Abstract: A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.

Abstract: Provided are vertical tail structures with symmetry action slat systems. Specifically, a vertical tail structure comprises a main element and a leading edge element. The leading edge element comprises a first slat body and a second slat body that are symmetrically positioned on either side of a longitudinal centerline of the vertical tail structure. Each slat body is configured to move between a retracted position and an extended position to increase a camber sag of an airfoil of the vertical tail structure and thereby increase a maximum aerodynamic yawing moment provided by the vertical tail structure. In a first operable mode, each of the slat bodes are in the respective retracted position. In a second operable mode, one of the slat bodies is in the respective extended position. The extended position of each of the slat bodies includes a pitch angle and an extension distance from the main element.

Abstract: A rotor blade for an aircraft includes first and second blade tips, a blade body, and a vortex-generating blade. The blade body has an end forming the first blade tip of the rotor blade and an airfoil section configured such that during rotation, pressure acting on a lower surface of the blade body is greater than pressure acting on an upper surface of the blade body. The vortex-generating blade is disposed at an end of the rotor blade and forms the second blade tip. The vortex-generating blade also has an airfoil section configured such that during rotation, pressure acting on a lower surface of the vortex-generating blade is smaller than pressure acting on an upper surface of the vortex-generating blade.

Abstract: The invention relates to a wind turbine blade having integrated thermoplastic anchoring sites for attachment of surface mounted devices, a method for producing such blade and a wind turbine equipped with such blade.

Abstract: An aerodynamic device for enhancing lift and reducing drag on a body, comprising a plurality of raised members, each having a symmetric profile and including a central portion having an elongated profile, and first and second outer portions having elongated profiles and arranged substantially parallel to and on opposing sides of the central portion, wherein the plurality of raised members are situated adjacent one another to form a continuous structure on or defining at least a portion of a surface of the body and oriented such that the raised members are substantially aligned with a direction of localized flow on the body. An aerodynamic device for enhancing lift and reducing drag of a flying disc, wherein the plurality of raised members are situated adjacent one another to form a continuous structure and the raised members are oriented in a substantially circumferential direction on the surface of the flying disc.

Abstract: Pressure relief holes are sized and positioned on each fin of a projectile to allow high pressure from one side of the fin due to canard and fin interaction to bleed to a low pressure area on the opposite side of the fin. The location of the pressure relief holes target pressure differences due to canard roll control downwash while not affecting pressure differences due to projectile attitude. The fin planform area remains small enough to meet packaging and fire requirements for this type of munition and large enough to aerodynamically stabilize the airframe thereby enabling a more robust pitch and yaw autopilot design.

Abstract: A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.

Abstract: A rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The rotor blade assembly also includes at least one noise reducer secured at the trailing edge. The noise reducer(s) includes at least one serration having a base portion and at least one side edge feature extending from the base portion. Further, the base portion extends along a first plane. The side edge feature(s) extends out of the first plane so as to reduce vortices generated by the serration(s).

Abstract: The invention relates to a method for producing or designing a leading edge of a lifting structure, wherein starting at the midpoint of the base (0,0), a curve is applied to the profile of the structure, the length “L1” of which is according to the maximum thickness of the NACA section in the base of the profile “H0” in the base and is defined by the equation L1=0.0510H02?0.0790H0+15.5790, and the maximum height of which on the “x”-axis is located at point “L1/2” and defined by means of the relationship x=0.0137(L1)1.4944, the shape of said curve being defined by means of the equation: (y?y0)=0.0000000107x6+0.0000016382x5?0.0000794412x4+0.0010194142x3+0.0097205322x2+0.0136993913x, and the rest of the curve being calculated by means of an iterative process according to the above.

Abstract: Systems and methods for tailoring fluid and energy interaction through surface texturing. The methods comprise: receiving behavior input data specifying known or modeled interactions between a material and pre-solved solution surfaces, discrete input data specifying parameters of a surface to be textured, and continuous input data specifying ranges of values for environmental characteristics that the surface is to be subjected to during use; transforming the behavior input data into a composite response surface comprising a weighted combination of the pre-solved solution surfaces generated based on the discrete input data and the continuous input data; determining an optimized surface texture for the surface based on the composite response surface and desired behavior data specifying a desired interaction between the material and the surface to be textured; and outputting the optimized surface texture (e.g., to a surface texturing machine) so that the optimized surface texture is applied to the surface.

Abstract: Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object.

Abstract: A method of controlling a fluid flow using momentum and/or vorticity injections. Actively controlling an actuator allows for direct, precise, and independent control of the momentum and swirl entering into the fluid system. The perturbations are added to the flow field in a systematic mater providing tunable control input, thereby modifying behavior thereof in a predictable manner to improve the flow characteristics.

Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.

Abstract: A vortex generator for a wind turbine blade to be mounted to a wind turbine blade includes: a platform portion to be mounted to a surface of the wind turbine blade; and at least one fin disposed upright on the platform portion. The platform portion has a cross section having a curved convex shape, at least along a blade spanwise direction of the wind turbine blade.

Abstract: An aircraft includes an elongated wing having a leading edge extending to a trailing edge, an upper surface extending from the leading edge to the trailing edge, and a lower surface extending from the leading edge to the trailing edge; an air passage forming an entrance opening at the leading edge and configured to extend to an exit opening positioned at the upper surface; and an airflow stop configured to control airflow movement through the air passage.

Abstract: A wind turbine blade includes a trailing edge including a radially inboard portion and a radially outboard portion opposite the radially inboard portion. The trailing edge further includes at least one serrated portion extending at least partially between the radially inboard portion and the radially outboard portion. The serrated portion includes at least one substantially acoustically absorbent material.

Abstract: The invention provides an aircraft wing, comprising a fixed wing and a wing tip device at the tip. The wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device in the locked flight configuration. A rotatable locking member is associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other. The rotatable locking member comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin is urged toward the rotation axis of the rotatable locking member by a camming action of the guide surface on the locking pin, thereby preloading the locking mechanism.

Abstract: A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.

Abstract: A method for calculating a trailing edge that is to be produced for a rotor blade of an aerodynamic rotor of a wind power installation, wherein the rotor blade has radial positions with respect to the rotor, the rotor blade has a local blade profile that is a function of the radial positions with respect to the rotor and the trailing edge has a jagged profile having a plurality of spikes, wherein each spike has a spike height and a spike width, and the spike height and/or the spike width is calculated as a function of the radial position thereof and/or as a function of the local blade profile of the radial position thereof.

Abstract: The invention relates to a locking mechanism for a folding wing tip. The locking mechanism has a locked configuration, in which a first part is received in a second part such that the first part may not be withdrawn from the second part along the longitudinal axis of the locking mechanism, and an unlocked configuration, in which the first part is received in the second part such that the first part may be withdrawn from the second part along the longitudinal axis of the locking mechanism, wherein the locking mechanism is moved between the locked configuration and the unlocked configuration by rotation of at least one of the first part or second part around the longitudinal axis of the locking mechanism.

Abstract: A rotor blade system includes a rotor blade having an outboard section and an inboard section, a hinge joint rigidly attached to the outboard section, and an adhedral tip engaged with the hinge joint. A method includes pivotally attaching an adhedral tip to the rotor blade and pivoting the adhedral tip during flight to change the flight performance characteristics of the blade during flight.

Abstract: An apparatus and method using an interference body to shape a sonic boom signature is provided herein. The interference body can be installed on various control surfaces, including a vertical control surface. The interference body can be sized and positioned to create a desired amount of interference with expansion wave s generated by one or more components of an aircraft. In one configuration, the interference body can be operative to reduce the sonic boom formed by an aircraft operating at or above supersonic speeds.

Abstract: Universal vortex generators for wind turbine rotor blades and methods of manufacturing same are disclosed. The vortex generator includes a base portion configured for attachment to at least one of a suction side surface or a pressure side surface of the rotor blade and at least one airflow modifying element extending from the base portion. In addition, the airflow modifying element includes one or more discontinuities configured therein so as to increase flexibility of the vortex generator.

Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.

Abstract: Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.

Abstract: A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion.

Abstract: The present invention includes a method of controlling a fluid flow using momentum and/or vorticity injections. Actively controlling an actuator allows for direct, precise, and independent control of the momentum and swirl entering into the fluid system. The perturbations are added to the flow field in a systematic mater providing tunable control input, thereby modifying behavior thereof in a predictable manner to improve the flow characteristics.

Abstract: A flying toy for throwing and/or catching includes an elongated body forming a fuselage. The body extends along a longitudinal axis from a front end to a rear end. A lift-generating wing is non-movably attached in relation to the body. A horizontal stabilizer is disposed at or near the rear end of the body, where the horizontal stabilizer disposed behind the lift-generating wing. A vertical stabilizer is disposed at or near the rear end of the body, where the vertical stabilizer is disposed behind the lift-generating wing. A push surface is attached to the body and extends perpendicular in relation to the longitudinal axis. The push surface faces towards the rear end of the body. The push surface allows a user to push the flying toy forward when thrown.

Abstract: 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 principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.

Abstract: The invention relates to a vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).

Abstract: A trailing edge protective cap for a rotor blade of a wind turbine and method of manufacturing same is disclosed. The method includes infusing a first material onto a first mold so as to form a first part having a length. While the first part is still in the first mold, the method may also include placing a second mold onto the first part. The method may then include infusing a second material onto the second mold and at least a portion of the first part so as to form a second part having a length. The first and second parts may then be joined or infused together along a portion their respective lengths so as to form the protective cap, wherein the protective cap includes a joined section and an open section.

Abstract: A rotary actuator includes a housing, a rotor assembly rotatably journaled in said housing and including a rotary output shaft, a central actuation assembly including a central mounting point formed in an external surface of the rotary output shaft, said central mounting point proximal to the longitudinal midpoint of the rotary output shaft, a mounting assembly adapted for attachment to an external mounting connector of a mounting surface of an aircraft structural member, and an actuation arm removably attached at a proximal end to the central mounting point, said actuation arm adapted at a distal end for attachment to an external mounting feature of an aircraft assembly to be actuated.

Abstract: A throwing or catching toy includes a generally elongated spheroidal body defined as having a longitudinal axis, where a length of the body along the longitudinal axis between a front end to a back end of the body is longer than an equatorial diameter. A support is attached to the body and extends beyond the back end of the body and does not extend beyond the front end of the body. A lift-generating wing is non-movably attached to the support. A push surface is disposed near the back end of the body, where the push surface is generally perpendicular to the longitudinal axis. A horizontal stabilizer is attached to the support and disposed behind the lift-generating wing. An impact transfer surface is attached directly to the support, where the impact transfer surface is disposed within the body and fixed between the front end of the body and the support.

Abstract: A system and method for providing reverse thrust is disclosed. The system can include one or more cascade elements. The one or more cascade elements can each include a plurality of vanes to redirect engine thrust in a forward direction relative to travel. Some, or all, of the vanes can include raised geometric patterns configured to increase the mixing of the airstreams between the reversed engine thrust and the airstream over the vehicle to reduce noise and improve reverse thrust. The angle, curvature, and geometric pattern of the vanes can be optimized for a particular cascade element, engine, location on the engine, row, or can be optimized individually to maximize reverse thrust and minimize noise.

Abstract: An arrangement to reduce noise of a wind turbine rotor blade is provided, including a wind turbine rotor blade and a noise reduction device. The noise reduction device includes a serrated extension for at least reducing noise generated from the wind turbine rotor blade, the noise reduction device attached to the trailing edge section. The serrated extension has a number of first and second teeth. The designs of the first and second teeth are differently compared to each other such that suction side noise and pressure side noise are both reduced by the teeth of the serrated extension. Advantageously, the first teeth and the second teeth are arranged in an alternating, periodic pattern and differ from each other by an angle of inclination with regard to a trailing edge streamline and or by its planform shape. Furthermore, a method to reduce noise of a wind turbine rotor blade is provided.

Abstract: In one aspect, a rotor blade assembly for a wind turbine may generally include a rotor blade extending lengthwise between a root and a tip. The rotor blade may include a pressure side and a suction side extending between a leading edge and a trailing edge. Additionally, the rotor blade assembly may include a chord extender having an attachment portion coupled to at least of the pressure side or the suction side and an extension portion extending outwardly from the attachment portion beyond the trailing edge. The extension portion may extend chordwise between a first end disposed adjacent to the trailing edge and a second end disposed opposite the first end. The extension portion may include a surface defined between the first and second ends. The extension portion may further include at least one stiffening rib projecting outwardly from the surface.

Abstract: A wind turbine rotor blade has a longitudinal axis, a blade root, a blade tip, a pressure side, a suction side and an aerodynamic profile which, in a longitudinal section of the rotor blade, has a profile chord and a thick trailing edge. The rotor blade includes a multiplicity of flow deflection elements which are arranged on the thick trailing edge and have respective inflow surfaces which are shaped and arranged such that a radial flow running in the direction from the blade root toward the blade tip is diverted by the inflow surface in the direction of the profile chord.

Abstract: For establishment of a laminar attachment line flow, an aircraft wing includes a leading edge including an attachment line, where air impinging on the region flows in a boundary layer spanwise along the leading edge. The leading edge and the attachment line are at least partially formed at first and second slats. The second slat is located adjacent to the first slat in the downstream direction of the attachment line flow, so that the leading edge includes a slat-to-slat junction, where a slat cavity is formed. A duct has a duct entrance at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing. The duct entrance extends around the leading edge and over the range of positions of the attachment line at the slat-to-slat junction.

Abstract: Exemplary practice of the present invention provides and implements a superior small-scale test model of a full-scale vessel hull describing a smooth axisymmetric body. The boundary layer of a smooth axisymmetric body moving in water is characterized, in succession from front axial-longitudinal end to back axial-longitudinal end, by a laminar region, an unstable region, an intermittent region, and a turbulent region. The smooth axisymmetric body's intermittent region is characterized by generation of turbulent spots, which bring about the turbulent region. According to exemplary inventive practice, a “turbulent spot inducer” (ring-shaped structure or structural arrangement) is strategically sized and placed to increase generation of turbulent spots, thereby reducing (axially-longitudinally shortening) the intermittent region and enlarging (axially-longitudinally lengthening) the turbulent region.

Abstract: The present disclosure relates to a wind turbine blade, in particular a wind turbine blade having devices or structures for reducing noise generated by the wind turbine blade during use and related method. The wind turbine blade comprises at least a first longitudinal section having a cross section perpendicularly to a longitudinal direction, the cross section having a plurality of flow modulating devices including a first primary flow modulating device and a secondary flow modulating device for modulating noise spectra, wherein the first primary flow modulating device and the first secondary flow modulating device are spaced perpendicularly to the longitudinal direction. Also disclosed is a method of retrofitting a wind turbine blade.

Abstract: Methods of manufacturing rotor blade components for a wind turbine and rotor blade components produced in accordance with such methods are disclosed. In one embodiment, the method generally includes providing a mold of the rotor blade component; coating at least a portion of an interior surface of the mold with an elastomeric material; inserting a foam material within the mold; and, removing the rotor blade component from the mold, wherein the elastomeric material forms a cover skin around at least a portion of the rotor blade component. In an alternative embodiment, the method includes providing at least one support member defining a profile for the rotor blade component on a mold surface; coating at least a portion of the support member with an elastomeric material; and, allowing the elastomeric material to cure on the mold surface so as to form the rotor blade component.

Abstract: An arrangement for reducing noise which is generated by a wind turbine blade is provided. The wind turbine blade has a first panel and a second panel. The first and the second panel are arranged at a trailing edge of the wind turbine blade, wherein the first panel is adjacent to the second panel. The first panel includes a first transition zone and the second panel includes a second transition zone. The first transition zone and the second transition zone are engaged in a way that whistle tones produced by a gap of the wind turbine blade, the gap being located between the first panel and the second panel, is reduced or even avoided.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: 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 adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock (9) so as to reduce its angle of sweep.

Abstract: Apparatus to adjust airfoils of rotor blades are disclosed. An example apparatus includes a first surface to be attached to a trailing edge of a rotor blade; a forward edge having a first thickness; an aft edge having a second thickness; and a middle portion between the forward edge and the aft edge having a third thickness greater than the first and second thicknesses.

Abstract: In one aspect, a rotor blade for a wind turbine is disclosed. The rotor blade may include a body extending between a blade root and a blade tip. The body may define a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the body may define a chord line extending between the leading and trailing edges. The rotor blade may also include an airfoil modifier coupled to at least one of the pressure side or the suction side of the body. The airfoil modifier may define an end surface disposed adjacent to the trailing edge. At least a portion of the end surface may extend at a non-perpendicular angle relative to the chord.

Abstract: 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 (d1, d2) between the centers and/or edges of adjacent bumps. The non-uniform spacing between the bumps can be arranged to give maximum wave drag alleviation for the minimum number of bumps as a function of the shock strength across the span, leading to minimum wing weight penalties for a given amount of wave drag alleviation.

Abstract: A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.

Abstract: Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft.

Abstract: An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.