Carbon fiber reinforced polymer matrix composites are increasingly used in the aeronautical sector due to their high strength-to-weight ratio and the possibility of tailoring the mechanical properties of the laminate. Among the main damage mechanisms, delamination represents a critical phenomenon that can significantly compromise the structural integrity of components. The present thesis work, carried out during an internship at ISAE-Supaero in collaboration with Airbus Atlantic and Institut Clément Ader, is aimed at the experimental and numerical characterization of the main mechanical properties of a thermosetting polymer composite reinforced with carbon fibers, with particular attention to interlaminar fracture toughness in Mode I and Mode II.