The surge line of 0.6 m continuous transonic wind tunnel compressor system with different static blade angles and wind tunnel pressures is completed. The data of surge line pressure ratio is modified by measured inlet temperature of compressor; The surge line data of static blade angles which are not measured are calculated by linear interpolation value through surge line data of measured static blade angle. In the debugging of Mach number 0.8–1.2, with the solid nozzle profile 1.0, the main compressor using the main air injection mode, “series” mode and “parallel” mode of the main and auxiliary compressors are respectively tested. By comparing the total operating power and operating pressure ratio of the unit, it is more economical to use the main compressor alone using the main air injection mode, which has certain guiding significance for the selection of the reentry position of the plenum chamber air extraction in the transonic wind tunnel construction and the operation mode of the power system within the range of Mach number.