Abstract: An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described.

Abstract: 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.

Abstract: An aircraft and system for minimizing the influence of unsteady flow states, wherein the wing has a respective main wing and at least one control flap adjustably arranged relative thereto, an adjusting drive for activating the at least one control flap, and a sensor arrangement for acquiring the setting position of the control flap. The system exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over the surface segment, a detection device for detecting unsteady flow states acting on the aircraft, and an actuating function connected with the flow-influencing devices to influence the flow in the different segments of a wing, designed so that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap acquired by the sensor arrangement, actuates the flow-influencing devices so as to minimize the influence of unsteady flow states on the aircraft.

Abstract: The invention relates to fluid actuator for influencing the flow along a flow surface through ejection of a fluid. By means of a like fluid actuator, a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber which is supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which a respective different pressure may be applied. Depending on the pressure difference at the control openings, the flow in the interaction chamber is distributed to the individual outlet openings.

Abstract: An aircraft with airfoils having a main wing and at least one control flap arranged such to be adjusted relative to the main wing, as well as a high-lift system with at least one regulating flap for adjusting the lift of the airfoils to adjust the state of lift of the aircraft, featuring flow control devices for influencing the fluid flowing over the surface segment; an activating unit; and a lift state specification device connected to the activating unit for adjusting the state of lift of the aircraft.

Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.

Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.

Abstract: A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system.

Abstract: A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described.

Abstract: A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.

Abstract: The present invention relates to a coated object comprising at least (a) a metal layer, (b) a coupling layer, (c) an inner polymer layer, and (d) a substrate surface, wherein the coupling layer (b) is arranged between layers (a) and (c) and connects said layers, the polymer layer (c) being arranged on the substrate surface (d) and the sum of the diameters of layers (a) and (b) being between 5 nm and 500 nm. The invention also relates to methods and devices for producing the object.

Abstract: An aircraft with aerofoils including a main wing and a control flap that includes an adjustment flap. The aircraft includes an actuator for the control flap, as well as a sensor device for acquiring the position of the control flap, an arrangement of flow-influencing devices for influencing the fluid that flows over a segment of the main wing, and flow-state sensor devices for measuring the flow state. The aircraft includes a flight control device connected to the sensor device for acquiring the position of the control flap and to the flow-state sensor devices, and connected to the actuator and flow-influencing devices for transmitting actuating commands, and a flight-state sensor device connected to the flight control device for transmitting flight states. The flight control device includes a function that selects the flow-influencing devices that are operated for optimizing local lift coefficients on the aerofoil, depending on the flight state.

Abstract: A fluid actuator for influencing the flow along a flow surface by ejecting a fluid flowing through the fluid actuator is described. The fluid actuator has at least two outlet lines with outlet openings at the respective ends thereof, and a feed line connected to the outlet lines for feeding fluid at a supply pressure, a flow direction diverting device into which the feed line opens and out of which the outlet lines open, and an adjusting device coupled to the flow direction diverting device to control the latter. The adjusting device is configured so the fluid is conducted successively in a cyclic sequence into each of the outlet lines. A discharge device for discharging a fluid out of a flow body, and a flow body having a multiplicity of discharge openings and a discharge device of said type are also described.

Abstract: A high-lift system with a main wing and adjustable flaps as well as guiding devices for holding the adjustable flaps and adjustment devices for adjusting the adjustable flaps, wherein the respective guiding device and/or adjustment device at least in part include/includes a fairing, including a flow influencing device for influencing the flow around the high-lift system, with at least one inlet line with at least one inlet that is situated on or below the bottom of the high-lift system, wherein, furthermore, at least one outlet line for air is provided that includes a fluid-communicating connection to the inlet line and includes at least one outlet situated at the top in the region of at least one adjustable flap of the high-lift system.

Abstract: An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.

Abstract: The invention relates to fluid actuator for influencing the flow along a flow surface through ejection of a fluid. By means of a like fluid actuator, a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber which is supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which a respective different pressure may be applied. Depending on the pressure difference at the control openings, the flow in the interaction chamber is distributed to the individual outlet openings.

Abstract: A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system.

Abstract: An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.

Abstract: The invention pertains to a flow body with 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, as well as to a method for 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.