连续变弯度翼型动态气动特性数值模拟

吴优; 戴玉婷; 张仁嘉; 宋晨; 杨超

doi:10.13700/j.bh.1001-5965.2020.0141

连续变弯度翼型动态气动特性数值模拟

doi: 10.13700/j.bh.1001-5965.2020.0141

吴优¹,
戴玉婷^1, ,,
张仁嘉²,
宋晨¹,
杨超¹

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
北京宇航系统工程研究所, 北京 100076

基金项目:

国家自然科学基金 11672018

详细信息

通讯作者:
戴玉婷, E-mail: yutingdai@buaa.edu.cn

中图分类号: V221.3
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- 文章访问数: 600
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- PDF下载量: 179
- 被引次数: 0
出版历程
- 收稿日期: 2020-04-15
- 录用日期: 2020-06-30
- 网络出版日期: 2021-06-20

Numerical simulation of dynamic aerodynamic characteristics of a camber morphing airfoil

1.
School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
2.
Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China

Funds:

National Natural Science Foundation of China 11672018

More Information

Corresponding author: DAI Yuting, E-mail: yutingdai@buaa.edu.cn

摘要

摘要:
针对翼型后缘连续变弯度运动中后缘边界精确数值模拟的问题，提出了基于二维多项式的时空曲面拟合方法，实现了对后缘边界时空位置的精确模拟。在此基础上，基于OpenFOAM发展了翼型后缘连续变弯度与大幅度俯仰运动耦合的运动边界数值模拟，并计算了翼型耦合运动的气动力，讨论了后缘线性/非线性变形对翼型大迎角动态气动特性的影响规律。结果表明：后缘运动对翼型俯仰运动的升阻特性影响显著，特别在翼型大幅度俯仰时后缘非线性变形对升阻特性改善效果比线性变形大6%~10%。同时还研究了翼型俯仰与后缘变形运动相位差对气动特性的影响。特别地，当相位差为180°时，后缘运动使动态失速时的最大升力提高50.3%，平均升力提高34.6%；当2种运动相位差为0°时，后缘运动使动态失速时的最大阻力降低39.7%，平均阻力降低30.2%，最大升阻比提高22.3%，平均升阻比提高16.8%；同时，翼型在动态俯仰过程中出现负阻力现象，对产生负阻力的原因进行了分析。这些结果可用于指导连续变弯度后缘控制律的设计。
- 连续变弯度翼型 /
- 动态失速 /
- 负阻力 /
- OpenFOAM /
- 动网格
Abstract:
In order to solve the problem of accurate numerical simulation of trailing edge morphing motion of a camber morphing airfoil, a spatiotemporal surface fitting method based on two-dimensional polynomial is proposed, which could accurately simulate the space-time position of the morphing trailing edge.On this basis, the numerical simulation method of the boundary motion caused by airfoil pitching motion and trailing edge morphing is developed in OpenFOAM, and the aerodynamic forces of the coupled motions of the airfoil are calculated. The results show that trailing edge motion has a significant influence on the lift and drag characteristics of the airfoil pitching motion, the effect of nonlinear deformation is 6%-10% greater than that of linear deformation in airfoil large-amplitude pitch motion. Meanwhile, the influence of phase difference between airfoil pitch motion and trailing edge motion on aerodynamic characteristics is discussed in this paper. In particular, when phase difference is 180 degree, trailing edge motion increases the maximum lift by 50.3% as well as the time-averaged lift by 34.6%. When phase difference is 0 degree, trailing edge motion reduces the maximum drag by 39.7% as well as the time-averaged drag by 30.2%. The maximum lift-drag ratio is increased by 22.3% and time-averaged lift-drag ratio by 16.8%. Meanwhile, during the airfoil pitching motion, negative drag coefficient is observed and the inducement is discussed. The above results provide important reference for the design of control law based on camber morphing airfoil.
- camber morphing airfoil /
- dynamic stall /
- negative drag /
- OpenFOAM /
- dynamic mesh

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图 1 翼段运动的分解

Figure 1. Decomposition of airfoil motion

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图 2 Γ_1xx的拟合结果

Figure 2. Fitting result of Γ_1xx

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图 3 翼型俯仰运动和后缘偏转引起的网格变形

Figure 3. Mesh deformation caused by airfoil pitch motion and trailing edge deformation

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图 4 OpenFOAM计算结果与文献[29]实验对比

Figure 4. OpenFOAM calculation results compared withexperiments of ref.[29]

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图 5 翼型俯仰运动函数

Figure 5. Pitch motion function of airfoil

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图 6 升力系数响应

Figure 6. Lift coefficient response

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图 7 0°相位差时翼型周围流场速度分布及压力分布

Figure 7. Velocity and pressure distribution of flow field around airfoil at 0° phase difference

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图 8 180°相位差时翼型周围流场速度分布及压力分布

Figure 8. Velocity and pressure distribution of flow field around airfoil at 180° phase difference

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图 9 阻力系数响应

Figure 9. Drag coefficient response

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图 10 不同迎角下连续变弯度翼型峰值气动力系数随相位变化与无偏转翼型对比

Figure 10. Peak aerodynamic coefficient variation with phase for camber morphing airfoil compared with baseline airfoil at different angle of attack

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图 11 不同迎角下连续变弯度翼型平均气动力系数随相位变化与无偏转翼型对比

Figure 11. Time-averaged aerodynamic coefficient variation with phase for camber morphing airfoil compared with baselie airfoil at different angle of attack

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图 12 连续变弯度翼型负阻力随相位变化与无偏转翼型对比

Figure 12. Negative drag variation with phase for camber morphing airfoil compared with baseline airfoil

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表 1 翼型形状参数

Table 1. Airfoil shape parameters

参数	数值
弦长l/m	1
旋转中心到前缘距离c/m	0.25
变形起始点到前缘距离p/m	0.70

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表 2 后缘中线形函数

Table 2. Shape function of trailing edge mean line

工况	ϕ(x)	A	p
0	0
1	AT(t)(x-p)	0.27	0.7
2	AT(t)(x-p)²	0.95	0.7

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表 3 计算参数设置

Table 3. Calculation parameter setting

参数	数值
雷诺数Re	1.35×10⁵
弦长l/m	0.15
参考速度U_Ref/(m·s^-1)	13.32
湍流度I/%	0.05
运动黏度ν/(kg·(m·s)^-1)	1.48×10^-5
空气密度ρ/(kg·m^-3)	1.225
最大库朗数Co	0.9
时间步长Δ t/s	Adjustable
最大时间步长Δ t_max/s	10^-5
注：Adjustble表示采用自适应步长。

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表 4 0°相位差时翼型小幅度俯仰的升力特性

Table 4. Lift characteristics of airfoil small-amplitude pitch motion at 0° phase difference %

工况	ΔC_L	ΔC_L
0 (无后缘变形)	0	0
1 (线性变形)	-34.2	-25.8
2 (非线性变形)	-34.1	-21.6

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表 5 0°相位差时翼型大幅度俯仰的升力特性

Table 5. Lift characteristics of airfoil large-amplitude pitch motion at 0° phase difference %

工况	ΔC_L	ΔC_L
0 (无后缘变形)	0	0
1 (线性变形)	-40.8	-32.5
2 (非线性变形)	-39.7	-30.2

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表 6 180°相位差时翼型小幅度俯仰的升力特性

Table 6. Lift characteristics of airfoil small-amplitude pitch motion at 180° phase difference %

工况	ΔC_L	ΔC_L
0 (无后缘变形)	0	0
1 (线性变形)	+36.0	+30.3
2 (非线性变形)	+36.0	+28.1

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表 7 180°相位差时翼型大幅度俯仰的升力特性

Table 7. Lift characteristics of airfoil large-amplitude pitch motion at 180° phase difference %

工况	ΔC_L	ΔC_L
0 (无后缘变形)	0	0
1 (线性变形)	+45.4	+28.5
2 (非线性变形)	+50.3	+34.6

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表 8 0°相位差时翼型小幅度俯仰的阻力特性和升阻比

Table 8. Drag characteristics and lift-drag ratio of airfoil small-amplitude pitch motion at 0° phase difference %

工况	ΔC_D	ΔC_D	ΔC_L/C_D
0 (无后缘变形)	0	0	0	0
1 (线性变形)	-30.5	-28.6	-5.3	-4.1
2 (非线性变形)	-30.5	-25.8	-5.3	-4.0

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表 9 0°相位差时翼型大幅度俯仰的阻力特性和升阻比

Table 9. Drag characteristics and lift-drag ratio of airfoil large-amplitude pitch motion at 0° phase difference %

工况	ΔC_D	ΔC_D	ΔC_L/C_D
0 (无后缘变形)	0	0	0	0
1 (线性变形)	-48.4	-40.5	+14.7	+12.4
2 (非线性变形)	-50.7	-40.2	+22.3	+16.8

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表 10 180°相位差时翼型小幅度俯仰的阻力特性和升阻比

Table 10. Drag characteristics and lift-drag ratio of airfoil small amplitude pitch motion at 180°phase difference %

工况	ΔC_D	ΔC_D	ΔC_L/C_D
0 (无后缘变形)	0	0	0	0
1 (线性变形)	+53.4	+44.3	-11.9	-9.7
2 (非线性变形)	+53.4	+44.0	-11.9	-10.4

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表 11 180°相位差时翼型大幅度俯仰的阻力特性和升阻比

Table 11. Drag characteristics and lift-drag ratio of airfoil large-amplitude pitch motion at 180°phase difference %

工况	ΔC_D	ΔC_D	ΔC_L/C_D
0 (无后缘变形)	0	0	0	0
1 (线性变形)	+102.2	+93.5	-28.9	-22.5
2 (非线性变形)	+96.9	+86.6	-23.7	-16.6

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