翼型最大厚度及位置对气动噪声的影响

Influence of Maximum Thickness and Position of Airfoil on Aerodynamic Noise

本文将研究不同最大相对厚度及翼型最大厚度位置对翼型气动噪声的影响。以NACA4与NACA6系列翼型为研究对象,采用基于BPM理论的风力机翼型噪声源仿真软件,研究翼型最大相对厚度及其位置对气动特性和声压级的影响。结果表明:最大相对厚度增大,翼型的气动特性变差,噪声变大。最大厚度越靠近尾缘处时,最大升力系数越大,最大升阻比越大,所对应的最优攻角越小,噪声先增大后减小。

In this paper, the effects of the maximum relative thickness and its position on the aerodynamic noise are studied. Taking NACA4 and NACA6 series airfoils as the research object, the influence of the maximum relative thickness and its position on the aerodynamic characteristics and sound pressure level is studied based on the BPM theory of the wind turbine aerodynamic noise source simulation software. The results show that the aerodynamic characteristics of the airfoil become worse and the noise becomes larger with the increase of the maximum relative thickness. When the position of the maximum thickness is close to the trailing edge, the maximum lift coefficient and maximum lift drag ratio are greater, but the corresponding optimal attack angle is smaller,and the noise increases first and then decreases.