In this study, flutter and aeroelastic responses of rotor blade with bending-torsional coupling have been investigated for composite thin-walled structure called ‘integration line equation closed-section’. The aerodynamic models adopted here are a simple aerodynamic model used for classical flutter and a reduced nonlinear aerodynamic model suitable for constant pitch motion for stall flutter, which are used in order to investigate quickly parameters that influence the behavior of the aeroelastic system. The coupled partial differential structural equation are solved by discretization, with time responses investigated.