Delaying leading edge vortex detachment by plasma flow control at topologically critical locations
Delaying leading edge vortex detachment by plasma flow control at topologically critical locations
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DOI：
10.1103/physrevfluids.6.023101
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发表时间：
2020-03
期刊：
影响因子：
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通讯作者：
J. Kissing;Bastian Stumpf;J. Kriegseis;J. Hussong;C. Tropea
中科院分区：
文献类型：
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作者：
J. Kissing;Bastian Stumpf;J. Kriegseis;J. Hussong;C. Tropea
扑翼推进提供了无与伦比的机动性和效率在低飞行速度和悬停。这些优点归因于在非定常机翼上发展的前缘涡，它引起附加升力。我们提出并验证了一个操纵假设，允许延长的前缘涡的增长阶段，通过延迟其脱离与援助的流动控制。这种方法的目标是增加非定常翼型的总升力。利用介质阻挡放电等离子体激励器成功地压缩了俯仰和纵倾平板上主涡上游的次级结构。为了确定流动控制的时机和位置，使用翼型表面上的切向速度，该切向速度也用于量化流动控制的拓扑效应。然后对不同的运动学和NACA 0012翼型进行了流量控制试验。在所有有流动控制的情况下，前缘涡的峰值环量显著增加约20%，表明这种方法适用于各种运动学、动力学和翼型。
Flapping wing propulsion offers unrivalled manoeuvrability and efficiency at low flight speeds and in hover. These advantages are attributed to the leading edge vortex developing on an unsteady wing, which induces additional lift. We propose and validate a manipulation hypothesis that allows prolongation of the leading edge vortex growth phase, by delaying its detachment with the aid of flow control. This approach targets an overall lift increase on unsteady airfoils. A dielectric barrier discharge plasma actuator is successfully used to compress secondary structures upstream of the main vortex on a pitching and plunging flat plate. To determine flow control timing and location, the tangential velocity on the airfoil surface is used, which is also used to quantify topological effects of flow control. This flow control is then tested for different motion kinematics and on a NACA 0012 airfoil. Significant increase of the peak circulation of the leading edge vortex of about 20% for all cases with flow control indicates that this approach is applicable for various kinematics, dynamics and airfoil types.