Abstract: An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·?; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=

Abstract: Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing.

Abstract: A vortex ring generator adapted to be associated with a body subjected to fluid flow, the vortex ring generator being adapted to produce a fluid flow in the form of a vortex ring with the fluid flow moving over the body from the vortex ring generator.

Abstract: A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.

Abstract: The invention pertains to an engine pod for an aircraft, one side of which features several fin-shaped vortex generators (3, 4, 5) such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases in order to improve the maximum lift, wherein the first vortex generator lies within a positioning corridor (K31) that is situated between two boundary lines (51, 52), wherein the point of origin (51a) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and the longitudinal engine pod coordinate X=L/4, the end point (51b) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=25 degrees and the longitudinal engine pod coordinate X=L·?, the point of origin (52a) of the second boundary line (52) is the point on the circumference of the engine pod wit

Abstract: An aircraft (10), in particular a trainer aircraft with improved aerodynamic performance, having a configuration able to keep a directional stability and a very good aerodynamic behaviour even at very high angles of attack, where, traditional configurations prove themselves inefficient. In particular, this configuration foresees a forebody (52) with variable section, optimised for high angle of attack flights, a LEX vortex control device (72) at least one diverterless air intake (46), and a wing profile (18, 20) optimised in order to reduce the buffet effects typical of low aspect ratio wings with thin profile and variable camber. The aircraft (10) presents, finally, staggered tails (44 and 38), to optimise the aerodynamic performance.

Abstract: A device for controlling a vortex trail generated by the oblong element of an aircraft bearing surface comprises a control means (8) which is arranged on the fixing element (11) of the oblong element (5) and on the bearing surface (4) in such a way that the base (12) thereof is brought into contact with the leading edge (6) of said bearing surface and which has a triangular shape on a plane perpendicular to the longitudinal axis thereof whose two adjacent sides form flanks interconnected by a rounded edge.

Abstract: An apparatus and method is provided for attenuating aerospace engine noise and unsteady pressure fluctuations associated with high velocity exhaust flows. The apparatus and method reduce acoustic fatigue damage to aerospace vehicles that may be caused by the reflection of exhaust energy from landing and/or launch platforms. The apparatus includes a passive treatment area associated with the platform operable for reducing the magnitude of the reflected sound waves and unsteady pressure fluctuations from the high velocity exhaust mass flow exiting from the engine. The passive treatment area may include a layer of sound absorptive material, at least one set of roughness elements for disrupting high velocity flow structures. A protective cover may be positioned over the passive treatment area for permitting exhaust flow to pass therethrough while still providing adequate structure to support the weight of the aerospace vehicle.

Abstract: According to the invention, a device for the generation of eddies creates or destroys eddies in a flowing medium in a particularly simple manner, with particularly low energy requirement with the lowest possible pressure drop, whereby the device comprises one or more profiles, for the flowing medium to flow around, which are provided with an external drive for a periodic movement relative to the flowing medium with an angular frequency ?. The profiles are thus periodically displaced with an angular frequency ? by an external drive.

Abstract: The flueted aircraft wing has one or more thin Streamline Flow Panels placed longitudinally over the upper surface of an aircraft wing, and extend out in front of the wing leading edge. These panels capture airflow from along the wing leading edge in addition to the relative wind flow ahead of the wing, and direct the total airflow over the surface of the wing. The Streamline Flow Panels partition regions of vortex airflow over the wing and reduce transverse airflow. Wing tip vortices and induced drag are greatly reduced, and lift is increased. Fuel economy is substantially improved because airflow energy losses are reduced.

Abstract: In order to reduce the surface of a support mast (2) of an aircraft engine in contact with the hot exhaust gases (18) of said engine, a vortex-generating device (24) is positioned on the surface of the mast (2), near the hot region (22). Thus, the vortex generated in the flow of cold gases (16) crosses the hot air and modifies its path, thus preventing it from reaching zones (22) of the mast that are not predefined. This system makes it possible to adapt to the operating conditions of an already-built aircraft, without any notable increased weight.

Abstract: An arrangement for reducing vorticity downstream of a turbine nozzle guide vane 34 in a gas turbine engine. The arrangement including directing cooling air through the guide vane 34 and out through outlets 40 in directions to counteract the wave vorticity produced downstream of the guide vane 34.

Abstract: Wake vortices are made less detectable or reduced in their effect on nearby vehicles by re-orientation of vorticity about an axis in the direction of vehicle motion to transverse vorticity interacting with the longitudinal vorticity. The re-orientation may be by a flapping foil, and arrangements of a plurality of foils moving toward or from each other may be used. Alternatively, fluid may be injected longitudinally between opposite surfaces each having a port so that selective suction through the ports alternately attaches the fluid to the surfaces to deflect the fluid from the longitudinal direction and generate transverse vortices. Oppositely rotating vortices may be formed by separators extendable from each surface to engage the deflected fluid, and extension of the separators may be varied to control vortex trajectory. The transverse vortices may be intermittent, selected for speed, or made asymmetric for maneuvering.

Abstract: The invention relates to a wing, a wing, a tail unit or grid fins for a flying object moving with supersonic speeds. The wing comprises leading edges and tailing edges. According to the invention, the contour of at least one of the leading contour and the tailing contour has a meandered shape. By means of the inventive meandered contours the wave drag of the flying object may be decreased. The inventive design of the leading or tailing edges of a wing can be used for aircrafts, spacecrafts, missiles, projectiles and the like.