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高级压比轴流压气机叶栅中激波、边界层相互作用会引起激波振荡并增加流动损失。本实验在超声速压气机叶栅风洞中研究激波、边界层相互作用现象并用激波、边界层相互作用的被动式控制方法寻求减弱激波振荡、减小流动损失的途径。被动式控制是用带有空腔的多孔表面部分地取代叶片吸力面的固体表面，并使该多孔表面恰好位于激波位置的下方。本文给出了有无被动控制时叶栅通道的纹影照相、高速照相、激波强度及叶栅损失，并对它们加以比较。结果表明，激波由无孔叶片时的单一波变成有孔叶片时的入波，激波强度变弱，激波振幅减小，叶栅等摘效率得以提高。
High-pressure axial shock Compressor cascade in the shock wave, boundary layer interaction will cause shock oscillation and increase the flow loss. In this paper, the shock wave and boundary layer interaction phenomena are studied in the supersonic compressor cascade wind tunnel. The passive control method of shock wave and boundary layer interaction is used to find ways to reduce the shock wave and reduce the flow loss. Passive control uses a porous surface with a cavity to partially replace the solid surface of the suction side of the blade and place the porous surface just below the location of the shock wave. In this paper, we present the smear photography, high-speed photography, shock intensity and cascade loss of cascade channel with or without passive control and compare them. The results show that when the shock wave is changed from a single wave into a perforated blade without a porous blade, the shock wave intensity becomes weaker and the amplitude of the shock wave decreases, and the efficiency of the blade cascade can be improved.