【摘要】 对NACA4424翼型、NACA4424翼型和加装2%弦长Gurney襟翼的NACA4424翼型以及对应的尾缘厚度为2%弦长的钝尾缘翼型进行了数值计算。针对风力机应用,对应于以弦长定义的雷诺数为1.27×105到1.02×106;迎角为0-32度;计算结果表明,在研究范围内的所有工作状态下,修改后的钝尾缘翼型对流场产生了强烈的下洗作用,明显地改变了翼型压力面和吸力面的压力分布,并使翼型升力及升阻比比原翼型有显著增加;大大推迟了翼型的失速的出现,甚至直到32度时,尚未发现有失速的迹象。更多还原

【Abstract】 A numerical study of aerodynamic characteristics was conducted of NACA4424 aerofoil,a modified NACA 4424 aerofoil with a Gurney flap of 2% chord height and another modified NACA 4424 aerofoil with a blunt T.-E.of 2% chord thickness.For application in a wind turbine,Reynolds number on the chord length of the blade is from 1.27×105 to 1.02×106,and the attack angle is 0-32 degrees.Computational results show that a strong down-wash effect is produced by the modified aerofoil with the blunt trailing-edge,which changes the pressure distribution on the pressure and suction surface significantly,therefore compared with the original NACA4424 aerofoil,the lift and lift-drag ratio of the modified NACA 4424 aerofoil are enhanced remarkably.In addition,the stall attack angle is increased,and the stall doesn’t occur even until AOA is up to 32 degrees.更多还原