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WO/2009/106872A2 |
An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a pri...
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WO/2009/098442A2 |
A control device (16) for a wing (10) comprises an airbox assembly (16) connected to an aerofoil wing tip (17). The airbox assembly (16) includes passages (23) that receive air from the lower surface of the aerofoil (10) and accelerate a...
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WO/2009/098340A1 |
Multi-tipped wind turbine blade comprising a main region (7) of aerodynamic profile with a leading edge (13), a trailing edge (15) and suction and pressure sides (17, 19) between the leading edge (13) and the trailing edge (15) and a tip...
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WO/2009/088780A2 |
Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surf...
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WO/2009/074528A2 |
The invention relates to a wingtip extension (10) with a leading edge (14) and a trailing edge (16) which may be applied to an outer end (8) of a wing (2), wherein the leading edge (14) is at least partly essentially straight and the str...
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WO/2009/064544A1 |
An apparatus for generating vortexes in fluid flow generally adjacent to a surface includes: (a) at least one vortex generating element; and (b) a piezoelectric motor element coupled with the at least one vortex generating element. The p...
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WO/2009/053984A1 |
The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, compu...
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WO/2009/053745A1 |
An aircraft noise-reduction apparatus comprise a flow-facing element(1)and a flow control device(2)positioned downstream of the flow-facing element(1). The flow (5) control device (2) is arranged, in use, to reduce noise induced by unste...
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WO/2009/053649A1 |
The invention relates to a method and a device for creating a continuous protected space along the path of an aircraft (1), in which protected space a maximum induced speed Vtc in a vortex (3) of radius Rtc in the wake of an aircraft (1)...
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WO/2009/048677A2 |
Tip feathers, including forward swept tip feathers, and associated aircraft systems and methods are disclosed. A system in accordance with one embodiment includes an aircraft wing (120) having an inboard portion (122), an outboard portio...
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WO/2009/045694A2 |
Wingtip feathers (141, 142), including paired, fixed features, and associated systems and methods are disclosed. A method for designing an aircraft wing (120) in accordance with a particular embodiment includes providing a geometry for a...
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WO/2009/023352A2 |
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 bod...
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WO/2009/005895A2 |
Embodiments of the invention relate to a method and apparatus for plasma actuated high performance flow control. A specific embodiment of a plasma actuator can incorporate a power source; a first electrode in contact with a first dielect...
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WO/2008/155566A1 |
A winglet comprising a root connected to a distal end of a wing; an upwardly angled section; a tip; and a transition between the upwardly angled section and the tip at which an outboard cant angle of the winglet decreases relative to a r...
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WO/2008/151843A1 |
An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators (3, 4, 5) so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by sai...
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WO/2008/136698A1 |
In a method for flow control of a gas with means of Electrohydrodynamic (EHD) actuating the flow the EHD-actuation generates a small discrete discharge region and a larger drift region respectively, which are both controlled independentl...
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WO/2008/134193A1 |
A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence (406) during landing and/or other operating conditions, and stow the flap edge fence during othe...
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WO/2008/118232A2 |
An airborne mobile platform (10) generally includes a plurality of rotating rotor blades (12) operating in an airflow that forms a boundary layer on each of the rotor blades. At least one of the rotor blades includes a section that encou...
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WO2008037865B1 |
The invention relates to a vertical take-off vehicle including two thermoreactors (1) or turbine engines having a rectangular air inlet (2) which opens into a positive-displacement rotary compressor (3) that supplies compressed air to a ...
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WO2008051269B1 |
Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flow s...
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WO/2008/108881A2 |
This patent provides for a method and apparatus for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface ge...
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WO/2008/100286A2 |
An aircraft can include a wing (42) with a leading edge (64) and a trailing edge (66). The wing has a main body (74) and movable control surfaces (80, 82) coupled to the main body. The wing (42) generates lifting forces when the aircraft...
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WO/2008/064102A2 |
There is disclosed a system for reducing drag and/or vortex induced vibration of a structure, the system comprising a fairing comprising a dampening mechanism adapted to dampen the rotation of the fairing about the structure.
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WO/2008/064104A2 |
There is disclosed a system for reducing drag and/or vortex induced vibration of a structure, the system comprising a fairing moveable from a short fairing configuration to a long fairing configuration.
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WO/2008/061739A1 |
Described is a wing tip shape for a wing, in particular of aircraft, which wing comprises a profile that extends in the direction of the span of the wing (1), and across said direction of the span of the wing (1) extends from the wing le...
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WO/2008/058368A1 |
The nacelle drag reduction device (22) comprises a substantially circular and axis symmetrical external airfoil (24) concentric with a aft section of the nacelle (20) and located outside a propulsive jet zone (30) defined behind the engi...
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WO/2008/051293A2 |
A wake vortex alleviator is provided. The wake vortex alleviator produces rapid variations in the position of vortices emanating from aerodynamic surfaces by using an active flap (302) that moves span-wise back and forth along the outboa...
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WO/2008/048131A1 |
The airplane is provided with right (6) and left (7) wing tips mounted on the right (2) and left (3) half-wings thereof. Said wing tips (6, 7) are mountable on the end parts of a wing, in particular on the end rib (14) of the wing and co...
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WO/2008/031620A2 |
The invention relates to an aerodynamic body (4) for applying to a carrier wing on which at least two flow flaps (5a, 5b) adjacently arranged in the longitudinal direction of the aerodynamic body are mounted, to a carrier wing comprising...
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WO/2007/140771A1 |
The invention relates to a wind turbine blade (5) comprising one or more turbulence generating strips (10), where the strips (10) are placed on a surface of the blade (5). The blade (5) is characterized in that at least one joint area (2...
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WO/2007/135270A1 |
The invention relates to an aircraft comprising a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pyl...
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WO/2007/133239A2 |
An aircraft includes a surface over which an airflow passes. A plasma actuator (1) is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of...
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WO/2007/129313A2 |
A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-pro...
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WO/2007/123612A1 |
An air induction system for an aircraft to control distortion and pressure recovery for improved aerodynamic performance. The system includes an inlet (28) and at least one dielectric barrier discharge generator (34) positioned upstream ...
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WO/2007/117278A2 |
Systems and methods for modifying fluid flowing over solid bodies are provided. A representative system incorporates a vorticity concentration-producing component and a synthetic jet actuator. The vorticity concentration-producing compon...
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WO/2007/113525A2 |
An aircraft (1) comprising: a fuselage (2), opposing wings (3, 4) either side of the fuselage (2), each wing (3, 4) supports at least one tangential flow rotor (5) and has a rotational axis. At least one tail section (3A) is disposed on ...
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WO/2007/095931A2 |
A device for reducing the aerodynamically induced noise at the side edge (12) of a regulating flap (11), in particular a high-lift flap of an aircraft, is described, wherein a device which reduces the aerodynamically induced noise and in...
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WO/2007/096171A1 |
In a flaptrack fairing (3) on the wing (2) of an aircraft (1), which flaptrack fairing (3) partly protrudes beyond the trailing edge (7) of the wing (2) in the direction of the longitudinal axis (x) of the wing (2), the invention provide...
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WO2006076647B1 |
The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe ...
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WO2007068450B1 |
The application describes a rudder of a commercial aircraft. According to the invention, the rudder (100) is divided along its longitudinal direction in at least one region, and the parts (100a, 100b) of the rudder (100) can be spread ag...
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WO2007057155B1 |
Described is a brake flap for an aircraft, which brake flap, for the purpose of delaying the aircraft, can be set at an angle relative to the airstream flowing around it, wherein the flap (20) comprises a free edge (21) which when set at...
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WO/2007/077620A1 |
This invention provides a smart vortex generator (1) comprising a body (3), at least a part of which is formed of a shape memory alloy, disposed on the surface of an object such as a main wing in an airplane which, together with fluid fl...
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WO/2007/054635A1 |
The invention relates to an aircraft (10) comprising: - a fuselage (12), - two wings (14, 16) to which engine nacelles are attached and which are each connected laterally to the fuselage, one on each side thereof, by a central fairing, t...
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WO/2007/036621A1 |
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...
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WO2007015656B1 |
The invention relates to aerohydrodynamics. The inventive method for reducing the aerodynamic noise generated by the separation a medium stream flowing around a structural element surface during the relative motion thereof consists in fo...
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WO/2007/031732A1 |
An aircraft 1 comprises a wing (5) having a positive dihedral, the wing comprising a tip and a wing tip device (7 ) mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region (7d) inclined at...
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WO/2007/018785A1 |
Methods and systems for efficiently increasing the wing area of an aircraft are disclosed herein. An integrated wingtip extension (310) configured in accordance with one embodiment of the invention includes a tapered wing section and a w...
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WO/2007/007108A1 |
This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at ...
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WO/2007/005687A1 |
A flow control device is disclosed including a flow control surface (20) over which fluid is designed to flow in a predetermined direction (F) . Vortex generators (30) are associated with the flow control surface. Each respective vortex ...
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WO/2006/122826A1 |
The present invention relates to a device for adapting aerodynamic characteristics of a wing element (1), wherein the device comprises a winglet (2), wherein the winglet (2) is movably attachable to the wing element (1), and wherein the ...
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