Low speed flutter and limit cycle oscillations of a two-degree-of-freedom flat plate in a wind tunnel |
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| Affiliation: | 1. LadHyX, CNRS-Ecole Polytechnique, F-91128 Palaiseau, France;2. Département ISME, CNAM, Paris, France;1. State Key Laboratory of Disaster Reduction in Civil Engineering, Tongji University, Shanghai 200092, China;2. Department of Bridge Engineering, Tongji University, Shanghai 200092, China;3. Key Laboratory of Wind Resistance Technology of Bridges of Ministry of Transport, Tongji University, Shanghai 200092, China;1. São Carlos School of Engineering, University of São Paulo (EESC/USP), São Carlos, SP, Brazil;2. Aeronautics Institute of Technology (ITA), São José dos Campos, SP, Brazil;1. Highway College, Chang''an University, Xi''an, Shaanxi 710064, China;2. State Key Laboratory of Disaster Reduction in Civil Engineering, Tongji University, Shanghai 200092, China;3. Department of Bridge Engineering, Tongji University, Shanghai 200092, China;4. Key Laboratory of Wind Resistance Technology of Bridges of Ministry of Transport, Tongji University, Shanghai 200092, China |
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| Abstract: | This paper explores the dynamical response of a two-degree-of-freedom flat plate undergoing classical coupled-mode flutter in a wind tunnel. Tests are performed at low Reynolds number (Re~2.5×104), using an aeroelastic set-up that enables high amplitude pitch–plunge motion. Starting from rest and increasing the flow velocity, an unstable behaviour is first observed at the merging of frequencies: after a transient growth period the system enters a low amplitude limit-cycle oscillation regime with slowly varying amplitude. For higher velocity the system transitions to higher-amplitude and stable limit cycle oscillations (LCO) with amplitude increasing with the flow velocity. Decreasing the velocity from this upper LCO branch the system remains in stable self-sustained oscillations down to 85% of the critical velocity. Starting from rest, the system can also move toward a stable LCO regime if a significant perturbation is imposed. Those results show that both the flutter boundary and post-critical behaviour are affected by nonlinear mechanisms. They also suggest that nonlinear aerodynamic effects play a significant role. |
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| Keywords: | Low speed flutter Limit cycle oscillation Nonlinear aeroelasticity Wind tunnel Flat plate |
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