Abstract: In this study, gradual demand for curved, stiffened panels composite emerged from Carbon Fiber Reinforced Plastics (CFRP) these are structures that are frequently used in aerospace engineering. Up to 50% of the primary structure of the Boeing 787 is made up of woven graphite-epoxy. This research emphasizes the buckling analysis of stiffened composite panels using the nonlinear, finite element modeling. The stiffened panel is assumed to be subjected to a uniform axial compression load of 10 kN. For the nonlinear buckling analysis, a stiffened composite panel is made of Carbon Fibre Composite (CFC) in epoxy, Kevlar in epoxy and E-Glass (EG) in epoxy. Due to the fact that there are numerous stiffened composite panels materials this study, therefore uses a numerical approach to present the study and results of the nonlinear static buckling analysis of i-stiffened on different composite panels. This research also presented the effect of the different ply orientations using Abaqus Finite Element Analysis (FEA).