尾缘射流对翼型气动性能的影响  

Influence of Trailing Edge Jet on Aerodynamic Performance of Airfoil

作　　者：韩彦军 叶舟[1] 徐学昊 李春[1] HAN Yan-jun;YE Zhou;XU Xue-hao;LI Chun(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai,China,Post Code:200093)

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《热能动力工程》2020年第10期131-139,共9页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金(51676131,51176129);上海市科学技术委员会资助项目(13DZ2260900)。

摘　　要：为改善风力机翼型气动性能,提出翼型尾缘射流控制方式,以NACA0018翼型为基础,采用SSTк-ω两方程湍流模型数值模拟方法,研究尾缘射流翼型在不同射流孔宽度(0.001c、0.002c、0.003c)、射流入射速度(15、20、25 m/s)和入射角度(20°^-20°,计算间隔取10°)时的气动性能。结果表明:射流翼型在不同射流角度时,小攻角下,负射流角度增加翼型升力,大攻角下,正射流角度抑制翼型流动分离;射流孔宽度不同时,随着射流孔宽度的增加,负射流角度翼型升力系数增加幅度大于正射流角度翼型,且在大攻角下不同角度射流翼型的阻力系数有较大增长;射流速度不同时,大攻角下,不同射流角度翼型的升力系数均优于原始翼型;随着射流速度的增加,-10°射流翼型阻力系数明显降低,-20°射流翼型阻力系数有较大增长,正射流角度翼型变化较小。To improve the aerodynamic performance of the wind turbine airfoil,the airfoil trailing edge jet control method is proposed.Based on the NACA0018 airfoil,numerical simulation method with SSTк-ωtwo-equation turbulence model is used to study the effect of the trailing edge jet airfoil on aerodynamic performance with different jet orifice widths(0.001c,0.002c,0.003c),jet velocities(15,20,25 m/s)and jet angles(20°to-20°,the calculation interval is 10°).The calculation results show that the negative jet angle increases the airfoil lift at small angles of attack,and the positive jet angle suppresses the airfoil flow separation at high angle of attack at different jet angles.For airfoil with different jet orifice width,the increase of the jet orifice width leads to larger increase in the lift coefficient of negative jet angle airfoil than that of positive jet angle airfoil,and the drag coefficient of the different angle jet airfoil increases at a large angle of attack.For airfoil with different jet velocity,at high angle of attack,the lift coefficients of all different jet angle airfoils are superior to that of the original airfoil.With the increase of jet velocity,the-10°jet airfoil drag coefficient is significantly reduced,the-20°jet airfoil drag coefficient is greatly increased,and the positive jet angle airfoil variation is small.

关 键 词：风力机 尾缘射流 数值模拟 流动分离 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]