基于凹凸前缘方法的风力机翼型气动噪声研究

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 .