This paper demonstrates the analyses of the interlaminar shear stress of laminated composite plates subjected to transversely impact. For this purpose, a plate finite element model based on the higher order shear deformation plate theory in conjunction with static contact laws is developed. Test materials were CFRP with cross-ply laminate $[O_4/{ heta}_4]_S$, $[90_4/{ heta}_4]_S$ stacking sequences and angle-ply laminate $[{ heta}_4/-{ heta}_4]_S$, $[{ heta}_4/-{ heta}_4]_S$ stacking deguences with $2^t{ imes}40^w{ imes}100^l(mm)$ dimension. As a result, stacking seguence and fiber orientation were found to have a significant effect on the interlaminar stresses in composite laminates.