The effective and direct means of helicopter aircraft aeroacoustics evaluating are experiments in aeroacoustic wind tunnel. In recent years, 3m diameter rotor test equipment was researched, and corresponding technology has been developed in China Aerodynamics Research and Development Center. As the first test of helicopter model full configuration aeroacousic test in windtunnel, the aeroa-coustic characteristics of full configuration and components are researched. Firstly, in order to ensure the accuracy of the test results, the precision of model control and ratio of signal and noise are validated, by comparing the test data form different wind tunnel. Sec-ondly, by conducting aerodynamic noise wind tunnel tests on main rotor/fuselage configurations and full configurations, the impact of parameters such as advance ratio, thrust coefficient, collective pitch angle, and shaft tilt angle on noise spectrum characteristics, harmonic noise amplitude, and OASPL was analyzed. At last, the contribution of tail rotor to the aeroacoustic of full configuration is also analyzed. The research results indicate that in the hovering state, intense blade-wake interaction noise can be induced at low collective pitch angle in hovering state. The thrust coefficient has little on noise level in forward. In decent flight, the sound level decreases with the increase of the thrust coefficient. The influence of tail rotor is also researched, the full configuration aeroacoustic is strengthen by the tail rotor acoustic in hovering and forward level flight. However, the tail rotor aeroacoustic has little influence on the full configuration aeroacoustic as the result of intense blade vortex interaction noise in the decent flight conditon.
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