Gurney襟翼在某型靶机上的应用  

Application of Gurney flap on certain target drone

作　　者：赵元立[1] 左林玄[1] 于东升[1] 王晋军[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2009年第8期913-916,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：武器装备预研基金资助项目(9140A13010608HK0104);国家杰出青年科学基金资助项目(10425207)

摘　　要：通过改变Gurney襟翼的高度,在风洞中研究了Gurney襟翼对某型靶机气动特性的影响.实验中襟翼高度为0.83%c^4.2%c(c为靶机机翼根弦长).无侧滑时Gurney襟翼可以在中小攻角下增加靶机的升力,使靶机最大升阻比对应的攻角提前.除4.2%c襟翼外,其余高度的襟翼在中小攻角下可以提高靶机的升阻比和最大升阻比.有侧滑时,在纵向上Gurney襟翼对靶机气动特性的影响和无侧滑时类似,但在横航向上,随着襟翼高度的增加,滚转力矩增加,偏航力矩则在襟翼高度为0.83%c^3.3%c时增加,而襟翼高度为4.2%c时急剧降低.Gurney襟翼对靶机气动特性的影响存在最佳高度,实验发现在襟翼高度为1.7%c时,能够在靶机力矩变化较小的情况下,提高飞机的升力和最大升阻比.Experiments of Gurney flap on aerodynamics of a certain target drone were conducted in wind tunnel, the height of Gurney flap is in the range of O. 83% c - 4.2% c（ c--root chord length of target drone wing in the experiment）. For the target drone without sideslip, Gurney flap could enhance lift at medium and small angles of attack, and decrease the angle of attack where lift to drag ratio reaches maximum value. Meanwhile, besides of the 4.2% c Gurney flap, the others could increase the lift to drag ratio and the maximum lift to drag ratio. For the model with sideslip, the corresponding aerodynamic performance is similar to that without sideslip in longitudinal direction. However, in yaw and rolling directions, rolling moment increases with Gurney flap height, and yaw moment increases too when the Gurney flap height is in the range of 0.83% c 3.3% c, but the yaw moment decreases abruptly when Gurney flap height is 4.2% c. There exists the optimum Gurney flap height for improving the target drone aerodynamics, Experimental results show that it could increase the lift and the maximum lift to drag ratio with little variation of the moments in three directions when the Gurney flap height is 1.7% c

关 键 词：GURNEY襟翼 增升 升阻比 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]