三角翼Gurney襟翼增升实验研究  

Experimental investigation of Gurney flaps on the lift enhancement of a delta wing

作　　者：李亚臣[1] 王晋军[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：《空气动力学学报》2002年第4期388-393,共6页Acta Aerodynamica Sinica

基　　金：国防科技重点实验室基金资助(99JS51HK01).

摘　　要：在北航D1风洞中进行了Gurney襟翼对40°三角翼气动特性影响的实验研究,基于根弦长的实验雷诺数Re为250,000。实验采用的Gurney襟翼高度为1%-5%根弦长,侧滑角分别为0°、5°、10°和20°。与不加Gurney襟翼的光滑三角翼相比,Gurney襟翼在中高升力系数条件下可以提高三角翼的升阻比,其中尤其以1%弦长Gurney襟翼最为显著;改变侧滑角将削弱Gurney襟翼的增升作用。An experimental wind-tunnel investigation was undertaken to determine the effects of Gurney flaps on a 40° delta wing at a chord Reynolds number of 250,000. In the experiment, the height of the Gumey flaps was varied from 0.01 C to 0.05 C, and the sideslip angle of the model was selected as 0°, 5°, 10° and 20°. In comparison with the baseline clean configuration results, it was found that the model with plate Gurney flaps can indeed increase the lift-to-drag ratio at moderate to high lift coefficient for the wing, and the greatest increment was obtained for the 0.01 C Gurney flap. The effect of Gurney flap on the increment of lift-to-drag ratio trends to be not significant with the increase of sideslip angle.

关 键 词：三角翼 GURNEY襟翼 增升 升阻比 风洞实验 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] V211