Gurney襟翼增升技术在三翼面布局飞机模型上应用的实验研究  

Investigation on application of Gurney flap to triplane configuration aircraft lift-enhancement

作　　者：王晋军[1] 蔡泽明[1] 刘铁中[1] 李亚臣[1] 

机构地区：[1]北京航空航天大学流体力学研究所,北京100083

出　　处：《实验流体力学》2006年第2期30-35,共6页Journal of Experiments in Fluid Mechanics

基　　金：国防预研基金(413130301);国家杰出青年科学基金(1042507)资助项目

摘　　要：在低速风洞进行了Gurney襟翼对三翼面布局飞机模型增升特性的全机验证实验研究,结果表明Gurney襟翼可显著提高飞机失速前的升力系数,特别是高度为1%c的三角型Gurney襟翼在迎角为2°和4°(巡航状态)时可分别使升力系数提高81.6%和37.4%,而相应的升阻比提高41%和8.2%。在起飞状态8°时,升力系数可提高15%。此外,实验进一步证实影响Gurney襟翼增升效果的主要参数是有效高度,有效高度相同的Gurney襟翼对布局的增升特性是相当的。The Gumey flap lift-enhancement experiment is conducted in low speed wind tunnel for a triplane configuration aircraft model. The experimental results show that the Gumey flap can indeed improve the lift coefficient before stall. Especially, the triangular Gurney flap with its height of 1% c can increase the lift coefficient by 81.6% and 37.4% at a - 2° and 4°（during cruise）, respectively, and the corresponding lift to drag ratio increment is 41% and 8.2%. At takeoff（ α = 8°）, the lift coefficient can increase about 15%. Moreover, the present experiment further verifies that the effective height of Gumey flap is the most important parameter influencing the lift-enhancement, which means that the Curney flap with the same effective height of different shape is equivalent to lift-enhancement.

关 键 词：GURNEY襟翼 增升 三翼面布局飞机 

分 类 号：V211.93[航空宇航科学与技术—航空宇航推进理论与工程] V211.7