摘要
增大飞机的升力可以有效地缩短飞机起飞和着陆的滑跑距离 ,本文通过对高升力多段翼型有、无Gurney襟翼时的翼面边界层、尾迹速度分布及表面压力分布的测量等实验方法研究了具有Gurney襟翼时的多段翼型绕流特性及增升规律。实验研究结果表明 ,在α =8°时 ,Gurney襟翼高度为 0 .0 2c和 0 .0 5 5c时 ,使多段翼型升力系数分别增加了 1 3%和 2 2 %。Gurney襟翼的增升效果不仅与Gurney襟翼的高度密切相关 ,而且还与在翼面上的安装位置有关。
The takeoff and landing distances of aircraft are reduced by increasing the wing lift, efficiently. In this paper, the principle of high lift and flow characters around multi element airfoil with and without Gurney flap are studied by testing method of surface boundary layer, wake velocity distribution and surface pressure distribution. The experimental results indicate that when α=8°,highness of Gurney flap is 0.02c and 0.055c, the lift coefficient of multi element airfoil increases 13% and 22%, respectively. The increasing lift effect of Gurney flap not only related with highness of flap, but also with the position of flap installation.
出处
《空气动力学学报》
CSCD
北大核心
2002年第2期174-178,共5页
Acta Aerodynamica Sinica
基金
国防科技重点实验室基金资助项目 (98JS5 1 .1 .1ZS5 1 0 1 )
