For their weight reduction, thin web panels are often used in airspace industry. In this study, a basic fuselage section is represented by a stiffened panel composed by skin, frame, stiffeners and attachments, as conceived by Arakaki and Faria [1]. In this panel design, the structure withholds large loads after the buckling of the web. This study presents a comparison between thick and thin ply composite laminates behavior under shear buckling loads. The two concepts were modeled using the commercial finite element software Abaqus®. Buckling and post-buckling nonlinear behavior for both thick ply and thin ply laminates was analyzed and results were compared.