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。
A numerical study of aerodynamic characteristics was conducted of NACA4424 aerofoil, a modified NACA 4424 aerofoil with a Gumey 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 doesnt occur even until AOA is up to 32 degrees.
出处
《沈阳航空工业学院学报》
2007年第1期1-5,共5页
Journal of Shenyang Institute of Aeronautical Engineering
