In this paper buckling analysis of rectangular composite laminates with a central square hole is investigated. Using the first order shear deformation theory, the buckling loads of rectangular laminated plates under the inplane loads are found for various hole sizes. The four-mode finite element method is used to obtain critical loads. The critical loads of symmetric angle-ply, antisymmetric cross-ply or angle-ply laminates are found for constant or various thicknesses, simple or clamped boundary conditions, various modules ratios, simple or biaxial loading versus hole sizes. Some results are compared with those of given references.