A profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.

A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

An aerodynamic lifting system for a VTOL aircraft is provided that includes a lifting structure defining a leading edge portion, a trailing edge portion, an upper surface extending between the leading edge portion and the trailing edge portion, and a lower surface extending between the leading edge portion and the trailing edge portion. A plurality of leading edge and trailing edge movable flaps, along with leading edge openings and trailing edge openings are employed to direct a flow of air, including along an upper surface of the lifting structure. During transition from a VTOL stage to forward flight, when a first leading edge movable flap is in a closed position, a net forward thrust is provided by the flow of air at the leading edge portion.

The invention relates to a profiled structure, elongated in a direction in which the structure has a length exposed to an airflow, and transversely to which the structure has a leading edge (164) and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations (28a) defined by successive teeth (30) and depressions (32).

Along the profiled leading edge and/or profiled trailing edge, the successive teeth (30) and depressions (32) extend only over a part of said length exposed to the flow over which the amplitude and/or spacing of the teeth varies monotonically except for the few teeth nearest each end of said part, a remaining part (280) of said length being smooth.

An impingement cooling system is disclosed, including an airfoil having an aerodynamically sharp leading edge, a fluid source, and a fluid dispersal device connected to the fluid source. The leading edge has a concave internal surface and the fluid dispersal device is configured to project a fluctuating stream of fluid toward the internal surface.

Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.

A free-streamline airfoil includes a front portion, the front portion including a leading edge geometry configured to force a sudden separation of the flow, and a contoured rear portion.

A leading-edge arrangement for a flow body has a curved skin panel having outer and inner sides, and a three-dimensional reinforcing lattice. The curvature of the outer side of the lattice corresponds to the curvature of the inner side of the skin panel. The outer side of the lattice has attachment points connected to the inner side of the skin panel. The lattice is constructed as a three-dimensional framework having a interconnected framework members that form at least one layer of interconnected three-dimensional bodies.

A foil, such as an aerofoil, having a leading edge and a trailing edge, of which at least a portion of one or both of the leading edge and trailing edge has a serrated profile comprising a plurality of adjoining teeth, each tooth having a tip point that represents a local maximum chord-wise extent of the tooth and, on each side span-wise of the tip point, a root point that represents a local minimum chord-wise extent of the tooth and at which the tooth adjoins a respective adjacent tooth, wherein the tooth edge profile varies with an ogee-like curve between tip point and root point such that the tooth is sharper in the neighbourhood of the tip point and in the neighbourhood of the root point than at locations in between.

A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.