Abstract This paper presents the application of a composite damage model to predict the edge impact and compression after edge impact (CAEI) response of CFRP laminates. First, a mesh sensitivity analysis is performed showing that the mesh needs to be sufficiently fine to accurately capture the permanent out-of-plane deformation at the impact location, which acts as the initiation site that induces laminate compressive failure at early stages in the deformation process. The simulations of edge impact are correlated with the impactor load-displacement data, impact area, and visible crack length data available in the literature. The experimentally measured stress-displacement curves are used to validate the residual strength predictions. The shape and size of the damage inflicted by the edge impact events on different laminates is well predicted, as well as the residual strength of the laminates subjected to CAEI. The model proposed can accurately capture stacking sequence effects, predicting significant changes in the shape of the damaged area when only the stacking sequence changes, in agreement with the experimental observations.