Flow control over a NACA 0012 airfoil using dielectric-barrier-discharge plasma actuator with a Gurney flap
Flow control over a NACA 0012 airfoil using dielectric-barrier-discharge plasma actuator with a Gurney flap
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DOI：
10.1007/s00348-012-1263-y
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发表时间：
2012-02
影响因子：
2.4
通讯作者：
Lihao Feng;T. Jukes;K. Choi;Jinjun Wang
中科院分区：
文献类型：
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作者：
Lihao Feng;T. Jukes;K. Choi;Jinjun Wang
在风洞中对带有Gurney襟翼的NACA 0012翼型进行了流动控制研究，结果表明，在襟翼上安装介质阻挡放电（DBD）等离子体激励器可以进一步增加升力，但阻力损失较小。时间分辨PIV测量的近尾流区域表明，等离子体迫使尾流向下移动，减少其再循环长度。尾涡动力学分析表明，等离子体激励器最初通过沿Gurney襟翼下游表面沿着增加动量来放大较低的尾流剪切层。这增强了上下尾涡之间的相互夹带，导致翼型升力增加。
Flow control study of a NACA 0012 airfoil with a Gurney flap was carried out in a wind tunnel, where it was demonstrated that a dielectric-barrier-discharge (DBD) plasma actuator attached to the flap could increase the lift further, but with a small drag penalty. Time-resolved PIV measurements of the near-wake region indicated that the plasma forcing shifted the wake downwards, reducing its recirculation length. Analysis of wake vortex dynamics suggested that the plasma actuator initially amplified the lower wake shear layer by adding momentum along the downstream surface of the Gurney flap. This enhanced mutual entrainment between the upper and lower wake vortices, leading to an increase in lift on the airfoil.