超临界翼型尾缘噪声影响因素研究

摘要

使用大涡模拟(LES)和FW-H相结合的方法对超临界翼型尾缘噪声进行了研究.针对超临界翼型后缘的不同设计参数(后缘厚度、后缘角和几何形状)对尾缘噪声的影响,使用ANSYS FLUENT的LES湍流模型计算声源,采用FW-H积分方法求解远场噪声总声压级.首先完成二维非定常流圆柱绕流的流场及其噪声的验证计算,计算结果与实验值符合,证明了求解器设置和网格生成的合理性.然后基于此正确的求解器设置和网格生成,使用LES/FWH对比了典型超临界翼型的不同后缘设计参数对远场总声压级的影响,所得结论对低噪声超临界翼型优化设计有参考意义,同时为进一步的噪声控制优化设计提供了基础.%Trailing edge of typical supercritical airfoils is studied using hybrids LES and FW- H method. Different design factors influencing the level of supercritical airfoil trailing edge noise, such as the thickness of trailing edge, trailing edge angle and the profile of the trailing edge are studied based on ANSYS FLUENT. The flow field is solved using LES model of high accuracy and then FW- H method is used to obtain the overall sound pressure level. The method is first validated using two- dimensional unsteady flow around a circular cylinder and the induced noise is evaluated. Good agreements were achieved compared with experimental data. The influence of different parameters of trailing edge on the overall sound pressure level of far- field of a typical supercritical airfoil is compared. The results provided the basis for trailing edge optimization with low noise levels and can be used in the implementation of further noise control strategies.