Simulation Study of Arc Discharge Plasma Actuator for Supersonic Compressor Cascade Shock Wave/Boundary Layer Interaction Control

被引：0

作者：

Sheng J.-M. ^{[1
]}

Zhang H.-D. ^{[1
]}

Wu Y. ^{[1
]}

Tang M.-X. ^{[1
]}

Gao L.-M. ^{[2
]}

机构：

[1] Science and Technology on Plasma Dynamics Laboratory, Aeronautics Engineering College, Air Force Engineering University, Xi'an

[2] School of Power and Energy, Northwestern Polytechnical University, Xi'an

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2020年 / 41卷 / 10期

关键词：

Flow control; Numerical simulation; Plasma; Shock wave/boundary layer interaction; Supersonic cascade;

D O I：

10.13675/j.cnki.tjjs.190803

中图分类号：

学科分类号：

摘要：

In order to study the control effect of the arc discharge plasma actuator for the supersonic compressor cascade shock wave/boundary layer interaction, a phenomenological model for simulating the effect of plasma actuation was first established, and the ARL-SL19 supersonic cascade was taken as a research object. The interaction between the arc discharge plasma with the internal flow of the cascade passage and effects of the interaction on the cascade flow loss were studied by numerical simulation. The results show that the plasma phenomenological model can better simulate the aerodynamic characteristics of shock waves induced by arc discharge plasma. The arc discharge plasma has three main effects on the internal flow of the cascade passage: in the discharge region, the injected heat has blocking effect, which increases the flow loss of the near wall airflow; in the shock wave/ boundary layer interaction region, the shock wave system structure can be changed and the shock wave loss can be reduced; in the wake region, the shock wave induces a shedding vortex. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：2228 / 2236

页数：8

共 28 条

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