Leading edge vortex control on a delta wing with dielectric barrier discharge plasma actuators
Leading edge vortex control on a delta wing with dielectric barrier discharge plasma actuators
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DOI：
10.1063/1.4989901
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发表时间：
2017-06
影响因子：
4
通讯作者：
Lu Shen;C. Wen
中科院分区：
文献类型：
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作者：
Lu Shen;C. Wen
本文介绍了在细长三角翼上应用介质阻挡放电（DBD）等离子体激励器控制前缘涡（LEVs）的实验研究。实验是在雷诺数为50000的风洞中进行的。烟流显示表明，在前缘的DBD等离子体激励器显着修改三角翼上的涡流结构。值得注意的是，对称控制在两个半跨度和非对称控制在一个半跨度导致相反的效果上的本地LEV。粒子图像测速（PIV）表明，剪切层变形的致动器。因此，LEV芯的强度和形状都受到很大影响。六分力测量结果表明，DBD等离子体致动器的升力和阻力的影响有限，而诱导相对较大的力矩。这表明DBD等离子体激励器是一种很有前途的三角翼机动技术。
This paper presents an experimental investigation of the application of dielectric barrier discharge (DBD) plasma actuators on a slender delta wing to control the leading edge vortices (LEVs). The experiments are conducted in a wind tunnel with a Reynolds number of 50 000 based on the chord length. The smoke flow visualization reveals that the DBD plasma actuators at the leading edges significantly modify the vortical flow structure over the delta wing. It is noted that symmetric control at both semi-spans and asymmetric control at a single semi-span leads to opposite effects on the local LEVs. Particle image velocimetry (PIV) indicates that the shear layer is deformed by the actuators. Therefore, both the strength and the shape of the LEV cores are deeply affected. The six-component force measurement shows that the DBD plasma actuators have a limited effect on lift and drag while inducing relatively large moments. This suggests that the DBD plasma actuator is a promising technique for delta wing maneuvering.