Abstract: Flush airdata sensing system (FADS), using an array of surface pressure measurements to infer the speed, position, and orientation of a vehicle in flight, has shown prime advantages in the requirements of modern aircraft performance, especially becomes a key technology of air-breathing supersonic aircraft. The FADS system processing algorithm requires a pressure model which relates air data parameters to the measured pressures. The aerodynamic models of a FADS system are analyzed firstly. For FADS system deployed on a blunt body, static wind-tunnel needs to calibrate the angle of attack error, the sideslip angle error and the position error. For FADS system deployed on a conical or a non-regular shape, the aerodynamic models need to be obtained by wind tunnel tests or flight tests. Static wind-tunnel tests for conical models are conducted in a trisonic wind tunnel named FD-06, the surface pressure distribution is reasonable and show that the difference of pressure on the symmetry ports in vertical plane can be used to acquire angle of attack, and the difference of pressure on the symmetry ports in horizontal plane can be used to solve angle of sideslip.