In order to solve the problem of insufficient research on the aerodynamic characteristics of the transonic probe at subsonic flow in the existing research, the structure design of the transonic wedge-shaped four-hole probe was carried out firstly, and the angle between the two inclined planes and the centerline of the designed probe was 17°, the diameter of the bleeding air hole is 1.1 mm. The flow field and structural strength of the probe are simulated by the fluid-structure interaction method, and it is found that under the supersonic condition, a stable appendage oblique shock wave is formed in front of the probe tip, and the maximum stress of the probe in the flow field is 142.86 MPa, the safety factor is 2.67. Finally, the probes were calibrated pneumatically under subsonic and supersonic conditions, and it is found that the calibration curves were relatively regular, the angle sensitivity was high, and the orthogonality between the calibration points was good. Under subsonic conditions, when the pitch angle of the probe is positive and the absolute value of the yaw angle is ≥5°, the orthogonality of the curve is poor, and with the increase of Ma, the orthogonality of the characteristic curve is improved.