缝道几何构型对翼型气动特性的影响

郝礼书; 林梓佳; 屈昊阳; 王暕书; 高永卫

doi:10.7638/kqdlxxb-2022.0188

缝道几何构型对翼型气动特性的影响

doi: 10.7638/kqdlxxb-2022.0188

西北工业大学翼型叶栅空气动力学国家级重点实验室，西安　710072

基金项目: 科工局重点实验室稳定支持项目（D5050210009）

详细信息

通讯作者:
郝礼书（1980-），男，四川威远人，博士，副教授，研究方向：流动控制. E-mail：haolishu@nwpu.edu.cn

中图分类号: V211.3
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- 文章访问数: 14
- HTML全文浏览量: 3
- PDF下载量: 5
- 被引次数: 0
出版历程
- 收稿日期: 2022-11-25
- 录用日期: 2023-02-01
- 修回日期: 2023-01-10
- 网络出版日期: 2023-03-13

Influence of slot geometry configuration on airfoil aerodynamic characteristics

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an　710072, China

摘要

摘要: 为了深入研究翼型开缝这种抑制翼型吸力面流动分离的被动流动控制技术，对NACA4421翼型开展了数值研究。在探讨了开缝依据的基础上，设计了7种缝道构型，并给出了缝道构型之间的几何联系，对比分析了曲线、折线及直线三种形式的缝道对翼型失速的控制效果，发现曲线缝道能够显著提高翼型的最大升力系数和失速迎角；分析了曲线缝道构型升力系数“双峰”现象的机理，提出了一种新型导流片缝道构型，该构型利用“科恩达效应”能够全面改善基准翼型的失速特性，失速迎角推迟可达14°，最大升力系数提高122%，达到2.785。本文所提出的导流片缝道，是一种新型的缝道构型，为增升装置设计提供了一种思路和参考。
- 翼型开缝 /
- 数值分析 /
- 流动控制 /
- 导流片 /
- 科恩达效应
Abstract: Airfoil slotted is a passive flow control technology that can effectively inhibit flow separation on the airfoil suction surface, and it has been widely studied by researchers domestically and abroad. In this study, slots on the airfoil NACA4421 are investigated with numerical simulations. The selection of the slot location on the airfoil is first analyzed, and the influence of the geometry change of the slot on the stall characteristics of the airfoil is discussed. Seven slot configurations are designed, and the geometric relations among them are given. The flow control effects of slots with curve lines, polylines and straight lines, on the airfoil stall are compared. It is found that the curve-line slot can significantly improve the maximum lift coefficient and the stall angle of attack of the airfoil. The "double peak" phenomenon of the lift coefficient distribution of the curve-line slot airfoil is analyzed, and the design of a new deflector slot is proposed. This new slot configuration is based on the Coanda effect, and can improve the stall characteristics of the baseline airfoil comprehensively, with the stall angle of attack delayed by 14° and the maximum lift coefficient increased by 122% to 2.785. The deflector slot presented in this study provides a novel idea and reference for the design of high-lift devices.
- airfoil slotted /
- numerical analysis /
- flow control /
- deflector /
- Coanda effect

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图 1 30P-30N多段翼型网格示意图和升力特性计算验证

Figure 1. Grid diagram and numerical validation of the lift coefficient for the 30P-30N airfoil

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图 2 翼型网格收敛性研究 ($ \alpha $ = 10º)

Figure 2. Grid convergence study for the airfoil at $ \alpha $ = 10º

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图 3 基准翼型的升力和阻力系数曲线

Figure 3. Lift and drag coefficient curve of baseline airfoil

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图 4 不同迎角下翼型表面的压力分布曲线

Figure 4. Pressure distributions on the airfoil under different angles of attack

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图 5 直线缝和偏折缝的对比

Figure 5. Comparison of the slot configurations with straight lines and polylines

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图 6 基于偏折缝的局部曲线修形处理过程中的缝道对比图

Figure 6. Comparison of the slot configurations with local curve modification

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图 7 导流片缝道构型的形成过程

Figure 7. Evolution of the deflector slot configuration

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图 8 直线构型缝道翼型的升力系数和阻力系数曲线

Figure 8. Comparison of the lift and drag coefficient curves for the airfoil with different straight-line slot configurations

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图 9 迎角19°时不同直线缝道构型的翼型流场对比

Figure 9. Comparison of flow fields for the airfoil with different straight-line slot configurations at $ \mathrm{\alpha } $ = 19°

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图 10 曲线构型缝道翼型的升力系数和阻力极曲线

Figure 10. Comparison of the lift and drag coefficient curves for the airfoil with different curve slot configurations

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图 11 曲线构型缝CS3前半段和后半段翼型的压力分布对比

Figure 11. Comparison of pressure distributions for the airfoil with curve slot CS3 under different angles of attack

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图 12 迎角18°时不同曲线缝道构型的翼型流场对比

Figure 12. Comparison of flow fields for the airfoil with different curve slot configurations at $ \mathrm{\alpha } $ = 18°

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图 13 CS3缝道构型不同迎角时的翼型流场对比

Figure 13. Comparison of flow fields for the airfoil with curve slot CS3 under different angles of attack

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图 14 不同缝道构型翼型的升力系数和阻力极曲线

Figure 14. Comparison of the lift and drag coefficient curves for the airfoil with different slot configurations

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图 15 不同缝道构型的翼型前半段和后半段表面压力分布对比（$ \alpha $ = 22°）

Figure 15. Comparison of pressure distributions on the front and rear sections of the airfoil with different slot configurations at $ \mathrm{\alpha } $ = 22°

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图 16 迎角27°时不同缝道的翼型流场对比

Figure 16. Comparison of flow fields for the airfoil with different slot configurations at $ \alpha $ = 27°

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表 1 7种缝道构型几何变化关系

Table 1. Geometric relationship of 7 kinds of slot configurations

序号	名称	几何特征关系
1	SS1	直线缝道，与弦线夹角56°。
2	SS2	在1基础上缝道中部折角处理，形成“偏折斜线缝道”。
3	CS1	在2基础上对缝道中部进行曲线修形，形成曲线缝道1。
4	CS2	在3基础上针对翼型下翼面的缝道口连接位置进行曲线修形，形成曲线缝道2。
5	CS3	在4基础上仅针对翼型上表面的缝道口靠近后缘方向的连接位置进行曲线修形，形成曲线缝道3。
6	DS	在5基础上针对翼型上表面的缝道口靠近后缘方向的连接位置进行导流片设计，形成新的“导流片缝道”构型。
7	CS4	在6基础上去掉缝道口的导流片，形成曲线缝道4。

下载: 导出CSV

表 2 典型缝道构型对翼型失速特性改善对比

Table 2. Comparison among typical slot configurations for improving the stall characteristics of the airfoil

缝道构型	最大升力系数	最大升力系数提高百分比/%	失速迎角推迟度数/(°)
直线缝道^[18]	1.51	26	7
折线缝道^[21]	1.65	3	0
弧形缝道^[19]	1.19	58	3
曲线缝道CS4[本文]	1.92	53	6
导流片缝道DS[本文]	2.785	122	14

下载: 导出CSV

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