 The stability of aircraft components made from composite materials is highly dependent on the presence of delaminations. Delaminations can cause rapid reduction in structural stiffness, leading to catastrophic failure if not detected early enough. This paper presents a sensitivity analysis of a typical aerospace reinforced panel with a circular delamination representing an impact damage event. Various configurations were analyzed, including different radii and positions along the thickness of the delamination. Additionally, some geometric parameters of the panel were modified to assess how the buckling load and the propagation of interlaminar damage evolved. This article was authored by Annie Yellow Riccio, Rosana Castaldo, Conchetta Palumbo, and others.