超临界翼型Gurney襟翼增升技术实验研究

Experimental study on lift enhancement of supercritical airfoil in subsonic by Gurney flap

通过在二元翼型风洞中进行测力实验,研究了不同高度Gurney襟翼对超临界翼型气动力和力矩的影响规律。实验结果表明:在亚声速条件下,Gurney襟翼同样可以明显增加翼型的升力系数,使整个升力曲线向上平移,并使翼型低头力矩增加。高度为翼型弦长0.5%的Gurney襟翼可以带来超临界翼型的最大升阻比。同Gur-ney襟翼对NACA 0012翼型气动特性改变的对比表明,其在超临界翼型上带来的升力系数增量要大于在NACA0012翼型上的效果,但是带来的低头力矩增量较小。

The effect of Gurney flap on the aerodynamic characteristics of a subsonic supercritical airfoil was investigated by force measurements in a two dimensional wind tunnel.The results indicate that the Gurney flap can increase the lift and nose down pitching moment of the supercritical airfoil in subsonic.The optimal lift to drag ratio is achieved with a Gurney flap height 0.5% of the airfoil chord length.Compared with the symmetrical airfoil NACA 0012,the lift increment of the supercritical airfoil induced by Gurney flap is larger,but the pitching down moment increment is in the opposite way.