Aerodynamic Characterization of a NACA 0018 Airfoil at Low Reynolds Numbers
Aerodynamic Characterization of a NACA 0018 Airfoil at Low Reynolds Numbers
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低雷诺数下 NACA 0018 翼型的空气动力特性
DOI：
10.2514/6.2010-4629
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发表时间：
2010
期刊：
影响因子：
--
通讯作者：
S. Yarusevych
中科院分区：
文献类型：
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作者：
Ryan J Gerakopulos;Michael S. H. Boutilier;S. Yarusevych
3 ~ 200 × 10 ~ 3，攻角0° ~ 18°。这些数据被用来表征分离气泡和确定升力系数。根据这些结果，可以确定升力曲线中的两个不同区域：在小迎角时升力系数快速线性增长的区域和在较高失速前角时更为平缓线性增长的区域。此外，在每个区域中的升力曲线的斜率被发现与分离，过渡和再附着位置的变化率与迎角。通过对NACA 0012翼型的实验数据进行分析，证实了这些发现。
3to 200x10 3 and angles of attack from 0° to 18°. These data were used to characterize the separation bubble and determine lift coefficients. From these results, two distinct regions in the lift curves can be identified: a region of rapid and linear growth of the lift coefficients at low angles of attack and a region of more gradual and linear growth at higher pre-stall angles. Furthermore, the slope of the lift curve in each region is found to be linked to the rates of change in separation, transition, and reattachment locations with the angle of attack. These findings are substantiated by an analysis of the available experimental data for a NACA 0012 airfoil.