具有前缘凹凸结构的组合翼型优化设计及其气动特性分析  

Optimized design and aerodynamic characteristics analysis of combined airfoil with leading-edge concave and convex structure

作　　者：陈坤 贵红亮 赵培尧 冯文慧 郝振华 CHEN Kun;GUI Hongliang;ZHAO Peiyao;FENG Wenhui;HAO Zhenhua(School of Mechanical Engineering,Xinjiang University,Urumqi,Xinjiang 830017,China)

机构地区：[1]新疆大学机械工程学院,新疆乌鲁木齐830017

出　　处：《排灌机械工程学报》2024年第8期771-777,共7页Journal of Drainage and Irrigation Machinery Engineering

基　　金：国家自然科学基金资助项目(51765062);新疆维吾尔自治区自然科学基金资助项目(2022D01C33)。

摘　　要：为了不断探索翼型改型的方法和提高翼型的气动性能,将传统翼型与生物翼型进行轮廓修型设计得到组合翼型,通过数值模拟的方法对组合翼型进行气动特性分析.同时,对组合翼型进行前缘凹凸结构优化设计,采用正交试验优选出气动特性表现最优的参数,并对最优前缘组合翼型进行气动特性分析.研究发现:相比标准NACA64-618翼型,组合翼型在小范围攻角有着较高的升力系数,升力系数最大提高了7.3%,此外,具有前缘凹凸结构的前缘组合翼型升阻比最大提高了9.98%.组合翼型的弯度前移使得吸力面负压峰值区域面积增大,翼型上下表面压差增大,进而提高了气动性能;前缘组合翼型由于前缘凹凸结构的存在,在翼型吸力面靠近尾缘处,形成一对反向旋涡,增加了流体在翼型表面覆盖的面积,抑制了流动分离的提前发生,进而达到失速延迟的效能.To further explore continuously the methods of airfoil modification and to improve the airfoil aerodynamic performance,the combined airfoil by profile modification design of the traditional airfoil and the biological airfoil was designed and the aerodynamic characteristics of the combined airfoil through numerical simulation was analyzed.At the same time,the design of the leading-edge concave and convex structure of the combined airfoil was optimized,and the parameters with the best aerodynamic performance were optimized by orthogonal test,and the aerodynamic characteristics of the optimal leading-edge combined airfoil were analyzed.The result shows that the combined airfoil has a higher lift coefficient at small angles of attack compared to the standard NACA64-618 airfoil,with a maximum lift coefficient increase of 7.3%and a maximum lift-to-drag ratio increase of 9.98%for the leading-edge combined airfoil with leading-edge concave and convex structure.The forward shift of the curvature of the combined airfoil expands the area of the negative peak pressure on the suction surface and increases the pressure difference between the upper and lower surfaces of the airfoil,thus improving the aerodynamic performance.The leading-edge combined airfoil forms a pair of reverse vortices on the suction surface of the airfoil near the trailing edge due to the existence of the concave-convex structure of the leading-edge concave and convex structure,which increases the area covered by the fluid on the airfoil surface and inhibits the early occurrence of flow separation,thus achieving the effectiveness of stall delay.

关 键 词：组合翼型 前缘凹凸 气动特性 优化设计 失速延迟 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]