Class / Patent application number | Description | Number of patent applications / Date published |
244200000 | By characteristic of airfoil's skin | 25 |
20080265100 | LAMINAR FLOW SURFACES WITH SELECTED ROUGHNESS DISTRIBUTIONS, AND ASSOCIATED METHODS - Laminar flow surfaces with selected roughness distributions, and associated methods are disclosed. A representative method for designing an airfoil includes selecting a parameter that includes a flow behavior distribution and/or a surface shape for an airflow surface. Based at least in part on the selected parameter, the method can include (a) selecting a target roughness value and determining a chordwise location forward of which surface roughness is at or below the target roughness value and/or (b) selecting a target chordwise location and determining a roughness value for a region forward of the chordwise location, with the surface roughness at or below the roughness value. In particular embodiments, a percentage of a local chord length of the airfoil over which the roughness is below a target value decreases in a spanwise direction. In another embodiment, the roughness at a particular spanwise location can increase over at least three values, continuously, in a step manner, or otherwise. | 10-30-2008 |
20090078830 | AIRCRAFT COMPRISING A CENTRAL FAIRING THAT ADJUSTS THE PRESSURE ON THE WING STRUCTURES BY MEANS OF LOCAL GEOMETRIC DEFORMATIONS - An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing. | 03-26-2009 |
20090294596 | Method of Reducing Drag and Increasing Lift Due to Flow of a Fluid Over Solid Objects - A method for reducing drag, increasing lift and heat transfer using a de-turbulating device is disclosed, with the preferred form of the deturbulator being a flexible composite sheet. The flexible composite sheet comprising a membrane, a substrate coupled to the membrane, and a plurality of ridges coupled between the membrane and the substrate, wherein a vibratory motion is induced from the flow to at least one segment of a membrane spanning a distances, wherein the vibratory motion is reflected from at least one segment of the membrane to the flow, and; wherein a reduction in fluctuations is caused in the flow pressure gradient and freestream velocity U at all frequencies except around f, where f>>U/s. hi one embodiment, the flexible composite sheet can be wrapped around a blunt leading edge of a plate facing an incoming flow of fluid, hi another embodiment, the flexible composite sheet can also be wrapped around one or more regions of an aerodynamic surface where a flow pressure gradient changes from favorable to adverse, hi another embodiment, the flexible composite sheet is replaced with a plurality of plates coupled to a substrate, wherein the plurality of plates has edges that interact with a fluid flow similar to a compliant surface. A method of adding a system of small viscous sublayer scale (around 30-80 micron height) backward and/or forward facing steps on the surface of an airfoil or other 2-D or 3-D streamlined aerodynamic body is disclosed, where the backward facing step is in a favorable pressure gradient and forward facing step is in an adverse pressure gradient, so as to speed up the freestream flow over the front portion of the airfoil or body and reduce skin friction drag by creating a marginally separated thin (0.1 to 10 microns) slip layer next to the wall behind the backward facing step and extending a significant distance behind said step. This method reduces the drag and increases lift if the body is a wing. Also the same method can be applied to a bluff body, such as an automobile to reduce flow separation induced drag by stabilizing the wake flow and making it appear to the flow as a solid streamiling extension of the original body. The gas mileage of a vehicle improves when treated in this manner. | 12-03-2009 |
20100213320 | DEVICE WHICH IS SUBJECT TO FLUID FLOW - A device such as an aerofoil which in use is subject to fluid flow, includes an outer surface part the geometry of which is variable to affect the fluid flow, the device including a support structure which supports the outer surface part, the support structure being internal of the device and including a plurality of support members of composite material the geometry of the support structure being changeable by an actuating apparatus, between a first stable geometry and a second stable geometry to effect variation in the geometry of the outer surface part, the support members providing structure stiffness to the outer surface part. | 08-26-2010 |
20100301171 | SHOCK BUMP ARRAY - An aerodynamic structure comprising an array shock bumps ( | 12-02-2010 |
20100301172 | AERODYNAMIC STRUCTURE WITH SERIES OF SHOCK BUMPS - An aerodynamic structure ( | 12-02-2010 |
20100301173 | AERODYNAMIC STRUCTURE WITH ASYMMETRICAL SHOCK BUMP - An aerodynamic structure comprising a shock bump ( | 12-02-2010 |
20100308176 | AERODYNAMIC STRUCTURE WITH NON-UNIFORMLY SPACED SHOCK BUMPS - An aerodynamic structure comprising a series of shock bumps ( | 12-09-2010 |
20100314500 | SHOCK BUMP - A shock bump ( | 12-16-2010 |
20110042523 | LAMINAR FLOW SURFACES WITH SELECTED ROUGHNESS DISTRIBUTIONS, AND ASSOCIATED METHODS - Laminar flow surfaces with selected roughness distributions, and associated methods are disclosed. A representative method for designing an airfoil includes selecting a parameter that includes a flow behavior distribution and/or a surface shape for an airflow surface. Based at least in part on the selected parameter, the method can include (a) selecting a target roughness value and determining a chordwise location forward of which surface roughness is at or below the target roughness value and/or (b) selecting a target chordwise location and determining a roughness value for a region forward of the chordwise location, with the surface roughness at or below the roughness value. In particular embodiments, a percentage of a local chord length of the airfoil over which the roughness is below a target value decreases in a spanwise direction. In another embodiment, the roughness at a particular spanwise location can increase over at least three values, continuously, in a step manner, or otherwise. | 02-24-2011 |
20110084174 | PASSIVE ADAPTIVE STRUCTURES - Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic load exerted on the body by the flow is one such parameter, typically characterized as lift or drag. It is the aim of the present disclosure to teach the use of passive adaptive morphing structures to manage these aerodynamic loads. | 04-14-2011 |
20110114794 | ENVIRONMENTAL COMPRESSION FOR FRICTION REDUCTION - A viscous drag-reducing surface is provided that achieves harmony between an object and the environment (liquid or gas) through which the object moves. Rather than opposing the effects of friction, the surface according to the present invention eliminates friction by bonding the environment to the object. The pressure generated on the object by the environment as the object moves through the environment effectively compresses the local environment onto the surface. Once compressed against the surface, the local environment in contact with the surface becomes static relative to the surface whereas the environment that is not in contact with the surface achieves a laminar flow. Friction is thereby significantly reduced, since friction between like substances (i.e. the in-contact environment and the environment that is not in contact with the surface) is minimal. | 05-19-2011 |
20140217241 | BOUNDARY LAYER FLOW DISRUPTORS FOR DELAYING TRANSITION TO TURBULENT FLOW - An apparatus delays the transition of a boundary layer flow from laminar to turbulent. Flow disruptors are positioned to be in contact with a boundary layer flow moving in a flow direction over a surface. Each flow disruptor generates fluctuations in the boundary layer flow such that the frequency of the fluctuations is a damping region frequency defined by an amplification rate curve associated with the boundary layer flow. | 08-07-2014 |
20160009376 | Semi-open Fluid Jet VTOL Aircraft | 01-14-2016 |
20160114883 | ACTIVELY-CONTROLLED SUPERHYDROPHOBIC SURFACES - Active superhydrophobic surface structures are actively-controlled surface structures exhibiting a superhydrophobic state and an ordinary state. Active superhydrophobic surface structures comprise an outer elastomeric covering defining an exposed surface, a controlled group of MEMS (micro-electro-mechanical system) actuators at least covered by the elastomeric covering, and, a controlled region of the exposed surface corresponding to the controlled group. The controlled region has a superhydrophobic state in which the controlled region is textured. The controlled region also has an ordinary state in which the controlled region is smooth (i.e., less textured than in the superhydrophobic state). Active superhydrophobic surface structures may be part of an apparatus that includes a controller and/or one or more sensors. The controller, sensors, and the controlled region may form a feedback loop in which the active superhydrophobic surface is actively controlled. | 04-28-2016 |
244200100 | Vortex generation in boundary layer | 10 |
20080265101 | Vortex ring generator - 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. | 10-30-2008 |
20080272241 | Device for Reducing a Drag Produced by the Relative Displacement of a Body and Fluid - The device reduces the drag or head loss due to the relative motions of a body and a fluid or of a fluid in a body. Within the surface of the body in contact with the fluid or on top of this surface, the device has elements ( | 11-06-2008 |
20100123046 | Disbanded Cascaded Array for Generating and Moving Plasma Clusters for Active Airflow Control - An array of electrodes for selectively generating plasma is described herein. The array includes a first electrode disposed along a first dielectric, and at least a second electrode. A second electrode is sandwiched between the first dielectric and the second dielectric. A power supply provides electrical power to at least the first and second electrodes. In turn, a power supply controller controls the power supply, so as to regulate the electrical power supplied to at least the first and the second electrodes, and to cause the first and second electrodes to generate and move plasma to modify different airflow patterns. | 05-20-2010 |
20110006165 | APPLICATION OF CONFORMAL SUB BOUNDARY LAYER VORTEX GENERATORS TO A FOIL OR AERO/ HYDRODYNAMIC SURFACE - 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 incorporation of planform edge vortex generators. The form edge is shaped to achieve submerged vortex generating shapes of chevron or ogival planforms, extending primarily chordwise on the foil surface. The vortex generators promote improved boundary layer dynamics by mixing free stream flow into the boundary layer while minimising separation and fluid losses. At the trailing edge, the shape formed with the chevrons applied apex forward, acts as a vented gurney tab series and additionally as disruptors to the Von Karman Street wake, delaying sheet rollup into the tip vortice. | 01-13-2011 |
20110095135 | PRISMATIC-SHAPED VORTEX GENERATORS - A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow. | 04-28-2011 |
20120312930 | STRUCTURE FOR REDUCING A FLOW RESISTANCE OF A BODY IN A FLUID - The invention relates to a body ( | 12-13-2012 |
20140021302 | Spin Resistant Aircraft Configuration - A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft. | 01-23-2014 |
20150329200 | RADAR ENERGY ABSORBING DEFORMABLE LOW DRAG VORTEX GENERATOR - A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.) the generation of radar cross-section spikes produced by the VGs themselves. | 11-19-2015 |
20160083083 | VORTEX GENERATORS RESPONSIVE TO AMBIENT CONDITIONS - A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity. | 03-24-2016 |
20160122006 | LOW DRAG TURBULENCE GENERATORS FOR AIRCRAFT WINGS - A wing design for an aircraft, including a plurality of turbulence generating devices distributed along a leading edge of a wing, configured in shape and in orientation to the wing to minimize drag and turbulence during cruising flight, and to increase turbulence during takeoff and landing. | 05-05-2016 |