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Flow separation on flapping and rotating profiles with spanwise gradients

机译：用翼展梯度拍打和旋转轮廓上的流动分离

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摘要

The growth of leading-edge vortices (LEV) on analogous flapping and rotating profiles has been investigated experimentally. Three time-varying cases were considered: a two-dimensional reference case with a spanwise-uniform angle-of-attack variation a; a case with increasing a towards the profile tip (similar to flapping flyers); and a case with increasing a towards the profile root (similar to rotor blades experiencing an axial gust). It has been shown that the time-varying spanwise angle-of-attack gradient produces a vorticity gradient, which, in combination with spanwise flow, results in a redistribution of circulation along the profile. Specifically, when replicating the angle-of-attack gradient characteristic of a rotor experiencing an axial gust, the spanwise-vorticity gradient is aligned such that circulation increases within the measurement domain. This in turn increases the local LEV growth rate, which is suggestive of force augmentation on the blade. Reversing the relative alignment of the spanwise-vorticity gradient and spanwise flow, thereby replicating that arrangement found in a flapping flyer, was found to reduce local circulation. From this, we can conclude that spanwise flow can be arranged to vary LEV growth to prolong lift augmentation and reduce the unsteadiness of cyclic loads.
机译：实验研究了相似拍打和旋转型材的前沿涡旋（LEV）的生长。考虑了三种时隙：具有始线均匀的攻角变化A的二维参考箱;随着朝向剖面尖端的情况（类似于拍打飞行器）;和朝向轮廓根的壳体增加（类似于经历轴向阵风的转子叶片）。已经表明，时变的曲率攻击梯度产生涡度梯度，其与翼展流程组合，导致沿着轮廓的循环的再分配。具体地，当复制经历轴向阵风的转子的攻击角梯度特性时，对准翼展涡度梯度使得循环在测量域内增加。这反过来又增加了当地的Lev增长率，这是刀片上的力量增强速度。反转翼展涡度梯度和翼展的相对对准和翼展流动，从而发现在拍摄飞行器中发现的布置，发现了减少局部循环。由此，我们可以得出结论，可以将翼展流量布置成改变Lev生长以延长升高增强并降低循环负载的不稳定性。

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