Finite element (FE) method is presented for the analysis of thin rectangular laminated composite plates under the biaxial action of in – plane compressive loading. The analysis uses the classical laminated plate theory (CLPT) which does not account for shear deformations. In this theory it is assumed that the laminate is in a state of plane stress, the individual lamina is linearly elastic, and there is perfect bonding between layers. The classical laminated plate theory (CLPT), which is an extension of the classical plate theory (CPT) assumes that normal to the mid – surface before deformation remains straight and normal to the mid – surface after deformation. Therefore, this theory is only adequate for buckling analysis of thin laminates. A Fortran program has been compiled. The convergence and accuracy of the FE solutions for biaxial buckling of thin laminated rectangular plates are established by comparison with various theoretical and experimental solutions. The good agreement of comparisons demonstrates the reliability of finite element methods used.