翼缝改形对翼型流动分离控制影响

Slot Modification Influence on the Flow Separation Control of Airfoil

为提高风力机的风能利用率,基于数值模拟方法,以NACA0018翼型为基准翼型,在传统翼型翼缝基础上设计出双弧形翼缝,分析翼缝相对位置(x/c)及翼缝数量对翼型流场结构及升阻力特性的影响。结果表明:在翼缝相对宽度h为1.0%c时,翼缝位于翼型中部位置时翼型气动性能改善最优;当攻角α为20°时,双弧形单翼缝翼型翼缝相对位置x/c=0.5,最大升力系数较原始翼型提高约34.1%,最大升阻比提高4.64倍;当攻角α为22°时,多翼缝翼型相对位置(x/c=0.4-0.5-0.6)最大升力系数较原始翼型提高约44.8%,最大升阻比提高7.13倍;双弧形翼缝翼型失速攻角最大可延迟8°,双弧形翼缝可显著改善翼型在大攻角下的气动性能。

In order to improve the wind energy utilization of wind turbine,based on the Fluent numerical simulation method,taking NACA0018 airfoil as the reference airfoil,a double-arc airfoil is designed based on the traditional airfoil.For the aerodynamic performance,the effects of the relative position and number of airfoil slots on the airfoil flow field structure and lift resistance characteristics were analyzed.The results show that when the relative width of the airfoil h=1.0%c,the aerodynamic performance of the airfoil is optimally improved when the airfoil is in the middle position of the airfoil;when attack angle α=20°,the double-arc single slot airfoil has maximum lift coefficient increased by about 34.1% at relative position x/c=0.5,Compared with the original airfoil,and the maximum lift-to-drag ratio is increased by 4.64 times.When attack angle α=22°,the multi-slot airfoil has,the maximum lift coefficient increased by about 44.8% at relative position x/c=0.4-0.5-0.6,and the maximum lift-to-drag ratio is increased by 7.13 times;the stall angle of attack of the double-arc slat airfoil can be delayed up to 8°.Double-arc slat airfoil can significantly improve the aerodynamic performance of the airfoil at high angles of attack.