Numerical simulation of nanosecond pulsed plasma actuator for cylindrical high-speed flow control

被引:0
作者
Ni, Fangyuan [1 ]
Shi, Zhiwei [1 ]
Du, Hai [1 ]
机构
[1] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics
来源
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2014年 / 35卷 / 03期
关键词
Dielectric barrier discharge; Flow control; Nanosecond pulse; Numerical simulation; Shock;
D O I
10.7527/S1000-6893.2013.0451
中图分类号
学科分类号
摘要
A computational study is performed for nanosecond-pulse dielectric barrier discharge (NS-DBD) plasma actuator using for cylindrical high-speed flow control. First, the flow field characteristic of a single NS-DBD plasma actuator in quiescent air is studied. The result shows that in the region of dielectric barrier discharge, there is a rapid injection of energy. At 5 μs after the discharge, a hot spot is formed at the downstream edge of the upper electrode. The maxima temperature of the hot spot reaches up to 900 K. The fast heating effect will result in a strong pressure perturbation and form an asymmetric perturbation wave spreading at the speed of sound. On this basis, the numerical simulation of NS-DBD plasma actuator disposed on the cylinder in the free stream Ma∞=4.6 is presented in this paper. Studies have shown that as the compression wave travels upstream, it interacts with the bow-shock and momentarily increases the bow-shock standing distance and weakens the shock strength, thus resulting in a drag decrease by as much as 13%.
引用
收藏
页码:657 / 665
页数:8
相关论文
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