To obtain more abundant data on the inlet pressure flow field of aero-engine, this paper adopts the concept of probe fusion and designs a composite pressure probe capable of simultaneously measuring single-point total pressure (low-frequency/highfrequency) and static pressure (low-frequency) in the flowfield. The probe has been developed, installed on an aircraft for flight testing, and validated. The results demonstrate: the newly equipped pressure probes exhibit a blockage ratio of 0.56%, with structural strength meeting installation requirements. Flight tests have successfully captured synchronized measurements of the steady-state total-pressure field, steady-state static-pressure field, and dynamic total-pressure field at the engine inlet, providing abundant and accurate flowfield data; compared to directly using dynamic pressure sensors, employing pressure tubes introduces a slight time lag in the measured data. Therefore,to minimize the impact of pipeline cavity effects and ensure the accuracy of measurement data in inlet/engine compatibility flight tests, on the one hand, the pressure routes for the inlet flow field measurement system be optimized for the shortest distance. On the other hand, the steady-state test points should be maintained for at least 3 seconds or more.