Study of a stall cell using stereo particle image velocimetry
Study of a stall cell using stereo particle image velocimetry
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DOI：
10.1063/1.4869726
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发表时间：
2014-04
影响因子：
4.6
通讯作者：
M. Manolesos;S. Voutsinas
中科院分区：
文献类型：
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作者：
M. Manolesos;S. Voutsinas
基于立体粒子图像测速测量分析了机翼失速细胞（SC）的结构。所有实验均考虑雷诺数 0.87 × 106 围绕带端板且长宽比为 2.0 的矩形机翼的流动。固有不稳定的失速单元通过局部展向扰动来稳定。还结合计算流体动力学数据介绍并讨论了机翼上方和尾流中的速度、涡度和雷诺应力数据。本研究完成并澄清了先前建议的有关 SC 结构的模型。 SC 出现在分离层和后缘剪切层之间，其中识别出三种不同类型的涡流：(a) 失速单元涡流，垂直于机翼表面开始，并继续向下游与自由流对齐；(b) 分离线涡流；(c) 后缘线涡流，两者平行于机翼后缘延伸，并在涡流中心显着增长。
The structure of Stall Cells (SCs) on wings is analyzed on the basis of stereo particle image velocimetry measurements. All experiments regard a Reynolds number 0.87 × 106 flow around a rectangular wing with endplates and an aspect ratio of 2.0. The inherently unstable stall cell is stabilized by means of a localized spanwise disturbance. Velocity, vorticity, and Reynolds stress data above the wing and in the wake are presented and discussed, also in combination with Computational Fluid Dynamics data. The present study completes and clarifies the previously suggested models regarding the SC structure. The SC emerges in between the separation and trailing edge shear layer where three different types of vortices are identified: (a) the stall cell vortices that start normal to the wing surface and continue downstream aligned with the free stream, (b) the separation line vortex, and (c) the trailing edge line vortex that both run parallel to the wing trailing edge and grow significantly at the center of the s...