垂直轴风力机的吸力面襟翼翼型结冰气动特性研究

Influence of Suction Surface Flap on Icing and Aerodynamic Performance of Vertical Axis Wind Turbine

摘要: 吸力面襟翼是一种有效的流动控制方式，能在一定程度上提高直线型垂直轴风力机的性能，然而其在结冰后能否继续发挥作用尚不明确。因此，本文开展NACA0015翼型吸力面襟翼的结冰模拟，对比分析结冰前后翼型气动性能。结果表明：未结冰和未失速工况下，吸力面襟翼安装位置和角度都对翼型气动性产生不利影响，且距离翼型前缘越近、与翼型之间的夹角越大，负面影响越大；在失速工况下，当襟翼安放在特定的位置和角度时能发挥积极作用。结冰后原始翼型和吸力面襟翼翼型前缘外形发生变化，导致翼型表面边界层提前分离，分流涡增大，翼型气动性能降低；结冰后吸力面襟翼翼型与原始翼型相比，小攻角工况下翼型的气动性能降低，但在大攻角工况下能小幅提高气动性能。

Abstract: Suction surface flaps, as an effective flow control method, can improve the performance of straight-blade vertical axis wind turbines to some extent; however, their usefulness after icing is unclear. Therefore, this paper carries out the icing simulation of NACA0015 airfoil with suction surface flap to compare and analyze the aerodynamic performance of the airfoil before and after icing. The results without icing show that both the installation position and deployment angle of the suction surface flaps adversely affected the aerodynamic performance of the airfoil under the unstable condition, and the closer to the leading edge of the airfoil and the larger the angle, the greater the negative effect. Under the stall condition, the flaps can play an active role when they are placed at a specific position and angle. After icing, the leading edge profile of the original airfoil and the airfoil with flap is changed, which leads to early separation of the boundary layer on the airfoil surface, increased separation vortices, and reduced aerodynamic performance of the airfoil. The aerodynamic performance of the suction surface flap airfoil profile is reduced for small angle of attack conditions but can be increased slightly for large angle of attack conditions compared to the original airfoil profile.