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Nonlinear aerodynamic characteristics and modeling of a quasi-flat plate at torsional vibration: effects of angle of attack and vibration amplitude

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Abstract

The clarification of the nonlinear and unsteady aerodynamic characteristics of a quasi-flat plate is of great importance to predict its wind-induced post-flutter behavior. Forced motion wind tunnel tests on a quasi-flat plate sectional model with a width-over-thickness ratio of 62.5:1 are conducted using the synchronous measurement of the dynamic forces and torsional displacements at various initial angles of attack (AoAs), vibration amplitudes and incoming wind speeds. The flutter derivatives related to torsional degree of freedom (DOF) are identified and compared. The nonlinear and unsteady characteristics of self-excited forces (SEFs) in terms of the frequency components and phase lag between the force and motion are quantitatively examined. The wind-induced energy maps of the quasi-flat plate at various initial AoAs are analyzed by introducing the aerodynamic work done by the self-excited lifting moment. A polynomial model is proposed to describe the nonlinear characteristics of the SEFs. It is validated that the flutter derivatives related to the torsional DOF are almost a single-valued function with respect to the reduced frequency, even at large vibration amplitudes. At large initial AoAs and oscillation amplitudes, the high-order frequency components of SEFs are significant, and the nonlinearity of the self-excited lifting moment is stronger than that of the self-excited lift force for torsional motion. This provides a reasonable explanation for the significant amplitude dependence of the flutter derivatives related to the lifting moment. The proposed polynomial nonlinear SEF model can achieve satisfactory accuracy in reproducing the SEFs in both time and frequency domains.

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Availability of data and material

Some data, models that support the findings of this study are available from the corresponding author upon reasonable request.

Code availability

Some codes that support the findings of this study are available from the corresponding author upon reasonable request.

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Acknowledgements

The authors gratefully acknowledge the support of National Natural Science Foundation of China (52078383, 52008314, 51978527) and Independent Subject of State Key Lab of Disaster Reduction in Civil Engineering (SLDRCE19-B-11).

Funding

National Natural Science Foundation of China (52078383, 52008314, 51978527) and Independent Subject of State Key Lab of Disaster Reduction in Civil Engineering (SLDRCE19-B-11).

Author information

Authors and Affiliations

  1. State Key Lab of Disaster Reduction in Civil Engineering, Tongji University, Shanghai, 200092, China

    Shengyuan Liu, Lin Zhao, Genshen Fang & Yaojun Ge

  2. Key Laboratory of Transport Industry of Wind Resistant Technology for Bridge Structures, Tongji University, Shanghai, 200092, China

    Lin Zhao & Yaojun Ge

  3. State Key Laboratory of Mountain Bridge and Tunnel Engineering, Chongqing Jiaotong University, Chongqing, 400074, China

    Lin Zhao

  4. School of Urban Construction, Wuhan University of Science and Technology, Wuhan, 430081, China

    Chuanxin Hu

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  1. Shengyuan Liu
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Contributions

Shengyuan Liu done physical test, data curation, and writing—original draft. Lin Zhao performed conceptualization and methodology. Genshen Fang investigated the study. Chuanxin Hu was involved in physical test and investigation. Yaojun Ge supervised the study.

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Correspondence to Lin Zhao.

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Appendix A

Appendix A

See Tables 3, 4, 5, 6.

Table 3 Comparison of various aerodynamic models
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Table 4 Fitting parameters of the nonlinear model for typical cases (AoA = 0°)
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Table 5 Fitting parameters of the nonlinear model for typical cases (AoA = 3°)
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Table 6 Fitting parameters of the nonlinear model for typical cases (AoA = 9°)
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Liu, S., Zhao, L., Fang, G. et al. Nonlinear aerodynamic characteristics and modeling of a quasi-flat plate at torsional vibration: effects of angle of attack and vibration amplitude. Nonlinear Dyn 107, 2027–2051 (2022). https://doi.org/10.1007/s11071-021-07082-y

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  • DOI: https://doi.org/10.1007/s11071-021-07082-y

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