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为了研究翼型后缘折边对翼型流体动力性能影响,基于N-S控制方程,选择标准k一占湍流模型,在雷诺数为3×10~6的条件下,利用Fluent软件对标准NACA4412翼型以及加不同角度折边的翼型进行数值模拟,计算其在不同攻角下的升、阻力系数,并对比分析不同折边翼型流场及压强分布。计算结果表明加折边会增大升、阻力系数且90°折边对升力系数影响最大,150°折边对阻力系数影响最小,同时加折边会使边界层在折边前分离,并在折边后产生漩涡。
In order to study the influence of airfoil trailing edge hems on the aerodynamic performance of airfoils, based on the NS control equation, the standard k-turbulence model was selected. Under the Reynolds number of 3 × 10 ~ 6, the standard NACA4412 airfoil As well as the airfoil with different angle flaps, numerical simulation of lift and drag coefficient at different angles of attack was carried out. The flow field and pressure distribution of different flanged airfoils were compared and analyzed. The calculation results show that the hemming increases, the drag coefficient and the 90 ° hemming affect the lift coefficient the most, and the 150 ° hemming has the least effect on the drag coefficient. At the same time, the hemming will separate the boundary layer before hemming, and at Eddy after the whirlpool.