Abstract Post-buckling behavior of imperfect, laminated composite cylindrical panels subjected to axial compressive load has been investigated by means of an equilibrium path approach which uses an arc-length method. Influence of the eigen imperfection shapes and its magnitude on the post-buckling behavior of the cylindrical panel with different curvature (R/t) ratios is briefly discussed for different unidirectional lay-up sequences of interest with all the sides considered as simply supported boundary configuration. Influence of curvature ratio on the post buckling behavior of cylindrical panel is briefly discussed where the thickness of the shell is considered as constant throughout this study while the radius (or curvature) 0f the panel varies according to the specified (R/t) ratio of the panel.