涡发生器间距对翼型气动性能影响的实验研究

EXPERIMETAL STUDY OF INFLUENCE OF VORTEX GENERATORS SPACING ON AIRFOIL AERODYNAMIC PERFORMANCE

以DU93-W-210风力机号用翼型为研究对象，采用风洞实验方法研究4组涡发生器（VGs）例距（S=5H、7h、13H、19H，H为VGs高度）对翼型气动性能的影响规律。风洞实验结果发现：在清净翼型失速攻角（8°）之前，涡发生器对翼型的升力系数影响较小。而对于阻力系数及升阻比，当间距S=5H、7H时会使翼型的阻力系数增加，其中S=5H时阻力最多增加27％，升阻比降低19％。间距S=13H、19H时使翼型阻力系数降低，其中S=13H时阻力最多降低70％，升阻比最多增加160％；在翼型失速攻角（8°）之后，涡发生器均能增加翼型升力、降低阻力、增加升阻比，其中S=5H时翼型升力系数最多增加48％，增加失速攻角近10°，且在失速攻角之后，S=5H时翼型升阻比增加最多。故加装涡发生器不一定在全攻角范同内均增加翼型升阻比，但会增加翼型最佳升阻比的攻角范围。所以，涡发生器存在最佳间距，若从最大升力系数来判断，当间距S=5H时效果最佳。若从最大升阻比来看，当间距S=13H时效果更佳。

The DU93-W-210 wind turbine airfoil as the research object, studied 4 groups of vortex generators spacing （ S=5H, 7H, 13H, 19H , H is the hight of votex generators） influence on the aerodynamic performance of the airfoil using wind tunnel test method. Experimental results showed that in the clean airfoil stall angle, 8 degrees, the lift coefficient of airfoil vortex generator the effect is small. And for the drag coefficient and lift drag ratio, when the spacing is 5H, 7H will make the airfoil drag coefficient increases, the drag of S = 5H increased up to 27%, lower than 19%. When spacing is 13H and 19H the airfoil lift drag, drag coefficient decreases, the S= 13H drag was most reduced 70%, liters drag increased by 160% than most; in the airfoil stall angle, 8 degrees, vortex generator can increase the lift, reduce drag, increase the lift drag ratio, when S = 5H the lift coefficient of airfoil increased up to 48%, increase the stall angle near 10 degrees, and in this angle range, S = 5H the lift drag ratio increased most. So is not necessarily in the angle of vortex generator range increase the lift drag ratio, but will increase the angle range of airfoil lift drag ratio optimal. Therefore, vortex generator has the best spacing, if from the maximum lift coefficient judge, when the spacing is 5H the effect is the best, if from the maximum lift drag ratio judge, when the spacing is 13H the effect is better.