襟翼结构及安装位置对风力机翼型的流场影响

The Impact of Flap Structure and Installation Position on Flow Field of Wind Turbine Airfoil

为了分析不同襟翼结构和安装位置对翼型附近流场的变化情况,以NACA0012翼型为研究对象,建立加装不同襟翼翼型的二维计算模型,使用计算流体力学软件Fluent求解定常、不可压缩雷诺平均的N-S方程并且采用Spalart-Allmaras湍流模型计算翼型在0°到18°攻角α范围下翼型升阻力系数、升阻比、表面压力系数以及翼型附近的流场流线分布,分析翼型尾缘附近不同位置处添加不同襟翼结构时其流场流动特性。结果表明:对于添加襟翼后各翼型,由于襟翼的存在,整个翼型形状发生改变,使翼型与襟翼连接处流场发生不同程度的突变,导致翼型尾缘附近的流场、压力场以及上下表面压力分布发生了显著的变化,尾缘Gurney襟翼突变程度大,流体较易发生分离;尾缘三角襟翼有个倾斜过程,减缓了流体分离,从而延迟了分离流动的攻角。小攻角(0°~4°)下尾缘三角襟翼的翼型有显著的增生效果。

To study the impact of different structure and installation position of the flap on the change of the flow field of near the airfoil, NACA0012 airfoil as the research object, the calculation model of a two-dimensional airfoil with flap is established, using the computational fluid dynamics software Fluent to solve steady, incompressible Reynolds averaged Navier Stokes equation and Spalart-Allmaras turbulence model is used to calculate the lift and drag coefficient, lift-drag ratio, surface pressure coefficient of the airfoil and flow field distribution around the airfoil that is at a range of 0° to 18° angle of attack, and analyze the field flow characteristics at the airfoil trailing edge near different locations adding different flap structure. The results show that for adding flaps of the airfoil, as a result of the existence of the flaps and the airfoil shape change, make the trailing edge Eurney flap have a large degree of change, the fluid is more prone to separation; trailing edge triangular flap has a tilt process, slowing the fluid separation, thus delaying the separation of the angle. All addition flaps, the small angle of attack （0° - 4°） has a significant effect on the airfoil of the trailing edge of the triangular flap.