In the flight test of civil aircraft, the trailing-cone device are usually pulled out of the rear of the aircraft to measure the static pressure of the atmosphere, and the pressure data obtained are used to calibrate the static pressure data measured by the aircraft’s static pressure system (total static pressure pipe, static pressure source). Understanding the pressure measurement characteristics of the trailing-cone device is of great significance to improve the static pressure calibration and even the airspeed calibration of the aircraft. At present, the main calibration method for the towed cone system is tower calibration, and the flight Mach number covered by this method is generally below 0. 4. A subsonic wind-tunnel has been used to do this research in order to obtain the measuring characteristics of the trailing-cone device. A ‘real’ trailing-cone device of the test aircraft has been used in this study, and the test scheme was comprehensively analyzed and designed. Fixed trailing-cone hose angle test and full free trailing-cone test have been done through Mach number 0. 3 to 0. 82 and available data were obtained. The research content of this paper complements the Mach number coverage of drag cone calibration and improves the drag cone calibration system.