In order to solve the problems of robustness and accuracy for the given shock's aerodynamic surface

a kind of inverse characteristic method was developed. This method could be used to generate the aerodynamic surface and dependent domain flow field for the given shock wave in a non-uniform upstream. Numerical verification indicated that the relative error of the cone shape (cone angle) gotten by inverse characteristic method was less than 0.5 ‰

when the conical shock was given at Mach number of 5; the calculations of two-stage axisymmetric shock showed that the two-stage compression cone corresponding to the flow field could be accurately acquired. Finally

three aerodynamic models were obtained with use of the method

including: Bump surface with two-stage shock wave and waverider forebody at Mach number of 4 and the integration of the wave precursor and inlet. The CFD calculation results show that these models are better designed and the inverse characteristic method proposed provides a way for aerodynamic design.