Boundary layer separation from flaps is responsible for large performance losses during take-off and landing phases of an aeroplane flight, including loss of lift and drag increase. On modern aircraft, a slot located between the wing and the flap enables to increase lift at low speed. To manage this slot, flap deployment systems are very complex and heavy. It would be of interest to simplify them and replace the slot by separation control devices whose parameters such as injected momentum and forcing frequency can be adapted in closed-loop and real-time. The present study aims at developing algorithms to control those parameters in order to fulfill two objectives, the first one is to maintain the flow attached when the flap is progressively deflected, the second one is to provide maximum lift despite of massive separation at high flap deflection angles, when the momentum injected into the flow is no more sufficient to reach full reattachment. In the literature, the first objective is related to the framework of flow separation control, and the second one to the framework of separated-flow control
