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- 2015
用于飞机机翼涡固干扰噪声数值模拟的 RANS/NLAS方法
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Abstract:
针对传统的气动噪声混合模拟方法对网格要求过高的问题,尝试将非线性声学方程应用于涡固干扰噪声的计算中,以串列柱？惨砟Ｐ妥魑？飞机关键噪声部件的典型模型,利用数值模拟方法来研究涡固干扰噪声机理。通过雷诺平均N？？S方程(RANS)求解流场信息,再通过非线性声学方程(NLAS)求解声场,获得串列柱？惨砟Ｐ偷湫臀恢么Φ牧鞒√匦院驮肷？预测结果,揭示了涡固干扰噪声机制。RANS/NLAS方法对计算网格要求低、节约计算资源、缩短计算时间且计算精度高,可较准确地模拟非线性噪声。模拟计算表明:非定常来流下,涡固干扰是造成机翼噪声的最主要原因,主要发声部位由机翼后缘移至前缘,串列柱？惨砟Ｐ驮肷？的单音峰值出现在频率1 354 Hz处,最大声压级为91 dB。对近场流动特性和远场噪声预测的结果,与文献中实验结果均取得很好的一致性。
The aerodynamic noise caused by vortex？？structure interaction is becoming one of the main research hotspots in aeronautics. The paper takes rod？？airfoil model as the research object to conduct acoustic analogy through NLAS and CFD analysis through RANS, to investigate the mechanism of this kind of noise. Compared with the traditional analogy methods, RANS/NLAS method can simulate the nonlinear noise more accurately with less gird requirements, higher accuracy and is easy to be implemented. The results show that the vortex？？structure interaction is the main cause of airfoil noise and leading edge is the major noise source position. Meanwhile, the RANS/NLAS method can successfully predict vortex？？structure interaction in near？？field and the noise spectra in far？？field, which is in accord with the earlier experimental research
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