Tip vortex structure and aerodynamic loading on rotating wings in confined spaces
Tip vortex structure and aerodynamic loading on rotating wings in confined spaces
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DOI：
10.1007/s00348-014-1815-4
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发表时间：
2014-09-01
影响因子：
2.4
通讯作者：
Jones, Anya R.
中科院分区：
文献类型：
--
作者：
Manar, Field;Medina, Albert;Jones, Anya R.
在充满液体的罐中的旋转翼上进行实验，以确定产生不受壁效应影响的数据所需的最小叶尖间隙。固定在 45 度迎角的旋转机翼以 120 至 10,000 之间的雷诺数旋转两圈。通过改变机翼尺寸，叶尖间隙从 0.5 到 5 弦变化，同时还改变机翼速度以保持雷诺数恒定。对机翼进行了力测量，并对整个油箱进行了染料流可视化和粒子图像测速。还通过计算测试了 0.5-7 弦的尖端间隙。所有测量结果显示，在所有测试的雷诺数下，0.5 弦尖端间隙的尖端效应较大，并且 5 弦尖端间隙没有壁效应。对于观察到的所有雷诺数，3 弦间隙情况在粒子图像测速和染料流可视化中都显示出可忽略不计的壁效应。 3 弦尖端间隙翼上的力表明雷诺数 >1,000 时第二次旋转中出现的壁效应。对于仅限于测试雷诺数范围内的两次机翼转数的实验，5 个弦的尖端间隙被认为没有壁效应。
Experiments on a rotating wing in a liquid-filled tank were conducted to determine the minimum required tip clearance to produce data free from wall effects. A rotating wing fixed at an angle of attack of 45 degrees was revolved for two revolutions at Reynolds numbers between 120 and 10,000. Tip clearance was varied from 0.5 to 5 chords by varying wing size, while also varying wing speed to hold Reynolds number constant. Force measurements on the wing, as well as dye flow visualization and particle image velocimetry of the entire tank, were conducted. Tip clearances of 0.5-7 chords were also tested computationally. Results of all measurements show large tip effects for 0.5 chords of tip clearance, and no wall effects for 5 chords of tip clearance at all Reynolds numbers tested. The 3 chord clearance case showed negligible wall effects in both the particle image velocimetry and dye flow visualization for all Reynolds numbers observed. The forces on the 3 chord tip clearance wing indicate wall effects appearing in the second revolution for Reynolds numbers of >1,000. A tip clearance of 5 chords is deemed to be free of wall effects for experiments limited to two wing revolutions within the range of tested Reynolds numbers.