Abstract: A flow body for a vehicle includes at least one planar skin section with an outer side, an inner side and at least one opening that penetrates the skin section, as well as at least one active flow control device that is designed for moving an air volume. The at least one active flow control device includes an air discharge section that is fluidically connected to the at least one opening, wherein the air discharge section and the at least one planar skin section are manufactured by a layer manufacturing process in the form an integral component that is free of joints, and wherein the air discharge section at least partially supports the skin section in a load-bearing fashion.

Abstract: The invention relates to a fluid actuator for influencing the flow along a flow surface by 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 supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which respective different pressures may be applied. The flow in the interaction chamber is distributed to the individual outlet openings as a function of the pressure difference at the control openings.

Abstract: A flow body for a vehicle includes at least one planar skin section with an outer side, an inner side and at least one opening that penetrates the skin section, as well as at least one active flow control device that is designed for moving an air volume. The at least one active flow control device includes an air discharge section that is fluidically connected to the at least one opening, wherein the air discharge section and the at least one planar skin section are manufactured by a layer manufacturing process in the form an integral component that is free of joints, and wherein the air discharge section at least partially supports the skin section in a load-bearing fashion.

Abstract: An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.

Abstract: An exterior structure component for an aircraft with an illuminating device includes a structure with an interior side and an exterior surface with at least one illuminated region and a multitude of optical fibers that extend from the interior side to the at least one illuminated region of the exterior surface. The optical fibers end on the interior side of the exterior structure component in a common interface area that is couplable to an illuminating device. The structure is made from a fiber composite material in which the optical fibers are integrated. In this manner a particularly weight-saving illuminating device that is capable of withstanding external influences may be provided.

Abstract: An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.

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: An exterior structure component for an aircraft with an illuminating device includes a structure with an interior side and an exterior surface with at least one illuminated region and a multitude of optical fibers that extend from the interior side to the at least one illuminated region of the exterior surface. The optical fibers end on the interior side of the exterior structure component in a common interface area that is couplable to an illuminating device. The structure is made from a fiber composite material in which the optical fibers are integrated. In this manner a particularly weight-saving illuminating device that is capable of withstanding external influences may be provided.