仿灰鲭鲨尾鳍襟翼的翼型气动性能数值研究  

Numerical Study of Aerodynamic Performance of Bionic Flap Airfoil with Mako Shark Tail-fin

作　　者：苏顺龙 叶学民[1] 吴英明 李春曦[1] SU Shunlong;YE Xuemin;WU Yingming;LI Chunxi(Hebei Key Laboratory of Low Carbon and High Efficiency Power Generation Technology,North China Electric Power University,Baoding 071003,Hebei Province,China)

机构地区：[1]华北电力大学河北省低碳高效发电技术重点实验室,河北保定071003

出　　处：《动力工程学报》2024年第6期895-904,共10页Journal of Chinese Society of Power Engineering

摘　　要：为进一步提高翼型的气动性能,基于灰鲭鲨尾鳍上尾叉型线结构,提出一种仿生襟翼结构。利用SST k-ω湍流模型模拟仿生翼型的气动性能和内流特征,分析了仿生襟翼相对位置和角度的影响,得到了气动性能最优的仿生襟翼翼型,并将其与格尼襟翼进行对比。结果表明:安装仿生襟翼后,翼型升阻比较原翼型显著提高;当襟翼相对高度不变时,减小襟翼安装角和增大襟翼与尾缘间的距离均导致翼型失速提前;安装角为45°且逆流向安装在尾缘处的仿生襟翼翼型气动性能最优,其升力系数较格尼襟翼翼型在失速前平均提高5.9%;安装仿生襟翼后流场结构更复杂,流场内涡的位置、数量及大小均有所改变。To further improve the aerodynamic performance of airfoils,a bionic curved flap was proposed based on the trail fin profile of mako sharks.The aerodynamic performance and internal flow of the bionic airfoil were simulated using the SST k-ωturbulence model,and the effects of relative position and installation angle of the bionic flap were analyzed to obtain the optimal bionic flap airfoil with the best aerodynamics,which was compared to the Gurney flaps.Results show that after installing a bionic flap,its lift-drag ratio is significantly higher than the baseline;when the relative flap height remains unchanged,reducing the installation angle and increasing the distance between the flap and the trailing edge lead to an early airfoil stall onset.The aerodynamic performance of the bionic flap airfoil with reverse installation angle of 45°at the trailing edge is the best,and the lift coefficient is 5.9%higher than the Gurney flap airfoil before the stall.After arranging the bionic flap,the flow field tends to be complicated,and the position,quantity and size of vortices change.

关 键 词：翼型 仿生襟翼 气动性能 结构优化 数值模拟 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]