Analysis by use of finite element method and experiments are performed in order to study the compressive buckling strengths of CFRP laminated panels. An inconsistent assumed stress hybrid model, which can satisfy even mechanical boundary conditions, is derived as an analysis tool. The numerical results show that the inconsistent assumed stress hybrid model is very useful to analyze the states of deformation and stress accurately in geometrical nonlinear problems. The snap through phenomena observed in experiments can be explained very well by numerical results as stability problems. From the results of experiments about four kinds of CFRP laminated panels containing 0° plies, 90°Plies and ±45° plies, it is observed that, different from the results of Part 1, the fracture of laminated panels is caused by the delamination near the free edge in inplane condition. Therefore, numerical solutions of the free edge effects on the interlaminar stresses are obtained using a finite element procedure. The failure stresses of uniderectional CFRP, whose resin is 3130 epoxy, are estimated from experimental results and numerical results in the present paper, taking experimental results of Part 1 also into consideration. It can be concluded that a 0°+90°laminated panel among the test specimens has the highest compressive buckling strength.
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