The postbuckling behavior of laminated composite eccentric stiffened plates subjected to uniform in-plane loading using finite element method is discussed in this paper. The plate and stiffener are modeled using an eight-noded degenerated shell element and a three-noded degenerated curved beam element with isoparametric formulation and C° continuity (FSDT) of the primary variables. Linear buckling analysis is done by solving the eigen-value equation. The postbuckling analysis is carried out by solving the non-linear equilibrium equation using Crisfield arc-length method. This study considers the effect of symmetric and antisymmetric lamination schemes, aspect ratio, and number of stiffeners on the postbuckling behavior of composite plates, and the results are discussed.