A highly flexible continuous wing model has been built to study either coupled-mode flutter or stall flutter in a wind tunnel. This model utilizes a composite cantilever beam arrangement that provides the bending and torsional stiffness, cladding segments representing a NACA0012 geometry and an added slender body allowing for the control of the ratio of the torsional and flapwise natural frequencies . In the present paper we will focus on a series of stall flutter experiments, tracking the motion of the tip of the wing to capture post-critical oscillation modes. Following the work of Tang and Dowel, the associated nonlinear post-critical behavior, due to both dynamic stall and static deflection, will also be studied using a continuous model including the ONERA dynamic stall formulation for the unsteady aerodynamics.