With the development of the aviation technology,the construction of a supersonic calibration wind tunnel which meets the needs of dynamic calibration of sensors is needed.According to the general principle of supersonic nozzle design, the characteristic line theory and the method of boundary layer correction,the design of supersonic nozzle with fixed Mach number is carried out.Surface shape and design of the nozzle numerical simulation results show that this method can achieve the design requirements, to meet the requirements of a supersonic wind tunnel calibration.