该文采用实验测量和数值计算相结合的方法,以DU93-W-210翼型为研究对象,研究仿生凹凸前缘结构对其降噪效果的影响。运用远场麦克风阵列获得光滑前缘翼型和凹凸前缘翼型的气动噪声,并通过数值计算得到翼型表面流场结果。通过对实验和数值计算结果的分析发现：凹凸前缘方法能有效抑制边界层分离,控制翼型吸力面涡量的团状分布,减小翼型表面的压力脉动,分解大尺度高强度脱落涡为小尺度低强度周期性脱落涡,使得仿生凹凸前缘翼型有明显的降低气动噪声的作用;具有凹凸前缘的幅值为0.24c（c为平均弦长）、波长为0.11c的仿生翼型降噪效果更为突出。
Abstract
In this paper, the methods of experimental measurement and numerical calculation are used to analyze the control of the leading-edge protuberances on reducing the aerodynamic noise for the DU93-W-210 airfoil. The far-field microphone array is used to obtain the aerodynamic noise of the baseline airfoil and airfoil with leading-edge protuberances, and the result of flow field on airfoil surface is obtained through numerical calculation. Through analysis of the experimental and calculation results, it is found that, the method of leading-edge protuberances can effectively suppress the boundary layer separation, thereby controlling the vortex distribution and reducing the pressure fluctuation of the suction surface of the airfoil, disperses the large-scale shedding vortices, and decomposes it into the small-scale periodic shedding vortices with low-strength,which makes the leading-edge protuberances have a significant effect on the reducing of aerodynamic noise. Moreover, the effect of noise reduction is more prominent for wavy airfoil with the amplitude of 0.24c（c: the average chord length） and the wavelength of 0.11c.
关键词
凹凸前缘 /
风力机翼型 /
气动噪声 /
数值模拟 /
气动噪声测试
Key words
leading-edge protuberance /
wind airfoil /
aerodynamic noise /
numerical simulation /
aerodynamic noise testing
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基金
国家自然科学基金（52106280; 51736008）; 中国科学院洁净能源先导科技专项（XDA21050303）
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