二维叶片襟翼增升的试验研究

EXPERIMENT RESEARCH ON THE LIFT ENHANCEMENT OF AN AIRFOIL USING A SMALL TRAILING EDGE FLAPS

本文在雷诺数为0.24×106，0°－40°攻角范围内测定了带有90°，45°，135°三种不同偏转角的位于压力面后缘的襟翼的NACA632—215叶片的表面压力分布．根据压力分布求得的升力系数和阻力系数（压差）表明，襟翼能在不同程度上起到增升的效果，且当襟翼高度相同时，偏转角为90°时增升效果最佳；当偏转角为90°时，襟翼高度越大，升力系数增加越多．

Surface pressure distributions were obtained for an NACA632-215 airfoil with Gurneyand 45°, 135°trailing edge flaps at a Reynolds number of 0.24 x 106 and the angle of atttackvaried from 0° to 40°. The wind tunnel tests were made with Gurney flap hights in the range1% to 2.5% of the airfoil chord. Lift and drag determined from the pressure measurementsindicate a superior performance of the Gurney flap compared with 45°, 135° trailing edgeflaps and the addition of a flap increased the maximum lift coefficients from 0.914 to 1.29.