The experimental and analytical investigations of buckling behavior of [0/$\pm$Θ/90]s composite laminated cylindrical panels for various fiber angles and panel widths were presented. Experiments were conducted for panels with fiber angles, Θ=0,30,45,60,90 (d/L=1.047) and panel widths, d/L=0.262,0.524,1.047(Θ=60). Experimental buckling and postbuckling load was obtained from load versus end-shortening curve. In addition, buckling mode shape was observed by the grid generated on specimen. Load recovery was studied for several panels as well. Analysis was performed by the nonlinear finite element program JSHELL which was developed for the buckling analysis of composite laminated cylindrical panel. Experimental results of buckling loads were in good agreement with finite element results which were implemented by initial imperfection of the composite panel.