Abstract: In order to obtain the characteristics of acoustic load on helicopter fuselage surface under complex flow field conditions, 16 microphones were arranged at different positions on the outer surface of the fuselage, and date from all channels were synchronously collected by a high-speed parallel acquisition system with a sampling frequency of 40.96 kHz. Using the rotor/body interaction model, the fuselage surface acoustic load test was carried out in the FL−10 wind tunnel. The test results show that the surface acoustic load of the helicopter fuselage increases with the increase of the collective pitch and forward flight speed; the rotating noise and broadband noise can be clearly captured on the surface of the helicopter fuselage; when the helicopter is in sloping descent, the noise of the blade vortex interaction can be clearly measured on the surface of the fuselage.