The present study is focused on dynamic stall behavior of a pitching airfoil. The deep stall regime is in particular considered. The final goal is the development of a model able to deal with different types of dynamic stall, including those characterized by vortex shedding. The first steps towards this goal are shown herein. The proposed model is appraised against an extensive data set of experimental (!, #$) curves for a NACA 0012, under steady and unsteady conditions. The results of an existing widely used model are also shown for comparison. The proposed model is able to reproduce fairly well not only the classic curves of deep dynamic stall, but also the curves characterized by lift oscillations at high angle of attack, due to the shedding of multiple vortexes.