Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).

Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).

Abstract: An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.

Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Abstract: A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.

Abstract: A method for suctioning the boundary layer at the surface (1) of an aircraft having an air-conditioning system (4), at whose flow-critical points of the surface multiple suction openings (2) are provided, the air quantity suctioned via these being discharged to the atmosphere again via at least one outlet (7) placed in a way favorable for flow, the air quantity suctioned from the surface (1) being fed to the air-conditioning system (4) of the aircraft, via whose outlet (7) the air quantity suctioned is discharged to the atmosphere together with the exhaust air of the air-conditioning system (4), to reduce flow losses.

Abstract: A method for suctioning the boundary layer at the surface (1) of an aircraft having an air-conditioning system (4), at whose flow-critical points of the surface multiple suction openings (2) are provided, the air quantity suctioned via these being discharged to the atmosphere again via at least one outlet (7) placed in a way favorable for flow, the air quantity suctioned from the surface (1) being fed to the air-conditioning system (4) of the aircraft, via whose outlet (7) the air quantity suctioned is discharged to the atmosphere together with the exhaust air of the air-conditioning system (4), to reduce flow losses.

Abstract: A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.