In this contribution, some preliminary results are presented, relevant to an experimental campaign on samples of GLARE, a fiber metal laminate for aviation applications, subjected to low velocity impact according to ASTM D7136. Rectangular panels have been produced, corresponding to GLARE 5 and 6 configurations, implementing surface treatments on the metal surfaces to improve inter-laminar adhesion. Experimental data in terms of reaction force versus time and post mortem visual inspection have been interpreted at the light of advanced numerical simulations, developed in Abaqus® environment by assuming a priori known the mechanical parameters of the different layers. Finite element analyses carried out in explicit dynamics have exhibited a satisfactory agreement with the experimental response, although premature delamination in a few samples caused a sudden decrease of the reaction force.