Flutter of a two-dimensional wing with asymmetry at low Mach numbers

Abstract

A two-dimensional wing aeroelastic model with a modified Leishman–Beddoes model in state-space form is performed to investigate the flutter behavior at low Mach numbers. The two-dimensional wing aeroelastic system employs highly aerodynamic non-linear features. The modifications to the Leishman–Beddoes model are validated by comparing with the experimental results of airfoil airloads at low Mach numbers, and the wing flutter experimental results also verify the model of the two-dimensional wing aeroelastic system. Results demonstrate that a fold bifurcation, which is related to the high-amplitude limit cycle oscillation, stems from the phenomenon of dynamic stall and the emergence of the period-2 limit cycle oscillation is due to the asymmetry of the aeroelastic system.

Keywords

Aeroelastic system flutter dynamic stall low Mach numbers asymmetry

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