基于LES与FW-H方程的圆柱-翼型干涉噪声数值研究

发布时间：2018-03-13 19:21

本文选题：大涡模拟　切入点：FW-H方程　出处：《航空动力学报》2016年09期 　论文类型：期刊论文

【摘要】：采用大涡模拟(LES)结合Ffowcs Williams-Hawkings(FW-H)方程研究了圆柱-翼型干涉噪声的频谱特征和四极子噪声的影响.流场结果与实验吻合较好,声场获得了与实验相一致的频谱形状,翼型前缘30%弦长为主要干涉噪声源.针对计算与实验展向高度不同的问题,首先基于相关函数为三角函数的假定推导了展向修正公式,并与相关文献采用矩形函数、指数函数及高斯函数所得结果进行了对比.结果表明:不同的修正方法修正量差别高达7.6dB,三角函数与矩形函数修正效果类似,优于高斯函数,指数函数修正效果最差.分别采用固体壁面和可穿透数据面作为积分面,研究了体声源的影响,结果表明低马赫数下四极子噪声的影响可以忽略不计.
[Abstract]:The spectral characteristics of cylindrical airfoil interference noise and the influence of quadrupole noise are studied by means of large eddy simulation (les) and Ffowcs Williams-Hawkingsn FW-HH equation. The results of the flow field are in good agreement with the experimental results. The 30% chord length of the leading edge of the airfoil is the main interference noise source. Aiming at the problem of the difference between the calculated and experimental spanned height, based on the assumption that the correlation function is a trigonometric function, the spanned correction formula is derived, and the rectangular function is used with the related literature. The results obtained from exponential function and Gao Si function are compared. The results show that the correction quantity of different correction methods is as high as 7.6 dB, and the effect of trigonometric function is similar to that of rectangle function, which is better than that of Gao Si function. The effect of volume sound source is studied by using solid wall surface and penetrating data surface as integral surface respectively. The results show that the influence of quadrupole noise at low Mach number can be neglected.
【作者单位】：西北工业大学动力与能源学院;
【基金】：国家自然科学基金(51276149;51476134) 空气动力学国家重点实验室研究基金(SKLA20140201)
【分类号】：V211

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