This paper presents a comprehensive numerical/experimental comparison to analyze both the scale and stacking e ects of laminated composite containing geometric singularities. The numerical simulation was carried out with the new mesomodel-based approach presented in the previous work. Numerical results demonstrate the robustness of this approach, showing a very good correlation with experimental data for both typical singular cases in the aeronautic indus try : holed and V-notched laminates. The complex subcritical damage process is accurately reproduced by the new split approach modeling, including the sud den appearance of local instabilities and nal rupture for all dimensional e ects in the plane, stacking sequences (including e ects due to an increased number of plies), and ply thickness. The physical nature of these e ects has been identi ed. They inevitably inuence the propagation of splits, which is the origin of stress relaxation around singularities and the orientation of delamination along adja cent interfaces, thus signi cantly impacting the complex evolution of subcritical damage.