【摘要】 针对尾缘襟翼长度对风力机翼型气动性能的影响,分别以S809翼型与DU翼型为研究对象,设计了6种襟翼长度的襟翼模型,襟翼向翼型压力面偏转角为10°,襟翼与翼型主体之间为均匀1mm间隙,利用AUTOCAD对各襟翼长度模型进行几何建模。采用计算流体力学软件Fluent 14.0对各襟翼模型进行不同攻角下的气动性能计算,对翼型边界附近流场及压力系数等进行了分析比较。结果表明:尾缘襟翼长度对翼型的气动性能有较大的影响,襟翼长度不仅对襟翼附近的流场产生影响,对整个翼型的流场都有较大影响;带襟翼模型升力系数比无襟翼模型大大提高,且在一定攻角范围内随着襟翼长度增加,升力系数逐渐增大;带襟翼模型阻力系数比无襟翼模型翼型大,且在一定攻角范围内随襟翼长度增大阻力系数也增大;带襟翼模型升阻比在一定范围内比无襟翼模型大。更多还原

【Abstract】 The goal of the study was to investigate the effect of trailing edge flaps length on aerodynamics of wind turbine airfoil,airfoil S809 and DU series airfoil were selected as research objects,and six kinds of flap length airfoil model were designed,have the same chord length of1 000 mm,and the same deflect angle of 10°,the gap between the flap and the main airfoil body was optimized to make the width of gap as even 1mm.The grids near the trailing edge are refined,and the grid independence is verified through the comparison of the calculated results with grid scales three,which a 148 000 grid model was selected for further calculation.The k-ωtwo equation turbulence model for commercial software Fluent was used here to calculate the aerodynamics of the flap models at different attack angles,the streamline,pressure contour and pressure coefficient near border of airfoil were analyzed and compared.The result shows that the flaps length of airfoil with trailing edge flaps has great effect on the aerodynamic performance of the airfoil,not only the streamline near the flap is influenced but also the whole streamline near the airfoil are influenced.The lift coefficient of airfoil with flap is bigger than that of airfoil without flap,and the lift coefficient increases with the increasing of flap length.The drag coefficient of flap model is also bigger than that of airfoil without flap,and the drag coefficient of flap modelalso increases with the increasing of angle of attack.The lift to drag ratio is bigger than that of airfoil without flap at some range of angles of attack.更多还原