### 脉冲表面电弧放电对高超声速压缩拐角非定常控制机理研究

1. 1. 西北工业大学
2. 空间物理重点实验室
3. 中国运载火箭技术研究院空间物理实验室
4. 中国运载火箭技术研究院
5. 北京临近空间飞行器系统工程研究所
• 收稿日期:2022-07-01 修回日期:2022-09-17 出版日期:2022-09-22 发布日期:2022-09-22
• 通讯作者: 陈真利

### Mechanism analysis of near surface DC arc discharge on the unsteady control of hypersonic compression corner

• Received:2022-07-01 Revised:2022-09-17 Online:2022-09-22 Published:2022-09-22

Abstract: Recently, a large number of experimental results indicate that the pulsed surface arc discharge plasma has a good ability to control the shock position and shock wave/boundary layer interaction (SWBLI) in the hypersonic flows. Be-cause of the short discharge time, strong electromagnetic interference and limited discharge area, it’s very difficult to obtain quantitative experimental data. In the most of experiments only qualitative Schlieren images were obtained. In order to reveal the unsteady control mechanism of pulsed surface arc discharge plasma, it’s necessary to establish a numerical simulation method for the interactions between the surface arc discharge plasma and the hypersonic flows. In present work, the unsteady control mechanism of pulsed surface arc discharge plasma on hypersonic compression corner flow is studied by using numerical and experimental methods. Based on the theoretical analysis and experi-mental results, a three-dimensional phenomenological model of the pulsed surface arc discharge is established. Joule-heating generated by arc discharge is added to the energy equation as a spatial power density source term to simulate the interaction between the surface arc discharge plasma and the hypersonic compression corner flow. The numerical Schlieren images at different times were predicted well compared with that of experiment, which verifies the correctness of the phenomenological model. The unsteady numerical results reveal the interaction mechanism be-tween the arc discharge plasma and the double wedge hypersonic flow. The local Joule-heating generated by the sur-face arc discharge induces the formation of the near-wall separation zone, which leads to the increase of the local displacement thickness and the formation of the unsteady virtual wedge moving along the wall. The moving virtual wedge generates an oblique shock wave with varying strength, which was reflected by with the front wedge shock wave forming an unsteady shock/shock interaction. The thermal gas bulb generated by arc discharge can effectively regulate the oblique shock wave. In a single pulse discharge, the maximum drag reduction is around 2%, and the maximum pitch moment change is around 3%.