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为研究格尼襟翼对风力机专用翼型DU93-W-210气动性能的影响,在有/无格尼襟翼情况下进行风洞实验(雷诺数为1×10~6)。实验研究高度为1.5%C、2.0%C、2.5%C格尼襟翼增升效果。研究表明:格尼襟翼能有效提高翼型的升力系数,襟翼高度越高,升力系数越大,相应的阻力系数也有所增大。格尼襟翼在中、高升力系数情况下效果较好;高度为1.5%C的格尼襟翼可获得较大升阻比。为了进一步减少阻力,对平板格尼襟翼开30°、45°、60°锯齿。结果表明,平板襟翼开锯齿能减小阻力;30°锯齿襟翼能在较大范围内增大升阻比,增升效果最佳。
In order to study the effect of Gurney flaps on aerodynamic performance of airfoil DU93-W-210 airfoil, wind tunnel experiments with Reynolds number of 1 × 10 ~ 6 were performed with and without Gurney flaps. Experimental research height of 1.5% C, 2.0% C, 2.5% C Gurney flap lift effect. The research shows that Gurney flap can effectively improve the lift coefficient of airfoil. The higher the flap height is, the larger the lift coefficient is, and the corresponding drag coefficient is also increased. Gurney flaps performed better under medium and high lift coefficients; Gurney flaps with a height of 1.5% C yielded larger lift-drag ratios. To further reduce drag, flat gurney flaps open 30 °, 45 °, 60 ° serrated. The results show that the flaps of the flat flap can reduce the resistance; the 30 ° sawtooth flaps can increase the drag ratio in the larger range, and the best lifting effect is achieved.