The investigation of a control strategy of the supersonic air inlet buzz phenomenon has been performed using Large Eddy Simulations (LES). This work aims at assessing how a passive air bleed device can contribute to mitigate and stabilize this highly undesired flow pattern. Therefore, a supersonic air inlet geometry equipped with a bleed system is examined in which the buzz phenomenon is provoked by partially blocking the duct exit area. LES are performed for one unthrottled reference case and one deeply subcritical case experiencing the big buzz phenomenon. The results are compared to a previous numerical study of the same geometry without a bleed system and experimental data obtained in reference wind tunnel tests.