基于前缘合成双射流的飞翼布局纵向气动控制特性研究

邓雄; 赵志杰; 王秋旺; 罗振兵; 刘杰夫

doi:10.7638/kqdlxxb-2022.0049

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基于前缘合成双射流的飞翼布局纵向气动控制特性研究

研究论文 | 更新时间：2026-05-28

- 基于前缘合成双射流的飞翼布局纵向气动控制特性研究
- Research on longitudinal aerodynamic control characteristics of flying wing based on leading-edge dual synthetic jets
- 空气动力学学报 2022年40卷第5期页码：79-90
- 作者机构：
  
  1. 国防科技大学空天科学学院,长沙,410073
  2. 西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
  
  邓雄（1984-），男，博士，副教授，研究方向：飞行器流场控制与热管理. E-mail：badi_arg@126.com
  罗振兵*（1979-），男，博士，研究员，研究方向：高超声速飞行器主动流动控制. E-mail：luozhenbing@163.com
- 基金信息：
  
  国家自然科学基金（11972369，U2141252）;湖湘青年英才项目（2021RC3075）;国防科技大学青年创新奖项目（青创20190703）
- DOI：10.7638/kqdlxxb-2022.0049
  中图分类号： V211.3;O357.4
- 纸质出版：2022
- 稿件说明：
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邓雄, 赵志杰, 王秋旺, 等. 基于前缘合成双射流的飞翼布局纵向气动控制特性研究[J]. 空气动力学学报, 2022, 40(5): 79−90.

DENG Xiong, ZHAO Zhijie, WANG Qiuwang, et al. Research on longitudinal aerodynamic control characteristics of flying wing based on leading-edge dual synthetic jets[J]. 2022, 40(5): 79-90.
邓雄, 赵志杰, 王秋旺, 等. 基于前缘合成双射流的飞翼布局纵向气动控制特性研究[J]. 空气动力学学报, 2022, 40(5): 79−90. DOI： 10.7638/kqdlxxb-2022.0049

DENG Xiong, ZHAO Zhijie, WANG Qiuwang, et al. Research on longitudinal aerodynamic control characteristics of flying wing based on leading-edge dual synthetic jets[J]. 2022, 40(5): 79-90. DOI： 10.7638/kqdlxxb-2022.0049.

摘要

为兼顾飞翼布局飞行器的隐身性和气动操控性，提出了一种基于合成双射流的飞翼布局纵向气动控制技术，研究其对小后掠飞翼布局大攻角下的气动操控能力。采用数值模拟方法，分析了前缘阵列式合成双射流与不同攻角飞翼布局流场的相互作用，探究其对飞翼布局纵向气动特性的影响，最后对比了传统合成射流控制，突出了其优势。结果表明：前缘阵列式合成双射流可有效提高大攻角升力、减小阻力，增大升阻比，同时还会使俯仰力矩出现非线性变化，具备大攻角滚转姿态操控能力；合成双射流在前缘形成周期性涡结构，增强了边界层底部低速流体与主流的动量交换，提高了边界层抗逆压梯度的能力；攻角8°～10°时，合成双射流可完全抑制前缘分离，但攻角10°时，在靠近后缘处形成分离区，使升力略有减小；攻角12°时，合成双射流可推迟流动分离，分离线移动至机翼中段；攻角14°～16°时，合成双射流虽然仅可有效抑制靠近展向分离起始位置处的流动分离，但同时也增加了分离区内的流动能量，有效提高升力；攻角18°时，吸力面近乎完全分离，合成双射流虽未能有效抑制分离，但会使前缘吸力峰值回升，仍有增升、减阻的效果；与合成射流相比，合成双射流控制产生的气动变化量更大，更具应用潜力。

Abstract

This paper proposes a longitudinal aerodynamic control strategy for flying-wing aircraft utilizing dual synthetic jets to compromise the stealth performance and aerodynamic maneuverability. The performance of this method for a small-swept-angle flying wing at large attack-of-angle (AOA) is examined by investigating the interaction between leading-edge dual synthetic jets and flow fields at different AOAs. Results show that an array of dual synthetic jets at the leading edge can effectively increase lift

reduce drag

and increase the lift-to-drag ratio at large angle of attack. The nonlinearly varying pitch moment indicates that the roll attitude control at high AOAs can be realized. Dual synthetic jets induce periodically evolving vortices at the leading edge

strengthening the momentum mixing across the wall-normal direction and enhancing the capability to resist reverse pressure gradient. Depending on AOA

dual synthetic jets have varied performance. At the AOAs of 8−10 degrees

they can completely suppress the leading-edge separation

while at the AOA of 10 degrees

a small separation area around the trailing edge leads to a slight decrease of lift. At the AOA of 12 degrees

the separation line moves to the middle section of the wing. At the AOA of 14−16 degrees

they can only effectively suppress the flow separation around the spanwise front of the separation zone

but they can still improve the lift efficiency by intensifying the energy in the separation zone. At the AOA of 18 degrees

the flow over the suction surface is almost completely separated. Nevertheless

the suction at the leading edge increases so that a relatively high lift-to-drag ratio remains. Compared with traditional synthetic jets

dual synthetic jets can significantly improve aerodynamic performance

manifesting their great potential.

关键词

Keywords

references

HU T Y. Multidisciplinary design optimization for flying wing aircraft preliminary design[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2010 (in Chinese).

DENG H Q. Multidisciplinary design optimization for preliminary design of unmanned aerial vehicle with blended wing body[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017 (in Chinese).

LI F S. Research on the Application of Optimization to the Conceptual Design of Aggressive Tailless Unmanned Aerial Vehicle(UAV)[D]. Xi'an: Northwestern Polytechnical University, 2007 (in Chinese).

ZHONG F. General conceptual design and analysis of flying wing unmanned aerial vehicle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2008 (in Chinese).

PENG C. Relaxed static stability analysis of flying wing aircraft and research on its fault-tolerant flight control methods[D]. Xi'an: Northwestern Polytechnical University, 2016 (in Chinese).

WANG L, WANG L X, JIA Z R. Control features and application characteristics of split drag rudder utilized by flying wing[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(8): 1392-1399(in Chinese).

ZUO L X, WANG J J. Experimental study of the effect of AMT on aerodynamic performance of tailless flying wing aircraft[J]. Acta Aerodynamica Sinica, 2010, 28(2): 132-137 (in Chinese).

GUY Y, MORTON S, MORROW J. Numerical investigation of the flow field on a delta wing with periodic blowing and suction[C]//Proc of the Fluids 2000 Conference and Exhibit, Denver, CO. Reston, Virginia: AIAA, 2000: 2321. doi: 10.2514/6.2000-2321

GUY Y, MORROW J, MCLAUGHLIN T, et al. Velocity measurements on a delta wing with periodic blowing and suction[C]//Proc of the 38th Aerospace Sciences Meeting and Exhibit, Reno, NV. Reston, Virginia: AIAA, 2000: 550. doi: 10.2514/6.2000-550

GUY Y, MORROW J, MCLAUGHLIN T. Pressure measurements and flow field visualization on a delta wing with periodic blowing and suction[C]//Proc of the 24th Atmospheric Flight Mechanics Conference, Portland, OR. Reston, Virginia: AIAA, 1999: 4178. doi: 10.2514/6.1999-4178

XU H Y, QIAO C L, YANG H Q, et al. Active circulation control on the blunt trailing edge wind turbine airfoil[J]. AIAA Journal, 2017, 56(2): 554-570. DOI:10.2514/1.J056223

FRITH S P. Flapless control for low aspect ratio wings[D]. School of Mechanical, 2007.

HOHOLIS G. Assessment of fluidic control effectors using computational fluid dynamics[D]. University of Liverpool, 2016

CAO Y F, GU Y S, HAN J X. Development and flight testing of a fluidic thrust vectoring demonstrator[J]. Acta Aerodynamica Sinica, 2019, 37(4): 593-599(in Chinese).

SONG M, PARK S, LEE Y. Application of backstep coanda flap for supersonic coflowing fluidic thrust-vector control[J]. AIAA Journal, 2014, 52(10): 2355-2359. DOI:10.2514/1.J052971

AMITAY M, WASHBURN A E, ANDERS S G, et al. Active flow control on the stingray uninhabited air vehicle: transient behaviour[J]. AIAA Journal, 2004, 42(11): 2205-2215. DOI:10.2514/1.5697

WASHBURN A, AMITAY M. Active flow control on the STINGRAY UAV: physical mechanisms[C]//Proc of the 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2004: 745. doi: 10.2514/6.2004-745

VISSER K, NELSON R, NG T. A flow visualization and aerodynamic force data evaluation of spanwise blowing on full and half span delta wings[C]//Proc of the 27th Aerospace Sciences Meeting, Reno, NV. Reston, Virginia: AIAA, 1989: 192. doi: 10.2514/6.1989-192

NIESTROY M A, WILLIAMS D R, SEIDEL J. NATO AVT-239 task group: active flow control simulation of the tailless ICE aircraft[C]//Proc of the AIAA Scitech 2019 Forum, San Diego, California. Reston, Virginia: AIAA, 2019: 0279. doi: 10.2514/6.2019-0279

XU X P, ZHOU Z. Study on longitudinal stability improvement of flying wing aircraft based on synthetic jet flow control[J]. Aerospace Science and Technology, 2015, 46: 287-298. DOI:10.1016/j.ast.2015.07.022

XU X P, ZHOU Z. Analytical study on the synthetic jet control of asymmetric flow field of flying wing unmanned aerial vehicle[J]. Aerospace Science and Technology, 2016, 56: 90-99. DOI:10.1016/j.ast.2016.07.007

MAHMOOD G, SMITH D. Proportional aerodynamic control on a UAV model using synthetic jets[C]//Proc of the 37th AIAA Fluid Dynamics Conference and Exhibit, Miami, Florida. Reston, Virginia: AIAA, 2007: 3851. doi: 10.2514/6.2007-3851

DU H. Nanosecond pulse dielectric barrier discharge plasma actuator flow contol mechanisms and application[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017(in Chinese).

SMITH B L, GLEZER A. The formation and evolution of synthetic jets[J]. Physics of Fluids, 1998, 10(9): 2281-2297. DOI:10.1063/1.869828

LUO Z B, XIA Z X, LIU B. New generation of synthetic jet actuators[J]. AIAA Journal, 2006, 44(10): 2418-2420. DOI:10.2514/1.20747

LUO Z B, ZHAO Z J, LIU J F, et al. Novel roll effector based on zero-mass-flux dual synthetic jets and its flight test[J]. Chinese Journal of Aeronautics, 2022, 35(8): 1-6. DOI:10.1016/j.cja.2021.08.015

ZHAO Z J, LUO Z B, LIU J F, et al. Effect of reverse blowing and suction control by dual synthetic jets on airfoil flow characteristics[J]. Acta Aerodynamica Sinica, 2021, 39(6): 165-174(in Chinese).

ZHAO Z J, LUO Z B, LIU J F, et al. Flight test of aircraft three-axis attitude control without rudders based on distributed dual synthetic jets[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1220-1228(in Chinese).

ZHAO Z J, LUO Z B, XU B, et al. Novel lift enhancement method based on zero-mass-flux jets and its adaptive controlling laws design[J]. Acta Mechanica Sinica, 2021, 37(10): 1567-1579. DOI:10.1007/s10409-021-01127-6

KIM W, KIM C, JUNG K J. Separation control characteristics of synthetic jets depending on exit configuration[J]. AIAA Journal, 2012, 50(3): 559-570. DOI:10.2514/1.J051223

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