基于动力学模态分解的柔性膜翼增升机制

doi:10.7527/S1000-6893.2024.30618

Abstract

Abstract:

Membrane airfoils can adaptively improve the flow distribution on the surface of the airfoil using aeroelastic effects in the low Reynolds number flow， which offers a novel aerodynamic design concept for smart aerocraft. In this paper， the membrane material is directly applied to the design of airfoil. Numerical calculations for the fluid-structure interaction of the membrane airfoil with different angles of attack and length of membrane are conducted. Modal analysis of the flow field of the membrane airfoil is performed based on dynamic mode decomposition. The results indicate that compared to the rigid airfoil， the membrane airfoil shows lift enhancement when there exists a lock-in phenomenon between the flow and the membrane structure. The lift enhancement of the membrane airfoil at the angle of attack of 16° is 21.74%， which is attributed to the energy feedback of pressure propagation generated by membrane vibration on the shear layer of the flow. The lift enhancement of the membrane airfoil with the length of membrane of 0.65 times the chord length is 14.22%. The upper surface of the membrane airfoil in this configuration can generate a downstream pressure propagation with a large pressure phase gradient， which allows the flow on the surface can obtain the maximum energy from structural vibration feedback. The lift enhancement of the membrane airfoil in this configuration is much greater than that in other configurations. The proposed methods and research conclusions can provide important theoretical support for active flow control.

Key words: flexible membrane airfoil, dynamic mode decomposition, lift improvement, energy feedback, flow control

CLC Number:

V211.3

Shilin HU, Bingzhou CHEN, Wei KANG. Lift improvement mechanism of membrane airfoil using dynamic mode decomposition[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130618.

Figures/Tables 17

Fig.1

Fig.2

Fig.3

Table 1

Table 2

Table 3

Dominant DMD mode frequencies and growth rates of membrane airfoils with different AOAs

DMD模态	AOA=4°		AOA=8°		AOA=12°		AOA=16°
DMD模态	频率/Hz	增长率	频率/Hz	增长率	频率/Hz	增长率	频率/Hz	增长率
1	5.49	0.000 887	4.75	4.99 $×$ 10^-10	3.35	1.66 $×$ 10^-10	2.20	4.15 $×$ 10^-11
2	10.98	0.013 700	3.80	2.18 $×$ 10^-9	1.75	1.84 $×$ 10^-11	4.20	7.59 $×$ 10^-11
3			4.00	2.06 $×$ 10^-9	2.10	4.91 $×$ 10^-11	1.90	7.87 $×$ 10^-11
4			4.90	7.71 $×$ 10^-8	2.90	3.47 $×$ 10^-11	0.90	1.59 $×$ 10^-11

Table 3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 4

Dominant DMD mode frequencies and growth rates of membrane airfoils with different LMs

DMD模态	LM=0.55c		LM=0.60c		LM=0.65c		LM=0.70c
DMD模态	频率/Hz	增长率	频率/Hz	增长率	频率/Hz	增长率	频率/Hz	增长率
1	3.55	1.98 $×$ 10^-3	3.58	7.01 $×$ 10^-4	4.57	4.34 $×$ 10^-3	4.20	4.81 $×$ 10^-3
2	1.78	4.61 $×$ 10^-5	5.38	5.41 $×$ 10^-3	2.28	5.65 $×$ 10^-4	3.96	1.01 $×$ 10^-3
3	5.33	4.45 $×$ 10^-3	1.80	2.20 $×$ 10^-4	6.84	4.18 $×$ 10^-3	4.30	1.82 $×$ 10^-3
4	3.57	1.15 $×$ 10^-3	8.96	6.53 $×$ 10^-5	9.12	6.87 $×$ 10^-3	4.11	6.10 $×$ 10^-3

Table 4

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

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AOA/（°）	振动频率/Hz
AOA/（°）	一阶	二阶
4	5.50	11.00
8	3.80	4.70
12	3.40	4.10
16	2.10	2.30

LM/c	振动频率/Hz
LM/c	一阶	二阶
0.55	3.55	5.30
0.60	3.60	5.40
0.65	4.60	6.90
0.70	4.20	4.00
0.75	3.80	4.70

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Lift improvement mechanism of membrane airfoil using dynamic mode decomposition

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