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WO/2012/122925A1 |
An aircraft wingtip device, comprising a transition part (1) and a wingtip part (2); the inner end of the transition part (1) is connected to the far end of an aircraft wing, and the outer end of the transition part is connected to the w...
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WO/2012/110845A1 |
An aircraft (10) with improved aerodynamic performances, adapted to keep the directional stability and a very good aerodynamic behaviour at medium-high incidence. Said aircraft (10) comprises a fuselage (12) to which shaped wings (18, 20...
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WO/2011/064456A9 |
The invention relates to the wing of a flying apparatus and a flying apparatus, the leading edge of which wing is at least partly at a sweep, on which leading edge part at a sweep are arranged means (2, 2') which, when activated, raise c...
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WO/2012/081704A1 |
Provided is an ionic wind generating body capable of suppressing generation of an adverse wind. The ionic wind generating body (3) has a first electrode (11A) and a second electrode (11B) which is at least partially displaced in one dire...
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WO/2012/078122A1 |
The invention relates to transport means in fluids. The method for producing traction consists in that a circulating fluid is sucked into the region below a dome-shaped body of a device for producing traction through an upper opening wit...
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WO/2012/048869A1 |
A wing (T) of an aircraft (F) has a pressure-side flow surface (70) and a suction-side flow surface (80) relative to an assumed main direction of attack (S) and comprises a flow fence disposed on a flow surface (100), wherein the flow fe...
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WO/2012/045783A1 |
A lift arrangement for an aircraft (2) comprises an aircraft fuselage section with an outside (3), an aerodynamic lift body (6, 8)attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a...
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WO/2012/036602A1 |
The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano- engineered composite material layer(5) comprising a set of electrodes arranged (7', 7'') in at least ...
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WO/2012/019179A1 |
A fluid interface device, such as an airfoil assembly, can include a device structure and at least one moveable band oriented such that the band moves in a direction of fluid flow. The at least one moveable band can be supported on the d...
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WO/2012/012036A1 |
Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret (12), such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be...
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WO/2012/007358A1 |
A wing tip device for fixing to the outboard end of a wing (401), the wing defining a wing plane, the wing tip device comprising: an upper wing- like element (404) projecting upwardly with respect to the wing plane and having a trailing ...
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WO/2011/135343A2 |
A fluid flow control device (10) for an aerofoil (11) comprises an aerofoil-tip body (17)of aerofoil shape, coupling apparatus (36) adapted to couple one end of the body (17) to an aerofoil (11), and a passive tip blowing assembly (16). ...
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WO/2011/133260A1 |
A method and apparatus comprise a first number of layers of a flexible material (803, 804), a second number of layers of a dielectric material (805, 806), a first electrode (808) attached to a surface layer in the first number of layers ...
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WO/2011/127938A1 |
A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box comprised of spars extending along the spanwise direction of the main wing, a plurality of ribs arranged one in back of the other viewed in the sp...
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WO/2011/101275A1 |
The invention relates to an arrangement of aerodynamic auxiliary surfaces, set up for being disposed on the lower face of an aircraft, and further comprising a longitudinal axis (32) and at least one aerodynamic auxiliary surface (20), w...
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WO/2011/098807A1 |
An apparatus and method for reducing aerodynamic drag is disclosed. The apparatus and method is adapted to reduce wave drag and profile (form) drag associated with aerodynamic bodies, wings, rotor blades, or other aerodynamic surfaces op...
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WO/2011/092429A1 |
The invention relates to a method and device for controlling the mass flow rate of a sonic gas stream (4) in a pipe (3). To carry out the above operation, an electric discharge is applied inside the pipe so as to create a plasma in the p...
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WO/2011/086304A1 |
The invention relates to an aircraft comprising at least one net for reducing aerodynamic noise from a structural element of said aircraft. According to the invention, the flexible net (5A) associated with the structural element (2) is r...
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WO/2011/070532A1 |
This invention discloses a wingtip (10) arrangement for an aircraft wing comprising at least one winglet (12) movably mountable to an extremity (16) of the wing (14); and actuating means (18) connected to the winglet for actuating in use...
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WO/2011/068659A2 |
An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachab...
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WO/2011/055062A1 |
The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substant...
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WO/2011/043431A1 |
Disclosed is a wing structure (1) which comprises a main wing (2) that extends in a second direction intersecting with a first direction serving as a direction along which fluid flows and an auxiliary wing (3) that is separated from the ...
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WO/2011/023270A1 |
The invention relates to a method for determining a flow, wherein flow velocities ΔV-LoS in the measuring direction (mr) are measured by means of sensors (2) at at least one measuring position, comprising the following steps: a) initial...
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WO/2011/016808A1 |
A method and device are provided for manipulating high-speed flows without moving aerodynamic structures. More particularly, a flow control actuator device (10) is provided that is capable of producing a pulsating synthetic jet (31) with...
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WO/2011/004261A1 |
A method of improving aerodynamic performance of foils by the application of conformal, low drag vortex generators. A film of erosion protection material or other conformal material is placed on the foil to provide a medium for the incor...
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WO/2011/004262A1 |
A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been pr...
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WO/2010/148508A1 |
An apparatus for reducing drag on a transport vehicle, which comprises retractable aerodynamic panels for deployment at the rear of the vehicle, behind the cabin, or both. When these panels are deployed, they provide an aerodynamic desig...
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WO/2010/129722A1 |
An improved vvinglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets (302) are located at the outer end of ...
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WO/2010/124877A1 |
A wing tip device (W; W1, W2) for a wing (T; 10a, 10b), comprising aroot (E1) and atip (E2) and the following determinant characteristics: the local dihedral of the wing tip device (W; W1, W2) continuously increases or decreases from the...
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WO/2010/116658A1 |
A first method comprises a step (S5) for investigating the start point of a shear layer as the flow field characteristics around the original shape of an object to be designed, and a step (S7) for giving a planar object to the vicinity o...
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WO/2010/103194A2 |
The invention relates to an eCRT electronic component that belongs to a new generation due to the high resolution thereof for sensing electromagnetic information, and that makes it possible to process the generation of self-induced curre...
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WO/2010/103193A2 |
Balancing problems are mechanical force interactions that generate electron fluctuations according to stable and known relations, elastic deformation of materials and piezoelectric effects. In the field of traditional mechanics that fact...
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WO/2010/100048A2 |
A wing for an airplane comprises a winglet (3) attached to the wing tip of the wing. A curved flap (5) having a variable angle of attack is articulated at the rear edge of the winglet (3), wherein the angle of attack of the curved flap (...
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WO/2010/077464A1 |
A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absol...
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WO/2010/052446A1 |
A shock control fairing (9) for mounting a junction (7) between adjoining aircraft surfaces(3). The fairing has a cross-sectional profile which varies along the length of the fairing. The cross- sectional profile of the fairing (9) has a...
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WO/2010/046679A1 |
The present invention provides a method of, and apparatus for, reducing noise caused by the interaction of airflow between two bluff bodies which are in a generally tandem arrangement, the method comprising providing flow control such th...
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WO/2010/043834A1 |
The lift Machine' is an isolated mechanism which generates lift using the 'Magnus- Effect' to Lift it's own weight, if necessary, under certain operating conditions, in an induced fluid-flow. The Lift Machine can work in any fluid. The d...
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WO/2010/006770A2 |
An aerodynamic flap (1) having a joint apparatus in order to form an axis of rotation for rotatable mounting of the aerodynamic flap (1) on a wing part (10) or structure part having a front flap part (7), which is located in front of the...
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WO/2010/002518A2 |
Systems (100) and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft componen...
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WO/2009/149932A2 |
Disclosed is a device for generating aerodynamic vortices which is to be arranged on the spanwise lateral edge of a wing or on a regulating flap that is adjustably disposed on said spanwise lateral edge of the wing, said wing and flap ea...
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WO/2009/143518A2 |
An airfoil boundary layer control system may be provided. The airfoil boundary layer control system may include at least one airfoil that may include a first surface and a second surface coupled together at a leading edge and a trailing ...
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WO/2009/141536A1 |
Wing-tip device for the tip of a wing or the blade of a wind generator or of a marine generator that makes it possible to reduce or even cancel what are known as wing-tip vortices. In the case of a wind generator, the result provides a s...
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WO/2009/136012A1 |
The setting up of the electron reorganization calls on priority of the various PCT documents filed. The present application relates to the chemical reactions of components before and after the reactions, which release residues, unburnt s...
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WO/2009/129023A1 |
Winglets (130) with recessed surfaces (150), and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing (110) having an inboard portion (111) and an outboard portion (112), and f...
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WO/2009/124728A2 |
Disclosed is a flow element (1) comprising an external side (3) that has a top face (3a) and a bottom face (3b) in relation to the direction of flow, and lateral end sections (5a, 5b) that form the lateral ends of the flow element (1) tr...
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WO/2009/124913A2 |
The invention relates to a flow controlling component (10) for influencing flows around a flow-exposed part (56) in particular of an aircraft. Said flow controlling component (10) comprises a driving device (12) for moving a flow-effecti...
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WO/2009/106871A2 |
An aerodynamic structure comprising a series of shock bumps (3) extending from its surface. The shock bumps are distributed across the structure with a non-uniform spacing (dl, d2) between the centres and/or edges of adjacent bumps. The ...
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WO/2009/106870A2 |
A shock bump (10) comprising a diverging nose (20) and a converging tail. The tail has at least one plan-form contour line with a pair of concave opposite sides (22, 23). The shock bump provides an improved shape with relatively low drag...
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WO/2009/106873A2 |
An aerodynamic structure comprising an array shock bumps (3, 10) extending from its surface, the array comprising: a first series of shock bumps; and one or more shock bumps positioned aft of the first series. Preferably at least one of ...
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WO/2009/106869A2 |
An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form a...
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