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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．
For a wing model with a length of 500 mm, a chord length of 250 mm and an airfoil of NACA0012, a variety of small delta wing vortex generators were installed for low-speed wind-force test to study the various camber of the delta and its relationship with the wing Of the relative position of the wing maximum lift and stall impact angle of attack. The experimental results show that when the delta wing and wing are at an optimal relative position, the maximum lift and the angle of attack of the wing have the largest increase. When the relative position of the small delta wing and the wing is constant, the small delta wings of various camber can greatly increase the maximum lift of the wing and the angle of attack of the stall, with little difference between each other.