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Patent Searching and Data


Matches 351 - 400 out of 752

Document Document Title
WO/2001/006134A1
The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic fluid flow (10) over a surface. More specifically, the present invention provides a system and method to control aer...  
WO2000055035B1
A wing (11, 12) in combination with a fuselage (10), the wing having a relatively unswept and sharp leading edge, where the thickness to chord ratio is about 2 % or less beyond a calculated point near the fuselage and the thickness to ch...  
WO/2000/055036A2
The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, t...  
WO/2000/055035A1
A wing (11, 12) in combination with a fuselage (10), the wing having a relatively unswept and sharp leading edge, where the thickness to chord ratio is about 2 % or less beyond a calculated point near the fuselage and the thickness to ch...  
WO/2000/050302A1
Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the bound...  
WO/2000/050778A1
An acoustic jet disposed within an aerodynamic surface (9), such as a wing or a blade, has a resilient wall (16) supporting a mass (17). Vibrations of the blade cause oscillatory pressure waves within the acoustic jet, the nozzle (20) of...  
WO2000020274A9
Method and apparatus for impingement on the sonic wave produced by a supersonic gas flow and the gas flow in a boundary layer of a gas that interfaces with a solid substrate comprising providing a source of a mixture of ions and electron...  
WO2000009392A8
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (...  
WO2000020274A3
Method and apparatus for impingement on the sonic wave produced by a supersonic gas flow and the gas flow in a boundary layer of a gas that interfaces with a solid substrate comprising providing a source of a mixture of ions and electron...  
WO/2000/039467A1
An actuator device providing an active surface. The actuator has a base (23) having at least one first electrostatic electrode mounted therein which is oriented for electrostatic cooperative action with an opposing electrostatic electrod...  
WO2000001576A3
The present invention refers to a device which accelerates the fluid (in which the device is immersed) differentially immediately below and immediately above a surface (1). This acceleration can be obtained through a convergent/divergent...  
WO2000009392A3
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (...  
WO/2000/024633A1
The invention concerns a novel design for a supersonic aeroplane whereof the engine burn is much less than that of existing aeroplanes or those being planned. Said design is characterised by the use engines having very different characte...  
WO/2000/020274A2
Method and apparatus for impingement on the sonic wave produced by a supersonic gas flow and the gas flow in a boundary layer of a gas that interfaces with a solid substrate comprising providing a source of a mixture of ions and electron...  
WO2000002775A3
The present invention pertains to the field of air transport and more precisely to that of heavy airplanes and hydrofoils in which the vortex trail of the wing must be reduced. This device for reducing the vortex trail of a high-lift win...  
WO/2000/018641A1
The invention concerns a load-bearing structure such as a wing provided with serrated plates (16) on its free edges for breaking tip vortex generated in those places by distributing the fluid pressure. The vortex dissipation is accelerat...  
WO/2000/015961A1
A wind turbine blade is provided with a plurality of vortex generators (3) projecting from its lee surface (2) for controlling the boundary layer separation. Each vortex generator (3) is formed as a solid and in a top view substantially ...  
WO2000001580B1
The invention concerns a device in the form of a spiral cylindrical cavity, mobile or fixed, capable of being adapted to the tip of all carrier profiles, in particular to aeroplanes and gliders or craft requiring lifting capacity in its ...  
WO/2000/012382A1
A jet aircraft has an elongated fuselage (12) with an intermediate section (16) of maximum lateral cross section, a generally conical aft fuselage section (18) of relatively smaller cross section and a single vertical stabilizer (20) ext...  
WO/2000/009392A2
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (...  
WO/2000/002775A2
The present invention pertains to the field of air transport and more precisely to that of heavy airplanes and hydrofoils in which the vortex trail of the wing must be reduced. This device for reducing the vortex trail of a high-lift win...  
WO/2000/001579A1
An aircraft wing comprising one or more streamwise slots located on its upper surface. Preferably the slots straddle the region where shock occurs and extend from between 43 and 47 % chord to between 53 and 57 % chord.  
WO/2000/001576A2
The present invention refers to a device which accelerates the fluid (in which the device is immersed) differentially immediately below and immediately above a surface (1). This acceleration can be obtained through a convergent/divergent...  
WO/2000/001580A1
The invention concerns a device in the form of a spiral cylindrical cavity, mobile or fixed, capable of being adapted to the tip of all carrier profiles, in particular to aeroplanes and gliders or craft requiring lifting capacity in its ...  
WO/2000/001578A1
An aerofoil incorporating a bump profile on the upper surface thereof such that the bump forms causes a discontinuous change in slope of the upper surface and wherein the leading edge of the bump member is located within plus or minus 2 ...  
WO/1999/050141A1
A deployable flow control device for a flow surface (10) over which fluid having a fluid boundary layer flows which fluid boundary layer exhibits certain dynamics is disclosed. The deployable flow control device comprises a flow effector...  
WO/1999/048755A1
A wing assembly has a wing (10) and at least one slender delta shaped flap (12) with sharp leading edges pointing into the flow direction and deployable above the upper surface of the wing (10). If a high lift configuration is required o...  
WO/1999/044888A1
The present invention pertains to the field of machine-tooling and more precisely relates to apparatus located and operating in a viscous flowing medium. The method for producing a lift force comprises generating a difference between the...  
WO/1999/044887A1
An apparatus and method for mitigating the formation of the necklace vortex (5) in junction flows is disclosed. A lifting structure (20) for inducing a positive lift vector and having at least one tip (22a or 22b) for inducing an outward...  
WO/1999/015711A1
A laminate which includes a barrier layer of OAUGDP bonded silicon oxide and a cellulosic or thermoplastic base layer. A process for applying same. A package container which includes the laminate.  
WO/1999/002397A1
The invention utilizes a moving band (4), typically on an airplane, to increase the apparent speed (9 and 8) and therefore the lift of any body moving through a fluid. The invention will allow take-offs and landings at reduced speeds and...  
WO/1999/000297A1
An active control method and apparatus for encouraging the early destruction of trailing vortices formed by a lifting body having at least two control surfaces (68, 70) on each side and creating multiple vortex pairs is provided. The met...  
WO/1998/056654A1
An airplane having a fuselage (11), opposed main wings (12), and blunt-leading-edge raked wingtips (8) is provided. Each main wing includes an outboard end (9) and a leading edge (14) having an outboard end leading-edge nose and nose rad...  
WO/1998/042568A1
The invention concerns a device for eliminating vortex in the trail of a moving supporting surface, such as an aeroplane wing (14 or 16), comprising tubular means located at the wing end adapted to receive the air at the front of the win...  
WO/1998/007622A1
An aircraft lifting member (wing) comprises a crossflow rotor (2) formed of a core (4) having rotor vanes (5) mounted around it, disposed in a trough (3) at the front upper part of a wing-like body (1). Rotation of the rotor induces a do...  
WO/1997/018990A1
An apparatus for controlling a boundary layer in a flow of an electrically conductive fluid moving relative to a surface in a free-stream direction comprises a plurality of selectively actuated control region tiles (406, 506) distributed...  
WO/1996/040555A1
A propulsion system for accelerating and directionally controlling a fluid having a continuous dynamic surface (40) for circulating through a fluid from an entrainment region (44) where fluid is introduced to the dynamic surface (40) to ...  
WO/1996/040554A1
An aircraft (10) including a stowable, wingtip mounted, vortex turbine (30) for dissipating or extracting energy from a lift induced vortex (28) emanating from the aircraft (10) is provided. The vortex turbine (30) includes a first and a...  
WO/1996/038311A1
The surface of a workpiece is cleaned by generating a steady-state one atmosphere glow discharge plasma above the surface of the workpiece. The use of one atmosphere, uniform glow discharge plasmas generated by a low frequency RF ion tra...  
WO/1996/014242A1
A movable sheet (22) overlying a wing (20) is disclosed that creates laminar flow over its exposed surface. The movable sheet (22) serves as a shield for protecting a suction support structure (24) of a wing (20) against contamination, a...  
WO1996003215A3  
WO/1996/008658A1
In order to break whirls at a surface submerged by a tangential turbulent flow (9), a wall (11) extends parallel to the surface, at a certain distance (12) therefrom, and is provided with periodically arranged structural elements. The di...  
WO/1996/003215A2
Methods for using tip generated vortices to improve performance of foils. These methods include generating a substantially streamwise beneficial vortex (74) near the outboard end (60) of a foil (82). This beneficial vortex (74) spins in ...  
WO/1995/020521A1
A method of reducing the effects of induced drag on a foil. A foil (10) is provided with a series of steps (15, 17) along its span in the trailing edge, whereby a series of spaced vortices (19, 20, 21) are generated. The spanwise spacing...  
WO/1995/011160A1
An aircraft wing possesses at least one vortex generator for controlling boundary layer separation, each vortex generator, which may be in the form of thin wires, being located entirely within the boundary layer such that the wing genera...  
WO/1995/011159A1
An aircraft flight control system in which wing-mounted flight control output devices are employed in a multipurpose role. The system in one form includes wing-mounted port and starboard output assemblies (24, 25) of yaw and roll control...  
WO/1995/000391A1
The boundary layer of a fluid travelling in a mean-flow direction relative to a surface of a wall of a body is controlled by generating in the fluid a magnetic field B having flux lines along the surface of the wall and an electric curre...  
WO/1994/028568A1
A steady-state glow discharge plasma is generated at one atmosphere of pressure within the volume (S) between a pair of insulated metal plate electrodes (14) spaced up to 5 cm apart and rf energized with an rms potential of 1-5kV at 1-10...  
WO/1994/022713A1
The wing of the invention with a span (b) has a main section (1) which has a virtually closed surface in relation to the flow (v) and has an end section at its free end in the form of a wing grid. The wing grid has at least two parallel ...  
WO/1994/018069A1
A supersonic flight aircraft having a longitudinally forwardly extending axis in the direction of flight, and a wing (11, 12) comprising a wing (11, 12) extending generally laterally relative to the axis, and having a leading edge (13, 1...  

Matches 351 - 400 out of 752