Aiming at the problem that the structural damage of supersonic inlet will affect its internal and external flow field and performance parameters, the numerical simulation was used to analyze the effects of two types of damage, namely, throat perforation and cone breakage, on the supersonic inlet, and the working conditions of three models at 0 and 4° angles of attack were calculated respectively. When the angle of attack is 0, the throat damage has a greater impact on the flow field, while the cone break damage has a smaller impact; when the angle of attack is 4°, the flow field changes slightly after the damage. However, the internal Mach number, pressure and the total pressure recovery coefficient distribution at the exit section of the two damage models are different from those of the non-destructive model. The pressure distribution on the symmetry plane of the damage model of sharp cone fracture is similar to that of the non-destructive model, while the pressure distribution on the symmetry plane of the damage model of throat perforation is quite different from that of the non-destructive model. The calculation results can provide a reference for the judgment of missile performance degradation after damage.