There is nothing as the absolute best composite layup. Layup design might depend on the kind of loads applied. An optimum design can be achieved by going through an iterative process. You might want to look at techniques such as Ant colony optimization. For a start, you could do with the classical quasi isotropic layup

Some factors should be considered. Optimizaiton based on numerical simulations can be done to find the optimum constituts, the number of layers in each orientation and the stacking sequence. 

There is not best laminate layup for such a problem. You should take into account several factors. To mention few: loads applied (uni-axial compression, bi-axial compression, shear, top/bottom pressure and any combination of those);plate's aspect ratio (a/b widht/lenght); number and thickness of layers; allowable orientations; stacking sequence. The design space is generally wide and you might want to use optimization to maximize the buckling load. To this end, there are countless papers dealing with this kind of optimization problem for composites (combinatorial optimization or constrained combiantorail optmization when also blending of laminates is concerned) using different kind of heuristics. Preliminary work were performed using the branch and bound algorithm. You might want to refer to the works of professor R. T. Haftka who firstly investigate the use of GA for the optimization of composite panles' layup. Furthermore, as a consequence of the introduction of tow steered composite, the design space is even wider. In this latter case you might want to refer to the works of Prof. Z. Gurdal or Prof. P. Weaver.