Abstract: Using an engineering design software of bump inlet based on waverider theory,an under fuselage bump inlet was designed based on the conic flow accurate stream line method.With regard to distribution of Mach numbers in the symmetric plane,limiting stream lines on the bump surface and distribution of pressure recovery coefficient(Cp) in the cross-section,the flow characteristics of the inlet were analyzed.It is shown that flow characteristics of the designed bump inlet are well consistent with the theoretical analysis with ideal gas.Supersonic aerodynamic properties of the bump inlet were analyzed by comparing the experimental results with computational ones.The results show that under design point condition,the average total pressure recovery coefficient at exit of bump inlet is nearly 0.87 at design Mach number of 2.0,and no less than 0.91 at mach number of 1.8.