Abstract: The flow field around a hypersonic spherical-conic aircraft is numerically simulated to obtain the characteristics of the fluctuating pressure environment within the turbulent boundary flow, as described by three statistical parameters in this paper. The results indicate that the intensity of the fluctuating pressure decreases from the upstream to the downstream of the aircraft flow field, and the excitation energy of the fluctuating pressure is limited within a frequency band lower than the specific frequency of the turbulence boundary. The longitudinal and transverse correlation of the fluctuating pressure flow field is increased in the flow direction, and the attenuation of the fluctuating pressure is enhanced as the spatial distance is decreased, as is consistent with the transmission and attenuation characteristics of fluctuating pressure. The investigation on the characteristics of the fluctuating pressure environment around aircraft can contribute to confirm the payload parameters in environmental compatibility researches for the aircraft, and to provide a design basis for aircraft structure improvement.