摘要
本文使用基于可穿透数据面的Ffowcs Williams-Hawkings方程(FW-Hpds)的预测方法分析了跨声速直升机悬停旋翼气动噪声的指向性。通过求解三维非定常欧拉方程计算了近场噪声,通过延迟时积分方法和求解FW-Hpds方程计算远场噪声。预测了跨声速UH-1H悬停旋翼的高速脉冲噪声(HSI),然后计算了不同观测点处的声压级,并通过声压级在不同方向上的分布分析了HSI噪声的方向性。根据本文研究发现HSI噪声在桨盘平面上最大,在转轴方向上最小,和其它研究者的结论一致。
The directivity of aerocoustic noise generated by transonic helicopter rotor is analyzed through a new prediction method based on 'penetrable surface' Ffowcs Williams Hawkings equation (FW-Hpds).The prediction of the noise needs the pressure data of the flow field. In the flow field computation,the three dimensional Euler equation is used as the governing equation.The CFD combined with FW-Hpds is used to calculate the aerodynamically generated noise of helicopter rotor.High speed impulsive noise of transonic rotor in hover is calculated.Sound pressure level is computed from the acoustic pressure data in time domain.The directivity of HSI noise is obtained through the analysis.The computational results are in agreement with other's researches.
出处
《直升机技术》
2007年第1期11-15,共5页
Helicopter Technique
关键词
直升机
旋翼
噪声
helicopter
rotor
noise
