The present invention relates to a forebody flow control system and more
particularly to aircraft or missile flow control system for enhanced
maneuverability and stabilization at high angles of attack. The present
invention further relates to a method of operating the flow control
system.In one embodiment, the present invention includes a missile or
aircraft comprising an afterbody and a forebody; at least one deployable
flow effector on the missile or aircraft forebody; at least one sensors
each having a signal, the at least one sensor being positioned to detect
flow separation on the missile or aircraft forebody; and a closed loop
control system; wherein the closed loop control system is used for
activating and deactivating the at least one deployable flow effector
based on at least in part the signal of the at least one sensor.