Composite Materials are materials with two or more distinct macroscopic phases which together result in a structure with properties which are not achievable with any of the individual constituents. Fibre-reinforced composites, specifically those based on fibre reinforced polymers, combine the best of the materials inheriting high stiffness and strength. Laminates are composites in which different layers of materials give them a specific character to perform a particular function. Composite laminates have been used increasingly in a variety of industrial areas due to their high stiffness and strength-to-weight ratios, long fatigue life, resistance to electrochemical corrosion and other superior material properties of composites. Laminated composite plate structures find numerous applications in aerospace, military and automotive industries. An accurate understanding of their structural behaviour is necessary, such as deflections and stresses for tailoring strong, reliable multi-layered structures. The objective of this research is to model a composite plate using Finite Element Method for further parametric study. A comparison of solutions obtained from Finite Element Method is made with Classical results. The finite element model subjected to uniformly distributed load is used to investigate the effect of laminate configuration on the deflection of composite plates. To get a better picture, failure in composite plate is analysed using Tsai-Hill Criteria. The numerical results from stress and deflection criteria show that design of composites is usually governed by deflection rather than strength