合成双射流逆向吹吸控制对翼型流动特性影响

赵志杰; 罗振兵; 刘杰夫; 邓雄; 李石清; 郑穆

doi:10.7638/kqdlxxb-2021.0213

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合成双射流逆向吹吸控制对翼型流动特性影响

翼型研究新进展 | 更新时间：2026-05-28

- 合成双射流逆向吹吸控制对翼型流动特性影响
- Effect of reverse blowing and suction control by dual synthetic jets on airfoil flow characteristics
- 空气动力学学报 2021年39卷第6期页码：165-174
- 作者机构：
  
  国防科技大学空天科学学院,长沙,410073
- 作者简介：
  
  赵志杰（1997-），男，博士生，主要研究方向：飞翼飞行器主动流动控制技术. E-mail：ji_yo_100@163.com
  罗振兵*（1979-），男，博士，教授，主要研究方向：飞行器主动流动控制技术. E-mail：luozhenbing@163.com
- 基金信息：
  
  国家自然科学基金面上项目（11972369，11872374）;国防科技大学青年科技创新奖资助项目（434517314）
- DOI：10.7638/kqdlxxb-2021.0213
  中图分类号： TP602;O357.4
- 纸质出版：2021
- 稿件说明：
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赵志杰, 罗振兵, 刘杰夫, 等. 合成双射流逆向吹吸控制对翼型流动特性影响[J]. 空气动力学学报, 2021, 39(6): 165−174.

ZHAO Zhijie, LUO Zhenbing, LIU Jiefu, et al. Effect of reverse blowing and suction control by dual synthetic jets on airfoil flow characteristics[J]. 2021, 39(6): 165-174.
赵志杰, 罗振兵, 刘杰夫, 等. 合成双射流逆向吹吸控制对翼型流动特性影响[J]. 空气动力学学报, 2021, 39(6): 165−174. DOI： 10.7638/kqdlxxb-2021.0213

ZHAO Zhijie, LUO Zhenbing, LIU Jiefu, et al. Effect of reverse blowing and suction control by dual synthetic jets on airfoil flow characteristics[J]. 2021, 39(6): 165-174. DOI： 10.7638/kqdlxxb-2021.0213.

摘要

为探究合成双射流（Dual Synthetic Jets，DSJ）技术对飞行器航向姿态的控制能力，采用数值模拟的方法，研究了反向DSJ对小攻角、大攻角下翼型绕流流场的控制机理及气动控制特性，并通过飞行试验验证了其航向姿态控制能力。结果表明：小攻角下，反向DSJ会使阻力增大，升力略有减小，俯仰力矩基本不变；大攻角下，反向DSJ会使升力、阻力及低头力矩增大。小攻角下施加控制后，激励器出口前由于射流的阻挡作用形成高压区，伴随着流向逆压梯度的增加，分别在两个出口后形成准定常低压回流区，致使前后压差阻力增大，但压力包络面积基本不变，故升力变化不大；大攻角下施加控制后，除了会在射流出口前、后分别形成高压区、低压区外，还会使背风面流动提前分离，扩大分离区域面积，同时也会减小分离区内的压力值，扩大压力包络，增大阻力的同时，也会提升升力。飞行试验结果表明，反向DSJ具有对飞行器巡航时航向姿态的控制能力，可实现的最大偏航角速度为9.01°/s。

Abstract

To explore the control capability of dual synthetic jets (DSJ) on the heading attitude of flight vehciles

numerical simulations were carried out to study the aerodynamic characteristics and control mechanism of reverse DSJ actuators on the airfoil flow field at both small and large angles of attack. Meanwhile

flight tests were also implemented to verify its control ability of the heading attitudes. The results show that at a small angle of attack

the reverse DSJ can increase the drag and decrease the lift slightly

while the pitching moment basically remains unchanged. At a large angle of attack

however

the lift

drag

and nose-down pitching moment can be increased by the reverse DSJ. At a small angle of attack

high-pressure zones and low-pressure recirculation zones are formed before and after the actuator exits due to the resistant effect of the jet

which causes the increase of the pressure difference induced drag. As the pressure envelope remains basically unchanged

the lift variation is negligible. At a large angle of attack

in addition to the formation of high-pressure and low-pressure zones before and after the jet exits

flow separation in the leeward side of the airfoil occurs in advance

enlarging the flow separation

reducing the pressure inside the separation region and augmenting the area of pressure envelope

which leads to the increase of both the lift and drag forces. Results of the flight tests show that the reverse DSJ can achieve an effective control of the heading attitude during the cruising flight

with a maximum yaw angular velocity of 9.01°/s.

关键词

Keywords

references

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