Abstract: A Bump inlet flow control is researched in this paper. Numerical simulation of the inner and outer flow fields of the inlet are focused on its aerodynamic and flow field properties under the condition of supersonic inflow with Mach number of 1. 60. Based on this result, flow control devices, which are spoiler for airframe ridge vortex and inlet micro-mass suction/blow or jet control devices, are designed respectively to improve the inlet total pressure recovery and decrease the flow distortion with the inflow Mach number of 1. 60 while inlet and engine match point. The performance of control devices are numerically simulated subsequently to provide database for the analysis of each flow control device's performance and its flow control mechanism. The results reveal that the spoiler is of weak performance at negative angles of attack with the inflow Mach number of 1. 60; however, the inlet micro-mass suction/blow or jets control method is effective to control inlet total pressure recovery. This study provides certain reference for the engineering development and flow control strategies of Bump inlet used in stealth fighter.