Numerical Simulation of Wake Deflection Control around NACA0012 Airfoil Using Active Morphing Flaps
Numerical Simulation of Wake Deflection Control around NACA0012 Airfoil Using Active Morphing Flaps
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DOI：
10.4236/jfcmv.2020.83007
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发表时间：
2020
期刊：
影响因子：
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通讯作者：
Yoshiaki Abe;T. Konishi;T. Okabe
中科院分区：
文献类型：
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作者：
Yoshiaki Abe;T. Konishi;T. Okabe
本研究展示了一个主动流动控制偏转方向的尾涡结构后NACA0012翼型使用主动变形襟翼。在弦雷诺数为10，000的情况下进行了二维直接数值模拟，并严格研究了受控和非受控尾流中的涡型以及驱动频率对控制能力的影响。发现在F + = 2.00附近存在一个最佳激励频率区域，该区域由弦长和自由速度归一化。根据威廉姆森的分类[1] [2]，控制良好情况下的尾涡模式被分类为2P尾涡模式，其中强迫振荡频率对应于无控制的自然涡脱落频率。目前的分类的尾涡模式和尾流偏转控制的最佳频率区的发现，可以导致一个更强大的设计适用于涡激振动（VIV）相关的工程系统。
This study demonstrates an active flow control for deflecting a direction of wake vortex structures behind a NACA0012 airfoil using an active morphing flap. Two-dimensional direct numerical simulations are performed for flows at the chord Reynolds number of 10,000, and the vortex pattern in the controlled and noncontrolled wakes as well as the effect of an actuation frequency on the control ability are rigorously investigated. It is found that there is an optimum actuation-frequency regime at around F + = 2.00 which is normalized by the chord length and freestream velocity. The wake vortex pattern of the well-controlled case is classified as the 2P wake pattern according to the Williamson’s categorization [1] [2], where the forced oscillation frequency corresponds to the natural vortex shedding frequency without control. The present classification of wake vortex patterns and finding of the optimum frequency regime in the wake deflection control can lead to a more robust design suitable for vortex-induced-vibration (VIV) related engineering systems.