y=0），低能流在进气道中心位置堆积；与非耦合相比，耦合会使得分离区最大值增大51%，进气道出口边界层厚度增大；同时也发现该耦合效应的影响范围是有限的，在压缩拐角前缘靠近侧壁面（|y|>0.6H）的流动区间内，基本不受耦合效应的影响。

关键词: 进气道;激波;湍流边界层;干扰;分离区;耦合效应;变后掠