Aeronautical compressor fans, currently, operate with minimal blade–casing clearance. Therefore, this makes the occurrence of rub events very likely. Under specific circumstances, the blade undergoes excessive amplification of contact-induced oscillations, called hereafter divergence, which can be critical for the structural integrity of the engine. This article proposes an investigation of the mechanisms responsible for the blade divergence. Experiments are conducted on a fully instrumented laboratory setup, consisting of a single flat blade being moved toward a rotating cylinder to initiate interactions, while monitoring the vibrations and the evolution of wear on the abradable coating. Two synchronization mechanisms have been identified as facilitating the divergence: (i) the inherent setup synchronization between the vibration modes related to the horizontal and vertical motion of the blade; (ii) the preferential blade–coating interactions in the vicinity of periodically distributed irregularities of the abradable coating, which act as a source of excitation of the vibrations.