鸭式布局大迎角复杂涡系干扰与控制技术

刘沛清; 易渊

doi:10.7638/kqdlxxb-2019.0022

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鸭式布局大迎角复杂涡系干扰与控制技术

研究论文 | 更新时间：2026-05-28

- 鸭式布局大迎角复杂涡系干扰与控制技术
- Vortex interaction mechanism and control technology of canard configuration at high angle of attack
- 空气动力学学报 2020年38卷第6期页码：1034-1046
- 作者机构：
  
  北京航空航天大学陆士嘉实验室,北京,100191
- 作者简介：
  
  刘沛清(1960-), 男, 陕西忻州人, 教授, 研究方向:旋涡分离流动及控制, 高速层流控制, 现代高效轻质螺旋桨设计与优化, 大型飞机起降气动特性、地面效应和水上迫降性能.E-mail:lpq@buaa.edu.cn
- 基金信息：
  
  国家自然科学基金（11772033）
- DOI：10.7638/kqdlxxb-2019.0022
  中图分类号： V211.43
- 纸质出版：2020
- 稿件说明：
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刘沛清, 易渊. 鸭式布局大迎角复杂涡系干扰与控制技术[J]. 空气动力学学报, 2020, 38(6): 1034-1046.

LIU Peiqing, YI Yuan. Vortex interaction mechanism and control technology of canard configuration at high angle of attack[J]. 2020, 38(6): 1034-1046.
刘沛清, 易渊. 鸭式布局大迎角复杂涡系干扰与控制技术[J]. 空气动力学学报, 2020, 38(6): 1034-1046. DOI： 10.7638/kqdlxxb-2019.0022.

LIU Peiqing, YI Yuan. Vortex interaction mechanism and control technology of canard configuration at high angle of attack[J]. 2020, 38(6): 1034-1046. DOI： 10.7638/kqdlxxb-2019.0022.

摘要

为了充分探讨近距耦合鸭式布局在大迎角机动飞行中的气动特点和控制技术，通过总结大量的流动显示和测力测压实验，以大迎角下鸭翼涡和主翼涡的干扰机理研究结果为基础，开展了鸭式布局涡系控制研究，旨在提出一种有效可行的大迎角鸭翼涡控制技术。结果表明：在鸭式布局中，鸭翼涡和主翼涡之间的干扰方式主要表现为涡系诱导、卷绕和破裂，特别是在大迎角下鸭翼涡与主翼涡在主翼头部区域通过诱导作用，在向下游发展中相互卷绕合并成单一集中涡，该集中涡后期因受逆压梯度和黏性的作用而出现破裂，由此将会明显损失涡升力，同时增加阻力。在这种情况下，如果对鸭翼进行展向吹气，可通过控制鸭翼涡，影响主翼涡的演变，改变涡系的诱导和卷绕，从而可以有效延迟主翼涡的破裂，达到增升减阻的作用。鸭翼展向脉冲吹气是通过迟滞效应而节省吹气量的有效方法，实验发现提高占空比、脉冲频率，可以使布局在较低的引气量下达到连续吹气的增升效果；在相同的增升效果下，脉冲频率越高，脉冲占空比越大，节省的吹气量也越大，在28°迎角时以0.3的吹气动量系数进行频率为5 Hz、占空比为0.2的脉冲吹气，即可达到以0.25的吹气动量系数连续吹气的升力幅值，节省吹气量可达76%。

Abstract

The vortex interaction mechanism and control technology of the close-coupled canard configuration at high angles of attack have been reviewed

and the vortex control technology of canard-span wise continuous or pulse blowing have been analyzed and discussed in detail. The results show that the aerodynamic performances could be improved at middle and large angles of attack in canard configuration through the interactions between the canard vortex and the wing vortex. The flow field near the apex of the main wing is affected by the down-wash effect of the canard

in the following downstream development

the co-rotating vortex pair gradually merges into a single stable concentrated vortex by mutual introduction

and finally develops into the concentrated vortex breakdown. Through canard-spanwise blowing

the vortex interactions on the wing might be transformed so the vortex breakdown could be delayed

therefore the maximum lift and stall angle could be further enlarged and the drag force could be reduced. The canard-spanwise pulse blowing can save the blow volume through the hysteresis effect. Either larger duty ratio or higher pulse frequency is conducive to achieve the target lift with a lower bleed air volume. With the same lift increment

the higher the pulse frequency

the smaller the corresponding pulse duty ratio

and the greater the amount of blowing could be saved. For instance

compared with continuous blowing with volume coefficient of 0.25 at 28°

the pulse blowing with volume coefficient of 0.3 could achieve the same lift amplitude under the frequency of 5 Hz and duty cycle of 0.2

which saves the air volume up to 76%.

关键词

Keywords

references

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