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.
出处
《空气动力学学报》
EI
CSCD
北大核心
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).
