Flow field control characteristics of dual synthetic jet thrust vectoring

SHI Shuo; DENG Xiong; LUO Zhenbing; WANG Hao; GONG Jianyu; WANG Yangxiao; ZHAO Zhijie

doi:10.7638/kqdlxxb-2025.0080

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Flow field control characteristics of dual synthetic jet thrust vectoring

更新时间：2026-05-28

- Flow field control characteristics of dual synthetic jet thrust vectoring
- Vol. 43, Issue 11, Pages: 130-144(2025)
- 作者机构：
  
  国防科技大学空天科学学院,长沙,410073
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0080
  CLC： O358;TP6
- Published：2025
- 稿件说明：
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石硕, 邓雄, 罗振兵, 等. 合成双射流推力矢量流场控制特性[J]. 空气动力学学报, 2025, 43(11): 130−144.

SHI Shuo, DENG Xiong, LUO Zhenbing, et al. Flow field control characteristics of dual synthetic jet thrust vectoring[J]. 2025, 43(11): 130-144.
石硕, 邓雄, 罗振兵, 等. 合成双射流推力矢量流场控制特性[J]. 空气动力学学报, 2025, 43(11): 130−144. DOI： 10.7638/kqdlxxb-2025.0080

SHI Shuo, DENG Xiong, LUO Zhenbing, et al. Flow field control characteristics of dual synthetic jet thrust vectoring[J]. 2025, 43(11): 130-144. DOI： 10.7638/kqdlxxb-2025.0080.

摘要

为研究合成双射流推力矢量流场控制特性，通过调节合成双射流峰值速度和激励频率，揭示其对喷管主流偏转的控制机理，并通过动力学模态分解（dynamic mode decomposition

DMD）方法提取流场主导模态分析合成双射流对流动结构的调控机制，在34 m/s来流下探究飞翼耦合喷管的主流偏转情况。结果表明：合成双射流峰值速度的提高使流场低压区影响范围扩大，主流偏转角增大至22°；提高合成双射流激励频率有助于主流偏转角增大，且在激励频率大于100 Hz时主流偏转角趋于稳定。在流场控制机理方面，合成双射流下出口在吸程时吸入主流形成低压区导致主流偏转，吹程时主流偏转回中使下游壁面形成附壁分离涡；上出口存在的卷吸引射效应加速了被动二次流。进一步通过DMD方法发现，合成双射流布置处及下游壁面均出现了主导性涡量脉动和速度脉动，表明合成双射流凭借较小的能量占比主导了流场的模态特性，下游壁面对主流偏转起到了增强作用。同时，研究发现，现有构型使喷管上壁面产生回流现象，抑制喷管主流偏转，最大偏转角仅为10°。

Abstract

To investigate the flow control characteristics of a dual synthetic jet in thrust vectoring

the peak velocity and excitation frequency of the dual synthetic jet were adjusted to reveal its control mechanisms over the nozzle mainstream deflection. The dynamic mode decomposition method was applied to extract and analyze the dominant flow field modes. Concurrently

an external flow of 34 m/s was applied to examine the mainstream deflection in the nozzle coupled with a flying wing structure. Results indicate that increasing the peak velocity of the dual synthetic jet expands the influence range of the low-pressure region in the flow field

leading to an increase in the mainstream deflection angle to 22°. Elevating the excitation frequency of the dual synthetic jet promotes the growth of the mainstream deflection angle

which tends to stabilize when the frequency exceeds 100 Hz. Regarding the flow control mechanism: during the suction cycle

the ventral orifice of the dual synthetic jet ingests the mainstream

forming a localized low-pressure region that induces mainstream deflection; during the blowing cycle

the mainstream recenters

causing the formation of wall-attached separation vortices on the downstream wall. The dorsal orifice exhibits a critical vortex entrainment and ejection effect that accelerates the passive secondary flow. Further dynamic mode decomposition analysis revealed dominant vorticity and velocity fluctuations occurring both at the location of the dual synthetic jet installation and on the downstream wall. This demonstrates that the dual synthetic jet

despite its minimal energy contribution

governs the modal characteristics of the flow field

while the downstream wall enhances the mainstream deflection. Simultaneously

simulation studies on the flying-wing-coupled nozzle revealed that the current configuration induces flow recirculation on the upper wall

which suppresses the nozzle's mainstream deflection

resulting in a maximum deflection angle of only 10°.

关键词

Keywords

references

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