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利用最新发展的直升机旋翼气动声学程序计算了某模型旋翼桨涡干扰（ＢＶＩ）噪声，叶片表面非定常压力脉动数据由最新实验获得。计算的声压时间历程和指向性与实验结果符合得非常好
Based on the latest development of helicopter rotor aerodynamic program, the rotor vortex disturbance (BVI) noise of a model was calculated and the data of unsteady pressure pulsation on the blade surface were obtained by the latest experiment. Computed sound pressure time history and directivity are in good agreement with experimental results