摘要
建立了一套基于CFD/FW-H_pds方法的旋翼跨音速高速脉冲噪声预估技术。在建立的旋翼流场CFD求解基础上,采用基于可穿透旋转积分面的鲁棒性较好的FW-H_pds方法来求解旋翼高速脉冲(HSI)噪声,并通过对UH-1H旋翼和AH-1旋翼的跨音速噪声的计算验证了该方法的有效性。
A method for predicting the rotor high-speed impulsive(HSI)noise based on CFD/FW-H_pds technology is established.Based on the rotor flowfield solved by CFD method,a robust FW-H_pds method based on the penetrable data surface is established for predicting rotor HSI noise,and the transonic acoustic characteristics of UH-1H rotor and AH-1 rotor have been simulated to verify the effectiveness of the present method.
引文
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