Abstract: Compared to traditional air data systems represented by probes and windsocks, Flush Air Data Sensing (FADS) systems are more suitable for hypersonic vehicle mission requirements in terms of thermal protection, stealth and measurement accuracy. For a hypersonic vehicle with an ellipsoidal nosecap, 11 pressure taps are arranged in the nosecap of the wind tunnel scaling experiment model. The angular and Mach number solutions were analyzed and selected for the angle and Mach number solutions by integrating the sensitivity of the pitch and yaw, Mach number solution accuracy and multiple redundancy. Combining the advantages of the Triples algorithm and the fitting algorithm, a systematic solution method for the flush air data sensing of the ellipsoidal nosecap hypersonic vehicle under the hypersonic condition is established, and corrected for the airflow angle amplification effect caused by the ellipsoidal nosecap of the aircraft and the shock wave. The results of wind tunnel (Ma = 6) validation experiments show that the angular solution uncertainty of the hypersonic FADS system is less than 0.41° and the accuracy is less than 0.38°, and the Mach number solution uncertainty is less than 1.1% and the accuracy is less than 0.52%.