Aerodynamic element having a cross section in an airflow direction with a suction side surface, a pressure side surface, and a trailing edge extending between the suction side surface and the pressure side surface. The aerodynamic element further comprises an extension body attached to the trailing edge near the suction side surface of the aerodynamic element. A top surface of the extension body is flush with the suction side surface. The aerodynamic element (10) is e.g. applied in a rotor blade for a wind turbine.

In the field of aeronautics, there is disclosed an aircraft with reduced installation noise and specifically an aircraft wing and jet engine system including an aircraft wing and at least one jet engine with high bypass ratio attached to the wing, suitable for emitting a jet intercepted by a first portion of the trailing edge of the wing. The range formed by the set of angles with orientation defined by a vector following the direction of the jet and by a vector following the tangent at a point of the first portion of the trailing edge and oriented towards the wing tip of the wing, is included within a range of angles selected from the range delimited by 5 and 65, and the range delimited by 115 and 175.

An aerodynamic control surface including an upper panel having an upper panel aft end portion, a lower panel having a lower panel aft end portion, mechanical fasteners connecting the upper panel aft end portion to the lower panel aft end portion, and a fairing having a fairing forward end portion and a fairing aft end portion, wherein the fairing forward end portion is connected to either the upper panel or the lower panel, and wherein the fairing aft end portion is connected to the other of the upper panel or the lower panel.

There is disclosed a method of treating a metal article which tapers towards an edge. A compressive force is applied to a treatment region of the article to generate an edge region of compressive residual stress adjacent the edge, and the treatment region is spaced apart from the edge region by an intermediate region.

Various embodiments of an airfoil and machines with airfoils are disclosed. The airfoils include a thicker leading airfoil portion and a thinner trailing airfoil portion. In one embodiment, the leading airfoil portion is formed by bending a body of the airfoil back toward itself. In another embodiment, the leading airfoil portion has a solid geometry and includes two elliptic surfaces. To prevent detachment of airflow, the leading airfoil portion includes at least two arc portions or surfaces that act to direct the airflow down to the trailing airfoil portion in a manner that stabilizes vortexes that may form in the region of changing thickness.

An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plurality of tubercles and the plurality of crenulations varies in a non-periodic fashion. The non-periodic fashion may be according to a Fibonacci function and may mimic the configuration of a pectoral fin of a humpback whale. The tubercles and crenulations may be defined with respect to a pivot point. The spanwise profile, including the max chord trailing edge curvature, may closely follow divine spirals and related Fibonacci proportions. The spanwise chord thickness may vary in a nonlinear pattern. Related methods are also described.

The aerodynamic element has a cross section in an airflow direction with a trailing edge (10c). The aerodynamic element (10) further includes a non-symmetrical swallow tail shaped cavity body (1, 2) attached to the trailing edge (10c) of the aerodynamic element (10). The aerodynamic element (10) is e.g. applied in a rotor blade for a wind turbine.

A combination comprises an aircraft wing trailing edge section and an adjustment body. The adjustment body comprises a tapered cross section in a local chord axis direction of the wing trailing edge section, a lower adjustment body surface connected to a top surface of the aircraft wing trailing edge section and a back-end surface having a height. The adjustment body is positioned such that the back-end surface is flush with the trailing edge of the aircraft wing trailing edge section. Attaching the adjustment body onto a top surface of the wing trailing edge section leads to compensation of an offset rolling moment due to unavoidable structural shape deviations of the aircraft and eliminates additional structural reinforcement requirements on the trailing edge compared to edge wedges mounted on the bottom surface of trailing edges. The trailing edge section may comprise a flap.

A device including a profiled member conformed to constitute an edge portion of an aircraft aerodynamic profile. The device includes a blower chamber to be pressurized and an air ejector nozzle making it possible to provide fluidic communication between the blower chamber and an external surface of the profiled member, the profiled member, the blower chamber and the nozzle forming an assembly to be mounted in one piece on the aerodynamic profile to constitute a trailing edge thereof. The blower chamber and the nozzle are formed directly in the profiled member, the profiled member, the blower chamber and the air ejector nozzle being formed in one piece.

In one embodiment, an airfoil includes a first side and a second side opposite the first side, and an apparatus coupled to the first side of the airfoil, the apparatus comprising a first edge having a first uneven edge pattern.