旋涡发生器对机翼最大升力和失速迎角的影响

Effects of Vortex Generators on Maximum Lift and Stall Angle of Attack over Wings

对一个展长为５００ｍｍ，弦长为２５０ｍｍ，翼型为ＮＡＣＡ００１２的机翼模型，安装各种小三角翼旋涡发生器作低速风洞测力实验，研究小三角翼各种弯度和它与机翼的相对位置对机翼最大升力和失速迎角的影响．实验结果表明当小三角翼与机翼在某个最佳相对位置时，机翼最大升力和失速迎角有个最大的增加．当小三角翼与机翼的相对位置不变时，各种弯度的小三角翼都可以使机翼最大升力和失速迎角有较大的增加，并且相互差别不大．

The effects of locations and various cambers of small delta vortex generators on the maximum lift and stall angle of attack of wings are studied in the wind tunnel.The small delta vortex generators varied in cambers and locations are fixed on the wing model which has NACA 0012 of span 500mm chord 250mm.The test results show that when the delta generator is the optimum position on the wing,the maximum increase of the maximum lift coefficient and stall angle of attack of the wing may be obtained and that when the position of the delta generator is fixed,delta vortex generators of various cambers may be used to increase the maximum lift coefficient and stall angle of attack of the wing and their increments are not much difference.