An active laminar flow control arrangement may comprise a modular arrangement comprising a plurality of frames and cover panels coupled to an outer skin having a plurality of hat stiffeners and stringers. A first cover panel may be coupled between a first frame and a first hat stiffener. A second cover panel may be coupled between a second frame and a second hat stiffener. A third cover panel may be coupled between the first cover panel and the second cover panel. The cover panels may enclose associated plenums whereby a flow of air is pumped into the arrangement for maintaining a laminar flow across an aerodynamic surface of the outer skin.

A flow guide body for an aircraft includes a main body having an outer aerodynamic surface having a plurality of outlet openings, and flow control devices, each having an inlet, an interaction chamber, a first outlet and a second outlet. A first control inlet is connected to the interaction chamber at the first side of the chamber axis. The outlets are each connected to outlet openings in the aerodynamic surface. Each outlet has a control outlet. A second flow control device is arranged such that one outlet is connected with the inlet of the first flow control device. One of the control outlets of the first flow control device is connected to the first control inlet of the first flow control device, and the other of the control outlets of the first flow control device is connected to the first control inlet of the second flow control device.

A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil, a flow separation control device, and an injection system. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body. The injection system includes an inlet tube, a pump in gaseous communication with the inlet tube, and a flow regulator in gaseous communication with the pump and the plurality of capillary tube.

An aerodynamic body for use on an aircraft including at least a first perforated surface portion (25) and an ice-protection system (31). The first perforated surface portion (25) has perforations. The ice-protection system (31) includes an actuatable element (33) and the actuatable element (33) is movable or deformable between a first position and a second position. In the first position, the actuatable element (33) is thermally coupled to the first perforated surface portion (25) and configured to prevent an inflow or outflow between a boundary layer of an outer aerodynamic airflow and the aerodynamic body through at least one of the perforations. In the second position, the actuatable element (33) is distanced from the first perforated surface portion (25) and configured to allow an inflow from a boundary layer of an outer aerodynamic airflow through at least one of the perforations into the aerodynamic body.

An aircraft structure, for example a wing, including a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing). A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor is also described.

A leading edge structure (13) for a flow control system of an aircraft (1), including a double-walled leading edge panel having an inner wall element (45) and an outer wall element (47). Between the inner and outer wall elements (45, 47) are elongate stiffeners (49) spaced apart from one another. And, between adjacent stiffeners (49) are a hollow chamber (51). The outer wall element (47) includes micro pores (53). The inner wall element (45) includes passages (55) forming a fluid connection between the hollow chambers (51) and a vacuum system (15). An ice protection system in the stiffeners (49) includes hot air ducts (57) configured for connection to a hot air system (17), and the stiffeners (49) include hot air openings (59) forming a fluid connection between the hot air ducts (57) and the hollow chambers (51).

An aircraft includes an active drag control system such as a Laminar Flow Control (LFC) system having a port LFC apparatus and a starboard LFC apparatus. The aircraft has a control system to test how efficiently the LFC system is working by differentially operating the port LFC apparatus and the starboard LFC apparatus, for example by deactivating either LFC apparatus, and measuring the effect on the direction of flight of the aircraft. The control system also can change the direction of the aircraft, and trim the aircraft, by differentially operating the port LFC apparatus and the starboard LFC apparatus.

An assembly is provided for active laminar flow control. This assembly includes a panel, which panel includes an outer skin, an inner skin and a plurality of plenums between the outer skin and the inner skin. Each of the plurality of plenums is fluidly coupled with a respective array of perforations through the outer skin. The panel is constructed from fiber-reinforced composite material.

A system for suction of the boundary layer of a wing and protection against icing of this wing includes a wall including micro-perforations and delimiting a leading edge extended by a pressure-side wall and by a suction-side wall. The system also includes a perforated tube running along the leading edge, an exhaust duction for sucking air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and via the perforations of the tube, and a supply duct for blowing hot air into this perforated tube during a phase of protection against icing, this hot air being discharged successively via the perforations of the tube and via the micro-perforations of the wall.

An active laminar flow control arrangement may comprise an outer skin having an inner surface, an outer surface, and a perforated area, and a panel coupled to the inner surface. The panel may comprise a longitudinal wall, a sidewall extending from the longitudinal wall, a ridge intersecting the sidewall, a cavity disposed in the panel and at least partially defined by the sidewall and the longitudinal wall, and a division wall disposed in the cavity and extending from the longitudinal wall, wherein the division wall divides the cavity into a first plenum and a second plenum. The longitudinal wall, the sidewall, the ridge, and the division wall may comprise a single, monolithic piece.