An actuator assembly is capable of manipulating a fluid flowing around a flow body, the fluid being received or able to be received in a volume of at least one cavity arranged in the flow body, and the fluid passing through at least one opening in the at least one cavity during manipulation of the fluid. In this process, the volume of the at least one cavity can be changed by moving a wall portion delimiting or defining the cavity. The actuator assembly has a drive unit with at least one actuator, which executes a periodic movement over time when actuated, causing a translational movement of the wall portion delimiting or defining the cavity and the wall portion being shaped in terms the topology thereof in such a way that it is adapted to the shape of the at least one cavity with the at least one opening thereof.

An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough.

An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening.

A leading edge structure for an aerofoil is disclosed. The leading edge structure includes a skin configured to form an external aerodynamic surface of the aerofoil. The skin includes a plurality of first regions interleaved with a plurality of second regions. Each first region includes a plurality of holes extending through the skin, and each second region includes an electrical heating system configured to increase the temperature of the skin.

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 method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of operating aircraft for flight in close formation includes establishing a communication link between a first aircraft and a second aircraft, assigning to at least one of the first aircraft or the second aircraft, via the communication link, initial positions relative to one another in the close formation, providing flight control input for aligning the first and second aircraft in their respective initial positions, tracking, by at least one aircraft in the close formation, at least one vortex-generated by at least one other aircraft in the close formation, and based on the tracking, providing flight control input to adjust a relative position between the first aircraft and the second aircraft.

An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.

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.