Bubble Burst Control for Stall Suppression on a NACA 631 - 012 Airfoil
Bubble Burst Control for Stall Suppression on a NACA 631 - 012 Airfoil
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DOI：
10.2514/1.43924
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发表时间：
2009-07
影响因子：
2.2
通讯作者：
C. Wong;K. Rinoie
中科院分区：
文献类型：
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作者：
C. Wong;K. Rinoie
基于爆破板的新概念，研究了在NACA 631-012翼型截面上安装不同位置(翼弦的5%、7.5%和10%)的爆破板在翼型弦雷诺数为1.3×105的情况下对层流分离气泡的延时、抑制失速、增升减阻的效果。防爆板的有效性取决于它的高度、宽度、几何形状以及翼型前缘与板后缘之间的距离。利用烟幕流动显示技术研究了附板和不附板翼型的流动形态。结果表明，原翼型(不加防爆板)的失速角出现在10o处，加装防爆板后，失速角可成功推迟到13o左右。升力和阻力测量的迎角范围从0度到+20度。实验结果表明，NACA 631-012翼型在9°以上迎角的情况下，附板翼型的升力明显大于原翼型，阻力也有较大幅度的减小。总体结果表明，在NACA 631-012翼型上应用爆破板可以有效地控制低速流动中的气泡爆裂和翼型失速。
Based on the novel concepts of the burst control plate, the current article aims to demonstrate the effectiveness of the burst control plate attached at different locations (5%, 7.5% and 10% of the chord of the airfoil) on a NACA 631-012 airfoil section for laminar separation bubble burst delay, stall suppression, lift augmentation and drag reduction at a chord Reynolds number of 1.3x10 5 . The effectiveness of the burst control plate is governed by its height, width, geometry and the distance between the leading-edge of the airfoil and the trailing-edge of the plate. Flow patterns around the airfoil with and without the plate attachment were studied with an aid of smoke flow visualization. The results suggest that the stall angle of the original airfoil (without the burst control plate) occurs at 10 o and it is successfully postponed to approximately 13 o when the burst control plate is attached onto the airfoil. Lift and drag forces were measured for a range of angle-of-attack from 0 o to +20 o . The experimental results have shown that the lift generated on the NACA 631-012 airfoil with the plate attachment and above 9 o angle-of-attack is significantly higher than the original airfoil, while the drag is sufficiently reduced. The overall results demonstrated the application of the burst control plate on the NACA 631-012 airfoil can be effective means of bubble burst control and airfoil stall suppression in low speed flows.