Abstract: A rotorcraft provided on top with a waterdrop-shaped fairing arranged below the rotary wing of a main rotor of the rotorcraft and overlying a cover covering a power plant of the rotorcraft. The trailing edge(s) of the fairing is/are provided with a respective movable member guiding a first stream of air flowing along the fairing and escaping from the trailing edge towards the rear of the rotorcraft in flight. By way of example, the movable member is arranged as a flap or as a bladed roller that may potentially be motor-driven as a function of the effects of the first stream of air on the behavior of the rotorcraft in flight.

Abstract: Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.

Abstract: Various air deflector shapes, sizes and configurations for use in a load compensating device on an airfoil are provided. The air deflector arrangements are configured to alter the airflow around the air deflector in order to affect sound or acoustics associated with the air deflector when deployed during operation. Some example configurations that may alter the air flow around the air deflector include air deflectors having a plurality of apertures, air deflectors including a scalloped edge, and/or air deflectors including a plurality of protrusions extending from a portion of the air deflector.

Abstract: A natural-laminar-flow swept transonic wing fitted with a wing tip pod for controlling the location of a wing shock in the wing tip region, such that the shock extends outboard substantially up to the wing tip without substantially sweeping forward toward the wing tip leading edge.

Abstract: The fairing assembly uses inflatable wall panels that automatically deploy and retract at certain speeds to provide sturdy, light-weight aerodynamic fairings, which cover and enclose the space between the tractor truck and connected trailers to improve the aerodynamics of the tractor-trailers. The fairing assembly uses a module design and includes two or more panel units, a blower/vacuum and an electronic controller. Each panel unit includes a panel housing and an inflatable wall panel, which inflates and deflates to deploy and retract from its housing. The controller actuates the blower/vacuum to provide a continuous flow of air to the inflatable wall panels during deployment and to draw an air flow from the inflatable wall panels when retracting the panels back into the panel housings.

Abstract: In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams.

Abstract: A wing skin, which was secured to a wing structure by a plurality of fasteners extending through the wing skin, is removed from the wing and aligned with a template. Template holes are drilled through the template corresponding to each of the fastener holes of the wing skin. The template is then aligned with a new wing skin, and pilot holes are drilled through the new wing skin corresponding to each of the template holes. The new wing skin is then aligned with the wing structure such that the pilot holes permit access to corresponding fastener holes of the wing structure. A mill bit is then positioned through each pilot hole and aligned with the center of the corresponding consumable bushing in the fastener hole of the wing sub-structure, and the skin pilot holes are milled to form fastener holes in the new wing skin aligned with existing sub-structure.

Abstract: Embodiments of the invention relate to a method and apparatus for providing high thrust density plasma, and/or high control authority plasma. In specific embodiments, such high thrust density, and/or high control authority, plasma can be at or near atmospheric pressure. Embodiments pertain to a method and apparatus that use electron confinement via one or more magnetic fields, and/or one or more electric fields, in a manner to improve the ionization due to surface plasma actuators. Specific embodiments can improve ionization by several orders of magnitude. This improved ionization can result in a high electric field inside the sheath for the same applied voltage and can result in very high thrust.

Abstract: 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.

Abstract: A method of retrofitting vortex generators on a wind turbine blade is disclosed, the wind turbine blade being mounted on a wind turbine hub and extending in a longitudinal direction and having a tip end and a root end, the wind turbine blade further comprising a profiled contour including a pressure side and a suction side, as well as a leading edge and a trailing edge with a chord having a chord length extending there between, the profiled contour, when being impacted by an incident airflow, generating a lift. The method comprises identifying a separation line on the suction side of the wind turbine blade, and mounting one or more vortex panels including a first vortex panel comprising at least one vortex generator on the suction side of the wind turbine blade between the separation line and the leading edge of the wind turbine blade.

Abstract: An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.

Abstract: Thermal actuation of riblets is described herein. One disclosed example apparatus includes a riblet defining an aerodynamic surface of a vehicle. The disclosed example apparatus also includes a thermal expansion element within or operatively coupled to the riblet, wherein the thermal expansion element changes shape in response to a surrounding temperature, to displace a movable portion of the riblet relative to the aerodynamic surface to alter an aerodynamic characteristic of the vehicle.

Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.

Abstract: Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft.

Abstract: Aerodynamic microstructures having sub-microstructure are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure defining an external surface of a vehicle, and a pattern of sub-microstructures superimposed on the microstructure to convey a representation of an image.

Abstract: The present subject matter directed to a rotor blade assembly for a wind turbine having at least one rotatable aerodynamic surface feature configured thereon. The rotor blade assembly includes a body shell including a pressure side surface and a suction side surface extending between a leading edge and a trailing edge. The aerodynamic surface feature is disposed adjacent to the pressure side surface, the suction side surface, and/or both. In addition, the surface feature may have a generally airfoil-shaped cross section. As such, an actuator can be configured at least partially within an internal volume of the surface feature, the actuator being configured to rotate the surface feature relative to the body shell.

Abstract: A method and apparatus for forming a winglet formed as a one-piece composite for an aircraft is presented. The winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the winglet. The root region is configured to receive an attachment system for attaching the winglet to a wing of the aircraft.

Abstract: A fairing for a rotor, the fairing comprising a movable top half-shell, the fairing including a mover device provided with a slideway, the slideway being provided with a stationary portion secured to the head of the rotor, the slideway being provided with a movable portion secured to the top half-shell, the movable portion sliding in elevation along the stationary portion along an axis in elevation, the mover device including a driver device co-operating with the movable portion to move the movable portion in translation relative to the stationary portion from a closed extreme position to an open extreme position, and vice versa.

Abstract: An airflow generation device of an embodiment has a main body and a voltage application unit. The main body has a base formed of an insulating material and provided with a first electrode and a second electrode. The voltage application unit generates an airflow by applying voltage between the first electrode and the second electrode. Here, the main body is formed to include a portion which gradually decreases in thickness from a center portion to an end portion.

Abstract: A blade comprises a first blade surface, a second blade surface forming the reverse surface of the first blade surface, a primary wind receptor protruding from the front end of the first blade surface in a direction away from the second blade surface and with the back surface formed in a curved shape concave toward the front side in a forward direction, a front edge connected to the front end of the primary wind receptor and the front end of the second blade surface and formed in a curved shape convex toward the forward direction, and a back edge connected to the back end of the first blade surface and the back end of the second blade surface and formed in an acute angle facing the back side of the forward direction.

Abstract: An aerodynamic unit is attached onto a roof of a road vehicle so that air passes over the unit during forward movement of the road vehicle. The unit has a first end for positioning distal to a rear end of a vehicle roof and a second end for positioning proximal a rear end of a vehicle roof. The unit includes an inclined guide portion which decreases in height in a direction towards the trailing end of the unit. The unit also includes a flow director, which directs air flow to the guide portion, disposed at or near the leading end of the aerodynamic unit. The flow director has a height increasing in a direction from the leading end towards the trailing end. The unit may include vortex generators protruding from the guide portion. A fin may extend along each side of the unit in a direction between the trailing end and the leading end.

Abstract: The invention provides a fan cowl (11) of an aircraft engine made of a composite material having an optimized structure for withstanding the expected loads and for being able to be manufactured as a monolithic ensemble. The structure comprise a skin (13), frames (15) of a closed cross-section arranged in a transverse direction to the longitudinal axis of the aircraft and longitudinal beams (17, 19) comprising first parts (21) of a closed cross-section to be superimposed to the transverse frames (15) in their crossing zones and second parts (23) of an open cross-section in zones not crossing transverse frames (15) having their webs (41) arranged in a same plane. The invention also refers to a manufacturing method of said fan cowl (11).

Abstract: A wind turbine blade airfoil trailing edge (TE) with a first waveform profile (44B, 44C, 44E) as seen from behind, formed by ruffles or alternating ridges (21) and valleys (22) formed on the airfoil (20) and ending at the trailing edge. The trailing edge may further include a second waveform profile (48B, 48C, 48E) as seen from above, resulting from serrations formed by an oblique termination plane (32B) of the trailing edge or by other geometry. The ridges and/or serrations may be asymmetric (44E, 48E) to increase a stall fence effect of the ridges on the suction side (SS) of the trailing edge. The first and second waveforms may have the same period (44B, 48B) or different periods (44C, 48C).

Abstract: A lipskin for a nacelle includes a generally annular first lipskin segment that extends generally upstream from a first lipskin edge to a forward edge. The forward edge is proximate to a hilite of the nacelle. The lipskin also includes a generally annular second lipskin segment that extends generally downstream from the forward edge to a second lipskin edge. The second lipskin segment is oriented generally concentrically about the first lipskin segment. The first lipskin segment and the second lipskin segment are coupled together at the forward edge.

Abstract: An aspect of the invention relates to a surface cover for a body which can be brought into contact with a liquid, comprising: a layer which at least partly contains gas and which is designed and arranged such that at least some sections of a layer face facing the liquid contacts the liquid; a gas-permeable layer which is arranged on the gas-containing layer on a face that faces the body and is opposite the face facing the liquid or which is integrally formed with the gas-containing layer; and a gas-supplying device which is connected to the gas-permeable layer such that gas can flow from the gas-supplying device to the gas-containing layer through the gas-permeable layer. The invention also relates to an arrangement and a use.

Abstract: Methods, apparatuses and systems are disclosed relating to maintaining an outer mold line of a vehicle after a payload is deployed from the vehicle, and providing a low-force non-frangible method of deploying a payload from a vehicle.

Abstract: A torque tube door and related method steps may include a door coupled to an inboard wing flap, such that the door is movable with the flap to selectively cover and uncover a torque tube opening in an aircraft fuselage.

Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

Abstract: An arrangement for reducing drag on the body of an aircraft with a relatively wide fuselage comprises a gas turbine engine. At least one duct is selectively moveable between a closed position and an open position, such that the at least one duct allows airflow to move toward a fan rotor in the gas turbine engine in the open position, but blocks airflow when in the closed position. An aircraft body is also disclosed.

Abstract: A sunroof wind deflector for a vehicle includes a leading edge, a trailing edge and an outer surface extending between the leading edge and the trailing edge. The outer surface has a radius of curvature that changes along a length thereof so as to attenuate shear layer spreading.

Abstract: Drag experienced by a vehicle traveling through an environmental media, such as air or water, may be modified by one or more energy beams which may increase or decrease drag. A control system may be used to actively modulate the drag of the vehicle by selectively transmitting energy beams. Energy beams may include electric pulse signals, pulsed air, piezoelectric, infrared, ultraviolet, laser, optical band, microwave, thermal other known acoustic, electric, optical, or other electromagnetic energy and any combination thereof. This could be a constant or pulsed energy beam and adjusted for the speed and/or vertical lift, frequency, density, angle, pulse and wavelengths experienced by the vehicle. Charged particles may be emitted from the vehicle itself and then utilized in front or behind the vehicle via electric current to improve the boundary layer, boundary flow.

Abstract: Systems, devices and methods are disclosed for controlling the flow of a fluid over the window of an optical instrument housing in a freestream flow field. For example, the flow upstream of the housing may be split to create a flow region over the window that is conducive to successful operation of the instrument. The flow region may be maintained for various rotations of the housing about yaw, pitch, and roll axes. The disclosed features in some embodiments induce flow regions with reduced spatial and temporal density gradients of the flow over the window.

Abstract: An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension, liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Also described are the details of an isentropically expanded hypersonic stochastic switch (a singularity), which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle whereby a continuous flow continuum is transformed into a stochastic flux.

Abstract: A fluid supply system for a rotary machine, the system includes a rotor assembly with an array of blades arranged to be driven about a primary axis to provide propulsive thrust in use, each blade having a longitudinal axis, the rotor assembly including a casing structure, wherein the casing structure is rotatable in unison with the blades about the primary axis; and a directional fluid intake, the intake being rotatably mounted at an outer surface of the casing structure about a second axis which is angularly offset from the primary axis and which is offset from and independent of the longitudinal axis of the blade.

Abstract: A multilayer construction for an array of aerodynamic riblets incorporates a first layer composed of a material with protuberances, the first layer material having shape memory and a second layer composed of a material exhibiting a second characteristic with capability for adherence to a surface.

Abstract: A method for simulating a fluid flow that includes a laminar to turbulent boundary layer transition on a computer, the method comprising: for one or more locations on or near a boundary surface: performing a first calculation where a local boundary layer is taken to be a laminar boundary layer; performing a second calculation where the local boundary layer is taken to be a turbulent boundary layer; comparing a result from the first calculation to a result from the second calculation; and based on the comparing, selecting the result of the first calculation or the result of the second calculation; and inputting the selected result for the one or more locations into a simulation of activity of a fluid in a volume comprising the boundary surface.

Abstract: An aircraft comprises a wing assembly, a pod, and a pylon attaching the pod to the wing assembly. The pylon has a swept pylon flap, which is configured to unload the pylon and pod during flight of the aircraft, and also to create downward flow that counters a vortex trailing the pod.

Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.

Abstract: Examples of drag reduction apparatuses and assemblies for land vehicles, and particularly for attachment to a roll-up door of a land vehicle, are described. A drag reduction apparatus may include a plurality of panels foldably coupled together and automatically deployable into an unfolded configuration in which the panels define a cavity therebetween. The panels may be made from a semi-rigid material so that the panels generally conform to a roll-up door when the door is rolled up and/or down. The apparatus may be attached to the roll-up door using any of a variety of attachment mechanisms, for example a slidable keder-type device and/or one or more spring-loaded members.

Abstract: In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear attachments connecting the mast to two rear attachment points of the turbine engine, and a rear covering covering the rear attachments and providing a streamlined fairing. The rear covering includes two side walls, each including a first portion extending along and in proximity of the mast and extending rearwards, and a second portion projecting sideways relative to the first portion towards its outside, to cover the rear attachments. Each second portion is substantially a bulge and is connected to the first portion along a curved connection line extending between front and rear points situated substantially level with an inner longitudinal edge of the first portion to minimize the impact on a flow of bypass stream leaving the bypass passage.

Abstract: A cavity system that tends to increase the thickness (28) of the shear layer (22), comprising: a cavity (2) and a plate (104); the plate (104) comprising a plurality of holes (4) through it, wherein the proportion of the area of the plate (104) taken up by the holes is ?60%, for example ?75% or ?90%; the plate (104) being positioned in the proximity of a leading edge (14) of the cavity (2); the surface of the plate (104) at a perpendicular or oblique angle to the actual or intended flow direction (6). The plate (104) may be positioned at an oblique angle to the flow direction (6). One or more flow alteration elements, for example elongate members (34) positioned across the holes and/or members (38) positioned directly behind or in front of the holes (4).

Abstract: A surface area of a structure is fabricated with a textured surface that reduces the surface wear rate or erosion caused by a high speed flow of fluid containing abrasive particles over the surface area. More particularly, a leading edge surface such as a rotor leading edge surface, an aircraft airfoil leading edge surface, a propeller leading edge surface, etc. is fabricated with a textured surface comprised of a plurality of grooves that alter or break up a high speed flow of fluid containing abrasive particles over the textured surface. The grooves are contacted by the high speed flow of fluid containing the abrasive particles and alter or break up the flow of fluid and abrasive particles and thereby reduce surface wear rate or erosion of the structure leading edge.

Abstract: A motor vehicle component having at least one surface which, in the installed position, forms an outer side of the motor vehicle, in which the surface has substantially V-shaped and/or substantially U-shaped projections, with the closed sides thereof facing a direction of air flow during normal operation of the motor vehicle.

Abstract: An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

Abstract: Provided is a nose for a supersonic flying object, which has a natural laminar flow nose shape capable of suppressing laminar-turbulent transition and drastically reducing a frictional drag. The nose for a supersonic flying object has a low resistive body shape symmetrical about a central axis as a base shape, wherein the base shape is approximately a cone shape having a linear, simple convex curve, or simple concave curve generatrix and a deformation element having a wavy shape is added to the base shape.

Abstract: Accessories are mounted to a gas turbine engine from a frame attached to a pylon which is used to mount the engine to an airframe. The frame independently mounts the accessories so that engine vibrations are not transmitted to the accessories.

Abstract: An array of aerodynamic riblets incorporates a high elongation elastomeric layer having spaced tips and optionally a protective cladding. The elastomeric layer may be adhered to an aerodynamic surface directly or as an appliqué in combination with one or more of an adhesive layer, one or more supporting polymer layers and a metal foil layer.

Abstract: A method for attenuating aerodynamic noise from a landing gear may include researching a start point of a shear layer as a flow field characteristic of a region in the vicinity of an original shape of the landing gear, and adding a plate-shaped object in the vicinity of the start point, changing the start point to an edge portion of the plate-shaped object to make the shear layer farther from the original shape. Another method for attenuating aerodynamic noise from a landing gear may include researching a static pressure and an airflow velocity in a region in the vicinity of the landing gear as a flow field characteristic of the region, and adding a plate-shaped object covering a surface of the landing gear which is different from a surface facing an upstream side in an airflow direction, increasing the static pressure in the region to reduce the airflow velocity.

Abstract: Ventilated aero-structures include a micro-lattice structure operatively coupled to a honeycomb core. The interface between the honeycomb core and the micro-lattice structure is configured to permit air flow to and from the honeycomb core via the micro-lattice structure. Aircraft include a ventilated aero-structure and a ventilation system configured to circulate air through the ventilated aero-structure. Some methods include coupling a micro-lattice structure to a honeycomb core. Some methods include utilizing a ventilated aero-structure to assemble an aircraft.

Abstract: Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.