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Dynamic Stall of a Swept Finite Wing for a Range of Reduced Frequencies

机译：一系列有限频率的后掠有限翼的动态失速

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An experimental investigation of three-dimensional dynamic stall is performed on a finite wing with a leading-edge sweep of Λ = 30° at a chord-based Reynolds number of Re_c = 1 × 10~5 with varying reduced frequencies. The wing has a semi-aspect ratio of 2, a NACA 0012 airfoil cross-section, and a rounded tip. The wing is pitched sinusoidally about the root quarter-chord from 4° to 22° to 4°. Experiments are performed in a horizontal free-surface water tunnel. The dynamic stall process at a reduced frequency of k = πfc/U_∞ = 0.20 has previously been shown to exhibit an arch vortex near the wing tip at high angles of attack during the pitching cycle. This arch vortex interacts with the tip vortex, and significantly affects the near-body wake dynamics. Force and moment data is presented over a range of reduced frequencies from 0.02 to 0.30, as well as cross sections of planar PIV at a spanwise location of z/c = 1.7. At reduced frequencies of 0.30 and 0.20, the signature of the arch vortex is inferred through contours of the criterion. At reduced frequencies of 0.10 and 0.05, an initial dynamic stall vortex similar to the arch vortex appears to form, but quickly convects downstream. At reduced frequencies of 0.03 and 0.02 there is no indication of a coherent dynamic stall vortex at the studied span-wise location. This displays the dependency of the arch vortex formation process on a sufficiently unsteady pitching motion.
机译：在前掠角为Λ= 30°的有限机翼上，以基于弦的雷诺数Re_c = 1×10〜5并以变化的减小的频率进行了三维动态失速的实验研究。机翼的半高宽比为2，NACA 0012机翼横截面和圆形尖端。机翼围绕四分之一弦弦从4°到22°到4°呈正弦状倾斜。实验是在水平自由表面水隧道中进行的。先前已显示出降低的频率k =πfc/U_∞= 0.20时的动态失速过程会在俯仰周期中的高攻角处出现靠近机翼尖端的弧形涡旋。该弓形涡旋与尖端涡旋相互作用，并显着影响近身尾流动力学。力和力矩数据在0.02到0.30的降低频率范围内以及平面PIV在z / c = 1.7的翼展方向上的横截面中显示。在降低的频率0.30和0.20处，通过标准的轮廓可以推断出弓形涡旋的特征。在降低的频率0.10和0.05处，似乎形成了类似于拱形涡旋的初始动态失速涡旋，但很快向下游对流。在降低的频率0.03和0.02时，在所研究的跨度位置上没有相干动态失速涡旋的迹象。这显示出弓旋涡形成过程对足够不稳定的俯仰运动的依赖性。

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