阵列表面电弧激励控制激波附面层干扰机理

甘甜; 王琼

doi:10.13224/j.cnki.jasp.20210285

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阵列表面电弧激励控制激波附面层干扰机理

气动热力学与总体设计 | 更新时间：2025-03-14

- 阵列表面电弧激励控制激波附面层干扰机理
- Mechanisms for shock wave boundary layer interaction control using surface arc plasma actuators array
- 航空动力学报 2022年37卷第8期页码：1683-1691
- 作者机构：
  
  1.空军工程大学装备管理与无人机工程学院，西安 710051
  2.西北工业大学动力与能源学院，西安 710072
- 作者简介：
  
  甘甜（1988-），男，讲师，博士，主要从事超声速流动控制研究，超声速无人飞行器设计研究。
- 基金信息：
  
  国家自然科学基金(11902360);中国博士后科学基金(2021M702676)
- DOI：10.13224/j.cnki.jasp.20210285
  中图分类号：
- 稿件说明：
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甘甜, 王琼. 阵列表面电弧激励控制激波附面层干扰机理[J]. 航空动力学报, 2022,37(8):1683-1691.

Tian GAN, Qiong WANG. Mechanisms for shock wave boundary layer interaction control using surface arc plasma actuators array[J]. Journal of Aerospace Power, 2022, 37(8): 1683-1691.
甘甜, 王琼. 阵列表面电弧激励控制激波附面层干扰机理[J]. 航空动力学报, 2022,37(8):1683-1691. DOI： 10.13224/j.cnki.jasp.20210285.

Tian GAN, Qiong WANG. Mechanisms for shock wave boundary layer interaction control using surface arc plasma actuators array[J]. Journal of Aerospace Power, 2022, 37(8): 1683-1691. DOI： 10.13224/j.cnki.jasp.20210285.

摘要

为了获得阵列表面电弧控制激波/附面层干扰不稳定性机理，开展了高频激励和低频激励的实验研究。综合运用高速纹影、动态压力等先进测试手段和分析方法，揭示阵列电弧等离子体激励的热效应和涡效应特性。结合流动显示和壁面动态压力脉动，深度揭示了控制过程。更为关键的，因为高频激励模式下的激励器处于低功耗状态，这样可以提供稳定的控制效果。基于动态压力频谱分析，发现高频激励下低频不稳定性能量的占比降低12.2%。结合纹影显示，获得高频激励下的涡效应主导机制。

Abstract

In order to reveal the control mechanism on shock wave/boundary layer unsteadiness，experiments were performed by using surface arc plasma actuators array based on both high⁃frequency and low frequency actuation.Advanced testing and analytical methods，including high⁃speed schlieren and dynamic pressure，were applied to reveal the thermal and vortex characteristic.The combined results of flow visualization and fluctuating wall pressure provided a valuable insight into the controlling process.More importantly，because of high⁃frequency actuation mode operating at a relatively low energy expense，this made it possible to achieve a stable control effect.Based on the reported results of the statistical analysis dynamic pressure，the percentage of the energy for low⁃frequency unsteadiness detected by spectra of pressure reduced by 12.2% at high⁃frequency forcing.Combined with schlieren display，a mechanism of shock wave boundary layer interaction control dominated by vortex effect can now be summarized.

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references

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