The work introduces a methodology to simulate fatigue crack opening and closing during crack propagation, using a commercial finite element code. This code is used to determine the crack opening and closure stress intensity factors. The Newman model is used as a baseline to develop the methodology. The nodes are released at the minimum load, during the crack propagation process. Four kinds of specimens SE-(T) ( Single Edge Tension), SE-(B) ( Single Edge Bending), M-(T) ( Middle Tension) of the an aluminum alloy Al-2024-T351 and a dual phase steel (ferrite + martensite) were evaluated. A compact tension specimen C-(T) of a dual phase steel was evaluated. The aluminum alloy specimens, SE -(T), SE-(B) and M-(T), were evaluated under constant amplitude loading with load ratios R = 0 and R = 0.5. The results of these analyses are compared with the results of FASTRAN, principal numerical code used to simulate crack opening and closing plasticity induced by, normalizing the opening stress intensity factor. The numerical results from a C-(T) specimen, under constant amplitude loading and a load ratio R = 0.1, were compared with results from a test performed in the laboratory. The numerical and experimental closure stress intensity factors are normalized with the maximum stress intensity factor. Crack closure simulations are currently used in the aircraft industry. They are now being incorporated in same automotive and other ground vehicle fatigue analysis procedures.