The unsteady and dynamic stall aerodynamic behavior of airfoil at low Mach number was investigated

and the modified Leishman-Beddoes (L-B) model was modeled from the viewpoint of the convection of the flow on the airfoil surface.Based on the modified L-B model

the flutter analysis model of a two-dimensional wing with aerodynamic and structural nonlinearity at low Mach number was presented.The modification to L-B is effective by comparing with experimental airfoil airload results

and the wing flutter experimental results also verify the analysis model of the two-dimensional wing aeroelastic system.Results demonstrates that the stall flutter of airfoil aeroelastic system is closely related to the initial pitch angle and the inflow velocity

and the quasi-periodical oscillation motion of the two-dimensional wing aeroelastic system mainly caused by the coupled cubic nonlinear stiffness in pitch and plunge.