Gurney襟翼对翼型气动特性影响的风洞实验研究

Wind-tunnel investigation of aerodynamic force for airfoil using Gurney flap

针对风力机叶片翼型WA251A在Re=3.0×106情况下,安装Gurney襟翼时气动力的变化展开风洞实验研究。对WA251A翼型在干净翼和安装Gurney襟翼情形下的气动力进行对比,重点讨论了Gurney襟翼安装高度、安装角度及安装位置等因素对翼型气动力的影响。实验结果表明:同一安装位置安装高度的增加其增升效应越明显,但阻力也会大幅增加;同一安装位置不同安装角度时都能增加升力,但是失速提前,阻力随着安装角度的减小而增加;同一安装高度安装位置从后缘逐渐前移时增升效果逐渐减弱,甚至出现升力减小的现象,伴随阻力的大幅增加,表明存在一个增升的有效区域。

Wind tunnel investigation was undertaken to determine the aerodynamic force effects of the Gurney flap on wind turbine blade airfoil WA251A at a chord Reynolds number of 3.0 × 10^6. Comparison between the experiment data with and without the Gurney flap has been carried out. Experiment over a WA251A airfoil with the Gurney flap shows that the aerodynamic performance of the airfoil is strongly influenced by the height, inclined angle and location of the Gurney flap. It is observed that the lift and drag are increased with the increase of the height of the Gurney flap, for the same location and given inclined angle of the Gurney flap, and then for the same loca- tion and length of the Gurney flap, the lift is all increased with different inclined angle of the Gurney flap, but for producing the stall regime ahead of time, the drag is increased with decrease of the inclined angle of the Gurney flap. With the Gurney flap moving from the lift is deteriorated gradually, even the lift is trailing edge towards the leading edge direction the effect of increasing decreased, and the drag is increased markedly. So it is an effective region that lift can increase.