Abstract: An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example an active flow control system includes a plenum, a plurality of nozzles fluidly coupled to the plenum, configured to eject high pressure air across a control surface, a compressor to supply pressurized air to the plenum, an electric motor to drive the compressor, and a control system to determine an amount of power input to the electric motor, determine a current speed of the electric motor, and determine a fault has occurred in the active flow control system based on the current speed of the electric motor.

Abstract: An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.