合成双射流控制水下圆柱绕流流动分离数值模拟研究

李潮隆; 夏智勋; 罗振兵; 邓雄; 杨升科; 王林

doi:10.7638/kqdlxxb-2018.0224

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合成双射流控制水下圆柱绕流流动分离数值模拟研究

研究论文 | 更新时间：2026-05-28

- 合成双射流控制水下圆柱绕流流动分离数值模拟研究
- Numerical study on flow separation of underwater cylinder with dual synthetic jets actuator
- 空气动力学学报 2020年38卷第2期页码：254-259, 267
- 作者机构：
  
  国防科技大学空天科学学院,长沙,410073
- 作者简介：
  
  李潮隆(1995-), 男, 硕士研究生, 研究领域为主动流动控制.E-mail:lichaolong13@nudt.edu.cn
  罗振兵*(1979-), 男, 教授, 研究领域为流动控制.E-mail:luozhenbing@163.com
- 基金信息：
  
  国家自然科学基金（11572349，11872374，11602299）
- DOI：10.7638/kqdlxxb-2018.0224
  中图分类号： O355
- 纸质出版：2020
- 稿件说明：
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李潮隆, 夏智勋, 罗振兵, 邓雄, 杨升科, 王林. 合成双射流控制水下圆柱绕流流动分离数值模拟研究[J]. 空气动力学学报, 2020, 38(2): 254-259, 267.

LI Chaolong, XIA Zhixun, LUO Zhenbing, et al. Numerical study on flow separation of underwater cylinder with dual synthetic jets actuator[J]. 2020, 38(2): 254-259, 267.
李潮隆, 夏智勋, 罗振兵, 邓雄, 杨升科, 王林. 合成双射流控制水下圆柱绕流流动分离数值模拟研究[J]. 空气动力学学报, 2020, 38(2): 254-259, 267. DOI： 10.7638/kqdlxxb-2018.0224.

LI Chaolong, XIA Zhixun, LUO Zhenbing, et al. Numerical study on flow separation of underwater cylinder with dual synthetic jets actuator[J]. 2020, 38(2): 254-259, 267. DOI： 10.7638/kqdlxxb-2018.0224.

摘要

为了探究合成双射流激励器及出口射流参数对圆柱绕流流动分离的控制效果，首次对合成双射流控制水下圆柱绕流流动分离进行了数值模拟。数值计算结果显示：保持激励器出口射流振幅不变的条件下，出口射流频率等于尾迹涡脱落特征频率时，射流控制作用与绕流流场耦合效果最好，控制流动分离效果最佳；保持出口射流频率为尾迹涡脱落特征频率时，在数值计算测试范围内，随着射流振幅的增大，射流对于流场的动量掺混能力增强，控制效果也随之增强。机理分析表明：合成射流位于前驻点的控制，主要通过在圆柱前缘形成虚拟气动外型来达到减阻控制的效果；而合成射流位于后驻点的控制，主要是通过增强回流区的动量掺混来提高回流区抑制分离的能力，从而达到减阻控制的效果。

Abstract

The effect of dual synthetic jets actuator (DSJA) and jets parameters is studied on the flow separation of cylindrical surface by a two-dimensional numerical simulation. The results show that the characteristics of the simulated flow field are consistent with the theoretical and actual distribution. When the working frequency of the actuator is equal to the characteristic frequency of the wake vortices shedding with constant actuator amplitude

the control effect of flow separation is the best. Keeping the actuator frequency as the characteristic frequency

the momentum blending effect of the jet on the flow field is enhanced by increasing jet amplitude

and the control effect is also enhanced. Finally

the control mechanism of the synthetic dual jet at the front stagnation point and the back stagnation point of the cylinder is illustrated. The control effect at front stagnetion mainly decreases the drag through the virtual aerodynamic shape formed by the jet; the control at back stagnation point is realized mainly through the jet forming a low pressure zone at the back edge of the cylinder to accelerate and promote the reattachment of the separation vortex to decreases the drag.

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references

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