Fiber-reinforced composites are receiving increased attention due to their superior mechanical properties compared to traditional materials. Since composites are made of multiple components, their failure mechanisms are complex and involve competing failure modes. This necessitates the need for sophisticated modeling and simulation to analyze failure as experimental studies are expensive and time-consuming. The current paper presents the experimental and numerical modeling of compression-after-impact (CAI) experiments of T650-5320 composite laminates. Experimental study is conducted at the National Institute for Aviation Research (NIAR) laboratories in accordance with ASTM D7136 for impact and ASTM D7137 for CAI experiments. The numerical finite element modeling is studied using SIMULIA Abaqus software. Shell elements are used to model the composite layup to provide a global solution. This is followed by a detailed simulation involving solid elements. Results are compared with the experiments to validate the two approaches. Shell modeling is demonstrated as a simpler approach to model CAI to get coupon-level results. Solid modeling is proposed to get detailed results to determine damage levels within each ply.