A side-mounted diverterless subsonic inlet of the UAV(unmanned aerial vehicle) was designed and the flow field was simulated.The design methodology of the bump was presented and the characteristics of the inlet were obtained.The results show that angle of attack and yaw angle have little effect on the inlet's performance within 0°～8°.The total pressure recovery of the inlet is great than 0.965 and the distortion index is less than 0.253 under all states.The inlet meets the requirements of the engine

proving that the side-mounted diverterless subsonic inlet is feasible.It has also been found that there exists a higher pressure region on the bump surface than that on the fuselage for the diverterless subsonic inlet.The effect of pushing boundary layer aside for the bump is related to the fuselage profile

lip

relative positon of the entrance and flight conditions.The leading curve of the bump should not be too sharp for side-mounted inlet and a curved surface is better than a flat one in pushing the boundary layer away.