A device for reducing aerodynamic disturbances in the wake of an aerodynamic profile. The device comprises a first air ejection nozzle arranged on the top side of the profile and a second air ejection nozzle arranged on the underside of the profile. A first blowing chamber is fluidically connected to the first nozzle and a second blowing chamber is fluidically connected to the second nozzle. Air supply means are configured to vary the distribution of air between said first blowing chamber and second blowing chamber. The distribution of the blown air can thus be adapted depending on the situation in which the profile is used, for example depending on the flight phase of an aircraft equipped with such a profile. Also, an aerodynamic profile, a pylon supporting a propulsion assembly for an aircraft comprising such an aerodynamic profile, and an aircraft.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.

A flow body and method for taking in and/or blowing out fluid through a plurality of openings in a flow surface section of a flow body is disclosed. In some aspects, the flow body includes a flow surface section that extends in a flow body wingspan direction and a flow body chord direction and with a plurality of fluid lines that lead into the flow surface section and respectively form an opening therein. In some aspects, the method includes taking in and/or blowing out fluid through at least one fluid line that leads into a flow surface section of a flow body and respectively forms an opening therein.

For dual management of anti-icing and boundary-layer suction, a system for an aerofoil of an aircraft, including: a channel having a double function of anti-icing and boundary-layer suction; a double-function main pipe to which a device for monitoring the boundary-layer suction and a device for monitoring anti-icing are connected; an anti-icing air-intake pipe connecting the main pipe and the channel; a non-return valve enabling anti-icing air to go from the main pipe to the pipe; at least one suction-air collection pipe connecting the channel and the main pipe; and a non-return valve enabling suction air to pass from the pipe toward the main pipe.

A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.

An aircraft, an aircraft wing structure and a method are provided in order to address lift and drag, such as by increasing lift and reducing drag. In the context of an aircraft wing structure, the aircraft wing structure includes a wing extending outboard from a fuselage of an aircraft. The wing also extends from a leading edge to a trailing edge. The aircraft wing structure also includes one or more actuators carried by the wing and causing fluid to be directed through one or more respective orifices defined by the wing so as to alter flow over a lower surface of the wing. The one or more orifices that are defined by the wing are closer to the leading edge than to the trailing edge. Thus, the fluid introduced through the one or more orifices may increase lift and reduce drag of the associated aircraft.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.