The shock wave/boundary layer interaction (SWBLI) induces the flow separation in the inlet of air-breathing vehicles leading to the fluid kinetic energy loss, decreases of total pressure recovery coefficient and inlet flow area. It affects the inlet performance and subsequently restricts the overall propulsion efficiency and flight stability of aircraft. In this paper, the blowing control of SWBLI is studied through numerical simulation and theoretical analysis. The flow principle of boundary layer separation and the mechanism of blowing control interfering with boundary layer flow and inhibiting separation are discussed. The numerical results show that a high-pressure area are generated at the inlet lip position when the blowing pressure does not reach the blowing effect. When the blowing position at 0.298 m of the inlet and the blowing pressure of 0.4 \(P_{0}\) , the separation area can be effectively controlled.