In order to meet the requirements of small size, multiple measuring points, high precision and high reliability of pressure probes in the flow field of aero-engine and gas turbine, based on CFD simulation analysis method and according to the characteristics of flow around a cylinder, the aerodynamic performance of probes with different diameters is analyzed, and the surface pressure distribution is studied. Then the design scheme of total static pressure composite probe is determined and the test pieces were processed. The calibration results of the test pieces show that when the Mach number is 0.2 to 0.6 and the flow has no deflection, the static pressure hole angle of the probe with a diameter of 10 mm, 12 mm and 14 mm are ±50o, ±47.5o and ±45o, the measurement error is not more than ±1%, which can meet the accuracy requirements of general test. In addition, on the premise of meeting the measurement error of ±1%, the static measurement insensitive angle of 10 mm diameter probe can reach ±18o at Mach number of 0.2~0.5 and it can reach ±15o at the Mach number of 0.6. The static measurement insensitive angle of 12 mm and 14 mm diameter probe can reach ±18o at Mach number of 0.2~0.4 and it can reach ±12o and ±3o at the Mach number of 0.5 and 0.6 respectively. The total pressure measurement errors of the probes are not more than ±0.3% at Mach number of 0.2~0.6 and insensitive angle of ±15o, which can meet the accuracy requirements of engine test.