正弦前缘对三维机翼气动性能的影响研究

应用CFD数值仿真预报方法,系统分析正弦前缘各参数对三维机翼气动性能的影响。应用分离涡模拟方法,绘制并比较标准和正弦前缘三维机翼的气动性能曲线,给出压力系数云图和流线分布云图。数值分析结果表明:当波高为3 mm、正弦前缘布置范围大于30%展长、正弦波周期为5.5时,与标准三维机翼相比,最大升力系数提高19.7%,失速角延迟16.7%。研究结果确定最佳的参数组合,有效抑制三维机翼大攻角工况下的失速现象。

Effects of sinusoidal leading-edge on aerodynamic performance of three-dimensional airfoil

This paper systematically analyzes the effects of the different parameters of the sinusoidal leading-edge on the aerodynamic performance of a 3D airfoil by CFD numerical simulation. By comparison of the normal 3D airfoil with the sinusoidal leading-edge 3D airfoil, it gives the curves of aerodynamic performance, contours of pressure coeffcients and streamline distribution contours by using the detached eddy simulation method. The numerical analysis results shows that with 3 mm wave height, a range larger than 30%span of sinusoidal leading-edge and a sinusoidal wave period of 5.5, the maximum lift the coeffcient of the sinusoidal leading-edge 3D airfoil increases by 19.7%, and the stalling angle delays 16.7%by comparison with the normal 3D airfoil. The investigation determines the optimal parameter combination, and effectively restrains the stalling phenomenon of 3D airfoil at a large angle of attack.