A side-mounted subsonic inlet of unmanned aerial vehicle (UAV) was designed and the flow field was simulated.The characteristics of the inlet were obtained.The results show that

the inlet lip

the junction of the duct and the engine hub have great influence on the flow filed and characteristics of the inlet.The engine hub can improve the quality of the flow field at the exit of the inlet and reduce the distortion index.The total pressure recovery coefficient of the inlet is more than 0.97 and the distortion index is less than 0.15.The inlet meets the requirements of the engine at all states.