相对厚度对翼型气动噪声影响的数值模拟  

Numerical simulation of the effect of relative thickness on aerodynamic noise of airfoils

作　　者：李瑞[1] 王龙[1] 许勇彬 LI Rui;WANG Long;XU Yongbin(School of Electrical and Mechanical Engineering,Anhui University of Science and Technology,Huainan 232001,China)

机构地区：[1]安徽理工大学机电工程学院,安徽淮南232001

出　　处：《河南工程学院学报（自然科学版）》2024年第4期35-39,共5页Journal of Henan University of Engineering：Natural Science Edition

摘　　要：相对厚度是无人机旋翼翼型的基本结构参数之一,会极大影响翼型性能。以NACA2412、NACA2418和NACA2424这3种不同相对厚度的翼型为研究对象,采用CFD/FW-H方法对翼型进行流场和声场数值模拟计算,分析相对厚度对翼型气动噪声的影响。数值模拟结果表明:在小攻角时,随着相对厚度的增大,翼型升阻比和低频噪声随之增大,中高频噪声和整体噪声逐渐变小;在大攻角时,3种翼型的整体噪声和升阻比明显变小,大厚度翼型仍表现出较好的气动性能和噪声性能。The relative thickness is one of the basic structural parameters of the rotor airfoil,which will greatly affect the performance of the airfoil.Taking NACA2412,NACA2418 and NACA2424 airfoils with different relative thicknesses as the research objects,the CFD/FW-H method is used to simulate the flow field and sound field of the airfoil,and the influence of relative thickness on the aerodynamic noise of the airfoil is analyzed.The results show that at a small angle of attack,as the relative thickness increases,the lift-to-drag ratio and low-frequency noise of the airfoil increase,and the medium-high frequency noise and the overall noise gradually decrease.At high angle of attack,the overall noise and lift-to-drag ratio of the three airfoils are significantly reduced,and the large-thickness airfoil still exhibits good aerodynamic performance and noise performance.

关 键 词：旋翼翼型 相对厚度 气动性能 噪声特性 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]