Low Reynolds number airfoil aerodynamic loads determination via line integral of velocity obtained with particle image velocimetry
Low Reynolds number airfoil aerodynamic loads determination via line integral of velocity obtained with particle image velocimetry
复制标题
通过粒子图像测速法获得的速度线积分确定低雷诺数翼型气动载荷
DOI：
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发表时间：
2012
期刊：
影响因子：
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通讯作者：
Y. Y. Su
中科院分区：
文献类型：
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作者：
T. Lee;Y. Y. Su
由NACA 0012翼型和薄平板在Re = 29,000和54,000产生的小幅度升力是通过速度线积分确定的，通过应用Kutta-Joukowsky定理，用粒子图像测速法获得。还获得了NACA0012翼型的表面压力测量值来验证升力系数Cl。发现束缚循环对预失速角矩形积分环的大小和纵横比不敏感。目前的Cl数据也被发现与地面压力决定的失速前升力系数非常吻合。然而，在失速后条件下，Cl随循环大小和长径比的变化很大。然而，目前的平板Cl数据也被发现与已发表的小攻角力平衡测量结果一致，尽管在大攻角的各种已发表数据之间存在很大差异。最后，利用整体平均尾流速度曲线计算阻力系数，进而计算升阻比。
The small magnitude lift forces generated by both a NACA 0012 airfoil and a thin flat plate at Re = 29,000 and 54,000 were determined through the line integral of velocity, obtained with particle image velocimetry, via the application of the Kutta–Joukowsky theorem. Surface pressure measurements of the NACA0012 airfoil were also obtained to validate the lift coefficient Cl. The bound circulation was found to be insensitive to the size and aspect ratio of the rectangular integration loop for pre-stall angles. The present Cl data were also found to agree very well with the surface pressure-determined lift coefficient for pre-stall conditions. A large variation in Cl with the loop size and aspect ratio for post-stall conditions was, however, observed. Nevertheless, the present flat-plate Cl data were also found to collectively agree with the published force-balance measurements at small angles of attack, despite the large disparity exhibited among the various published data at high angles. Finally, the ensemble-averaged wake velocity profiles were also used to compute the drag coefficient and, subsequently, the lift-to-drag ratio.