边条/鸭翼对前掠翼和后掠翼气动特性的影响

张冬; 陈勇; 胡孟权; 付向恒

doi:10.13700/j.bh.1001-5965.2019.0030

边条/鸭翼对前掠翼和后掠翼气动特性的影响

doi: 10.13700/j.bh.1001-5965.2019.0030

张冬¹,
陈勇^2, ,,
胡孟权²,
付向恒³

1.
空军工程大学研究生院, 西安 710051
2.
空军工程大学航空工程学院, 西安 710038
3.
北京航空航天大学自动化科学与电气工程学院, 北京 100083

基金项目:

国家自然科学基金 61473307

详细信息

作者简介:
张冬  男, 博士研究生。主要研究方向:空气动力学、飞行力学

陈勇  男, 博士, 讲师。主要研究方向:飞行力学、飞行控制

胡孟权  男, 博士, 副教授。主要研究方向:飞行力学、飞行控制

付向恒  男, 博士研究生。主要研究方向:自动控制、飞行控制

通讯作者:
陈勇, E-mail: cheny_043@163.com

中图分类号: V221⁺.3;TB553
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- 被引次数: 0
出版历程
- 收稿日期: 2019-01-22
- 录用日期: 2019-05-28
- 网络出版日期: 2019-10-20

Effect of strake and canard on aerodynamic characteristics of forward-swept wing and back-swept wing

1.
Graduate School, Air Force Engineering University, Xi'an 710051, China
2.
Aviation Engineering Institute, Air Force Engineering University, Xi'an 710038, China
3.
School of Automation Science and Electrical Engineering, Beihang University, Beijing 100083, China

Funds:

National Natural Science Foundation of China 61473307

More Information

Corresponding author: CHEN Yong, E-mail: cheny_043@163.com

摘要

摘要:
为分析前掠翼气动布局设计在航空工业中无法得到推广运用的原因，将前掠翼和后掠翼通过加装边条和鸭翼形成简化的边条翼布局、鸭式布局和边条/鸭式布局，从而深入认识前掠翼和后掠翼两种不同布局之间的流动特点以及涡系干扰机理。首先进行算例数值计算，通过对比分析计算结果与试验数据，验证了数值计算方法的可靠性和准确性；然后对不同布局进行数值计算，得到各布局的升力系数曲线；最后通过压力分布云图和流线图对各布局中复杂涡系的干扰机理进行分析。结果表明：基于后掠机翼形成的边条翼布局、鸭式布局和边条/鸭式布局中的涡系之间通过诱导和卷绕作用，涡系相互增强，大幅提高了布局的升力系数并推迟失速迎角，同时加装边条和鸭翼效果更加明显；基于前掠机翼形成的边条翼布局、鸭式布局和边条/鸭式布局中的涡系之间不存在卷绕作用，涡系之间存在碰撞挤压的不利干扰，这使得前掠翼布局在大迎角时的升力系数远远低于相应的后掠翼布局。前掠翼气动布局中的机翼前缘涡在大迎角时无法同鸭翼涡和边条涡相互耦合增强，不能充分地利用非线性升力，这是前掠翼气动布局设计中的一些不足。
- 边条 /
- 鸭翼 /
- 前掠翼 /
- 后掠翼 /
- 干扰机理
Abstract:
In order to analyze the reasons why the design of forward-swept wing aerodynamic configuration cannot be popularized and applied in aviation industry, simplified strake-wing, canard-wing and strake/canard-wing configurations were constituted by fixing strake and canard on forward-swept wing and back-swept wing, so as to deeply understand the flow characteristics and the mechanism of vortices interference between the two different configurations of forward-swept wing and back-swept wing. and First, the reliability and accuracy of numerical computation method were validated by comparing the computing results with experimental data of a standard model. Then, the lift coefficient curves of different configurations were obtained through numerical computation. Finally, the complex vortex interaction mechanism of different configurations were analyzed by pressure contours and streamlines. The results indicate that induction and convolution between vortexes of configurations based on back-swept wing enhance the lift coefficient and increase stalling angle of attack, and the effect was more apparent on the configuration fixed with strake and canard. There is no convolution effect between vortices of configurations based on forward-swept wing, and vortexes of configurations based on forward-swept wing perform an adverse interaction by bumping and squeezing, which makes the lift coefficient of the forward-swept wing much lower than that of the back-swept wing at high angles of attack. The leading-edge vortices of the forward-swept wing cannot be coupled with the canard wing vortices and strake vortices at high angles of attack, and cannot make full use of the non-linear lift force, which is the shortcoming in the aerodynamic layout design of the forward-swept wing.
- strake /
- canard /
- forward-swept wing /
- back-swept wing /
- interaction mechanism

HTML全文

图 1 BCS和FCS布局平面示意图

Figure 1. Plan sketches of BCS and FCS configurations

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图 2 计算模型网格分布

Figure 2. Grid distribution of computational model

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图 3 前掠翼计算模型和计算网格

Figure 3. Computational model and grid of forward-swept wing

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图 4 计算结果与试验数据的升力系数曲线

Figure 4. Lift coefficient curves of calculation results and experimental data

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图 5 后掠机翼各布局的升力系数曲线

Figure 5. Lift coefficient curves of various configurations based on back-swept wing

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图 6 单独后掠机翼表面压力云图和空间流线图

Figure 6. Surface pressure contours and streamlines in flow field of separate back-swept wing

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图 7 BS布局空间流线图

Figure 7. Streamlines in flow field of BS configuration

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图 8 BC布局截面及空间流线图(α=10°)

Figure 8. Streamlines over clip plane and flow field of BC configuration (α=10°)

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图 9 BC布局空间流线图

Figure 9. Streamlines in flow field of BC configuration

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图 10 不同布局表面压力云图(α=10°)

Figure 10. Surface pressure contours of different configurations (α=10°)

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图 11 BSC布局表面压力云图和空间流线图

Figure 11. Surface pressure contours and streamlines in flow field of BSC configuration

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图 12 前掠机翼各布局的升力系数曲线

Figure 12. Lift coefficient curves of various configurationsbased on forward-swept wing

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图 13 单独前掠机翼空间流线图

Figure 13. Streamlines in flow field of separate forward swept wing

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图 14 FS布局截面及空间流线图(α=10°)

Figure 14. Streamlines over clip plane and flow field of FS configuration (α= 10°)

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图 15 FS布局空间流线图

Figure 15. Streamlines in flow field of FS configuration

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图 16 FC布局截面及空间流线图(α=15°)

Figure 16. Streamlines over clip plane and flow field of FC configuration (α=15°)

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图 17 FC布局空间流线图

Figure 17. Streamlines in flow field of FC configuration

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图 18 FS和FSC布局空间流线图(α=23°)

Figure 18. Streamlines in flow field of FS and FSC configurations (α=23°)

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