Reusable aircraft has been a research hotspot in the field of aerospace. When a high-speed re-entry vehicle re-enters the atmosphere， accurate flight parameters such as angle of attack， sideslip angle and dynamic pressure， plays a crucial role in control and stability. The traditional outrigger pitot tube and angle of attack/sideslip sensing system causes a series of structural and thermal problems at a high speed， and cannot be applied to high angle of attack flight conditions. In order to solve these problems， a flush air data system （FADS） is developed. Combined with the pressure distribution model， FADS solves the atmospheric parameters based on the measurement of pressure information from multiple pressure taps embedded in the surface of the fuselage. The correctness of the FADS algorithm is verified by laboratory tests and the adaptability of the FADS is verified by wind tunnel tests. The test results can effectively evaluate the performance of FADS.