Abstract: A Coanda system for controlling directions of an aircraft. The system includes a fluid passage defined in part by a casing wall having an inner surface facing the fluid passage. The fluid passage is configured to pass fluid from a first end inlet to a second end outlet. A fluid control element including a Coanda surface is disposed at the second end outlet. The fluid control element is moveable within the second end outlet to direct the fluid exiting the fluid passage between an upper gap and a lower gap, around the Coanda surface. A contour element is disposed on the inner surface of the casing wall upstream of the fluid control element, and further assists in directing the fluid to the open gap.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Abstract: A fluidic actuator is configured to be mounted to an airfoil surface. The actuator includes a rotor supported within a housing. The rotor contains at least one generally radially extending nozzle that converges from an entry at an interior circumference of the rotor to an exit at an exterior circumference thereof, the converging shape of the nozzle assuring high velocity airflow at the nozzle exit. In one form, each nozzle also includes a curved path by which high-pressure air is enabled to induce spinning of the rotor. The fluidic actuator further includes a diffuser through which high-pressure air from the nozzles is cyclically ejected from those of the nozzles instantaneously exposed to the diffuser. In one form, the rotor spins at 300 revolutions per second and provides nozzle ejections effective to avoid boundary layer separation; i.e. to maintain an attached boundary layer flow over the airfoil.

Abstract: Active fluid control systems and related methods are disclosed. A disclosed example active fluid control system includes a plurality of plenums coupled together to define a fluid flow passageway, and a plurality of fluidic actuators coupled to outer surfaces of respective ones of the plenums. The fluidic actuators define actuator inlets and actuator outlets. The fluid flow passageway defined by the plenums to fluidly couple the fluidic actuators and a pressurized fluid supply source. The plenums are configured to couple to an aircraft structure supporting an aerodynamic surface to enable the actuator outlets to be mounted to the aerodynamic surface. The fluidic actuators are configured to provide the pressurized fluid to the aerodynamic surface to modify an aerodynamic characteristic of the aerodynamic surface.

Abstract: An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

Abstract: The systems and methods provided herein are directed to a stationary device for simulating the periodic unsteadiness typically produced by turbines in an air stream. A streamlined body includes a line of jets along its leading edge that pulses air at an angle against the air stream, and a separate line of jets along its trailing edge to expel a sustained air flow in the same direction as the air stream.

Abstract: An aircraft wing assembly including a main wing portion, a high-lift device with a flow surface including an upper skin portion and a lower skin portion, wherein the flow surface of the high-lift device comprises a first flow surface portion, a second flow surface portion and a third flow surface portion, wherein the first flow surface portion is micro-perforated for an air inflow, wherein the first flow surface portion extends on the upper skin from the leading edge in chordwise direction for 2% or less of the local chord and extends on the lower skin from the leading edge in chordwise direction for 2% or less of the local chord, and wherein the second flow surface portion is not micro-perforated and extends over the rest of the upper skin portion, and wherein the third flow surface portion is not micro-perforated and extends over the rest of the lower skin portion.

Abstract: A leading-edge slat for an aircraft is proposed, which includes a front skin), a back skin, a spar and an air inlet for receiving air at an elevated temperature for de-icing or anti-icing. In the slat, at least one air chamber is created, which is supplied with said air. A first portion of the back skin is attached to the spar at a distance to the bottom section, wherein a second portion of the back skin is attached to the top section. Thereby, a region in front of the fixed leading edge is created, into which air from air outlets integrated into the back skin can be exhausted outside of the slat.

Abstract: A wing structure for an aircraft includes a stationary wing, a movable wing and at least one plasma actuator. The movable wing is configured to have a slot between the movable wing and the stationary wing. The at least one plasma actuator is configured to control air flow through the slot.

Abstract: A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.

Abstract: An element including a leading edge forming a box delimited by a skin forming a lower surface and an upper surface and pierced with holes, in which the skin includes an inner wall and an outer wall that are electrically conductive and an electrically insulating intermediate wall, a pump for expelling or injecting air from or into the box. Each hole is equipped with an anti-clogging system including a conductive base, a needle made of piezoelectric material, one end of which is secured to the base, an electrical generator generating an electrical current in the needle, in which the form of the needle is such that a space is created between the needle and the edges of the hole, and in which the base has a recess in the extension of the space. Such an installation makes it possible to eliminate the residues which are lodged in the holes.

Abstract: A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.

Abstract: A projectile (100) with incidence steerable control surfaces (2) each pivotable with respect to the projectile (100), comprises: central control means (5) for controlling the control surfaces (2), a control arm (11) adapted to rotate the central control means (5) around pitch (Y) and yaw (Z) axes of the projectile (100), positioning means for positioning the arm (11), adapted to position one end of the arm (11) in a position determined with respect to an absolute reference frame, the positioning means comprising a cone (13) movable in translation so as to pivot the central control means around an orientation axis (AO), and a toothed wheel (16) meshing with a motorization intended to pilot the angular position of the orientation axis in an absolute reference frame.

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

Abstract: An integrated test method for testing the operation of an electrical power converter powered by an on-board power supply network and using field-oriented control to control a three-phase electric motor for a thrust reverser of a turbojet of an aircraft is provided. The method includes: receiving an order to initiate the integrated test; controlling the converter from a current setpoint defined from a non-zero in-phase component and a zero quadratic component; measuring the currents delivered on each of the three outlet phases of said converter; determining in-phase and quadratic components of the three phase currents previously measured; comparing these components with the in-phase and quadratic components of the current setpoint; and sending a notification concerning the malfunctioning or the functioning of the thrust reverser as a function of the result of the comparison.

Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

Abstract: There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.

Abstract: Methods and systems for controlling a fluid flow field near a surface are disclosed. In some embodiments, the system includes an array of oscillating bodies disposed on the surface to provide physical modification to the flow field. Fluid jets are also emitted from an outlet in the oscillating body to provide virtual modification of the flow field through momentum addition. Fluid jet sources, including synthetic jet generators such as piezoelectric drivers and sources of compressed fluids such as air or water, are positioned to be in fluid communication with the outlet at intervals during the oscillation of the oscillating body. Controlling the oscillation amplitude and frequency of the body, as well as the location of oscillating body outlets and frequency of fluid jet emission, have advantageous effects for the surface such as improved heat transfer properties and reduction in structural vibration and noise.

Abstract: A flow body for a vehicle includes at least one planar skin section with an outer side, an inner side and at least one opening that penetrates the skin section, as well as at least one active flow control device that is designed for moving an air volume. The at least one active flow control device includes an air discharge section that is fluidically connected to the at least one opening, wherein the air discharge section and the at least one planar skin section are manufactured by a layer manufacturing process in the form an integral component that is free of joints, and wherein the air discharge section at least partially supports the skin section in a load-bearing fashion.

Abstract: A nacelle may comprise an inlet cowling defining an inlet of the nacelle, wherein the inlet cowling comprises an inlet cowling maximum point and an inlet cowling aft edge, wherein the inlet cowling aft edge comprises an aft edge length; and a boat tail cowling disposed aft of the inlet cowling, wherein the boat tail cowling comprises a boat tail cowling forward edge having a forward edge length, and wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be smaller than the aft edge length, forming a step, the step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge.

Abstract: Various embodiments of the present disclosure provide an aircraft anti-icing system that includes an aircraft engine inlet component, a pressurized air source, and a heat source operable to: (1) heat the leading edge of the aircraft engine inlet component via the heat source to prevent ice formation on the outer surface of the leading edge; and (2) direct pressurized air from the pressurized air source so that it forces water off of the outer surface of the inlet components (and into the external air flow) as the water travels downstream from the leading edge outer surface downstream toward the trailing edge, which prevents runback ice formation.

Abstract: An aircraft rotor blade includes a surface of the rotor blade, at least one main hole that extends through the surface and has a width and a length, and at least one leader hole that extends through the surface and has a length that is less than the length of the main hole and arranged spaced from and adjacent the main hole. The leader hole gradually increases in width from a first end of the leader hole opposite the main hole to an opposed second end of the leader hole proximate the main hole to operatively gradually distribute stress in the leader and main holes and rotor blade and reduce an amount of the stress exerted therein.

Abstract: A system and method of analyzing an engine model is disclosed. The system and method include performing a Dynamic Systems Analysis on the engine model that includes modifying a transient allowance of the engine model to determine an optimal balance between performance and operability and assessing the conservatism level of the engine model.

Abstract: A high-efficiency, stall-proof airfoil is an aircraft wing configuration whereby a motive force directly induces gaseous fluid flow across a lifting surface of the airfoil without requiring a movement of the wing through an air space. The airfoil is provided with means to control a pitch, a roll and a yaw motion and to control a position and stability of the aircraft. When not undergoing horizontal displacement, it provides highly efficient use of fuel resources, precluding the formation of drag and its incumbent power consumption. Air pressure at a bottom of the wing remains essentially ambient. Therefore, differential pressure between a lower surface of the wing and an upper surface of the wing maintains its maximum possible quantity. Virtually, all of the power consumed is utilized in a production of lift. Additionally, because lift is generated without regard to an angle-of-attack, forward speed, nor a configuration of a leading edge of the wing, the configuration is essentially stall proof.

Abstract: An actuator assembly is capable of manipulating a fluid flowing around a flow body, the fluid being received or able to be received in a volume of at least one cavity arranged in the flow body, and the fluid passing through at least one opening in the at least one cavity during manipulation of the fluid. In this process, the volume of the at least one cavity can be changed by moving a wall portion delimiting or defining the cavity. The actuator assembly has a drive unit with at least one actuator, which executes a periodic movement over time when actuated, causing a translational movement of the wall portion delimiting or defining the cavity and the wall portion being shaped in terms the topology thereof in such a way that it is adapted to the shape of the at least one cavity with the at least one opening thereof.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example active flow control system includes a plurality of nozzles arranged in an array across a surface of an aircraft. The nozzles are oriented to eject air across the surface to reduce airflow separation. The active flow control system also includes an air source coupled to the nozzles and a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

Abstract: An aerodynamic surface assembly is provided to facilitate control of the flow over the aerodynamic surface. The aerodynamic surface assembly includes an aerodynamic surface defining an outer mold line over which a fluid is to flow in a downstream direction. The outer mold line defines a smooth contour that is interrupted by step down region that is inset relative to the smooth contour defined by the outer mold line upstream thereof. The aerodynamic surface defines an orifice opening in to the step down region. The aerodynamic surface assembly may also include an overhang extending from the outer mold line of the aerodynamic surface upstream at the orifice. The overhang extends in the downstream direction and at least partially over the orifice. The aerodynamic surface assembly may also include a fluidic actuator defining a pair of curved passageways extending from an input region and are in fluid communication with the orifice.

Abstract: Methods and systems for controlling a fluid flow field near a surface are disclosed. In some embodiments, the system includes an array of oscillating bodies disposed on the surface to provide physical modification to the flow field. Fluid jets are also emitted from an outlet in the oscillating body to provide virtual modification of the flow field through momentum addition. Fluid jet sources, including synthetic jet generators such as piezoelectric drivers and sources of compressed fluids such as air or water, are positioned to be in fluid communication with the outlet at intervals during the oscillation of the oscillating body. Controlling the oscillation amplitude and frequency of the body, as well as the location of oscillating body outlets and frequency of fluid jet emission, have advantageous effects for the surface such as improved heat transfer properties and reduction in structural vibration and noise.

Abstract: An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending between a forward end and an aft end along a longitudinal direction and a boundary layer ingestion fan mounted to the fuselage at the aft end of the fuselage. The air injection assembly includes a plurality of injection ports defined on a surface of the fuselage at a location upstream of the boundary layer ingestion fan. A supplemental airflow is provided through a fluid passageway to the injection ports where it is ejected to displace at least a portion of relatively higher velocity boundary layer airflow. In this manner, the airflow entering boundary layer ingestion fan is more uniform, has less swirl distortion, and has a lower average velocity.

Abstract: Systems, methods, and devices are provided that provide hybrid flow control for a simple hinged flap high-lift system using sweeping jet (SWJ) actuators for active flow control (AFC) and adaptive vortex generators (AVGs) that may be actuated by flap deflection for passive flow control (PFC). The various embodiments may significantly reduce mass flow, differential pressure, and power requirements for equivalent flow control performance when compared to using AFC only. The various embodiments may reduce the power requirement of AFC, while still maintaining the aerodynamic performance enhancement necessary for high-lift applications using a simple hinged flap. The various embodiments may provide the necessary lift enhancement for a simple hinged flap high-lift system, while keeping the pneumatic power requirement (mass flow and pressure) for the AFC within an aircraft's capability for system integration.

Abstract: A stealth craft's aerodynamics and flight stability are improved with the use of a multi-faceted dihedral planform. The stealth craft includes a multi-faceted dihedral planform extending in a direction from a front to a rear of a craft (or wing) and defined by a first set of facets followed by a second set of facets. In an exemplary embodiment, the first and second sets of facets have an angle of incline that is ascending and descending, respectively, with respect to the direction of the planform. Selected ones of the first and second sets of facets are configured with insufflation slots for improving aerodynamics and stability, the insufflation slots extending spanwise in a direction transverse to the direction of the planform and provided to insufflate a fluid to form a cushion of air along the multi-faceted dihedral planform for improving aerodynamics and stability.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example method includes supplying pressurized air to a plurality of nozzles. The nozzles arranged in an array across a control surface of an aircraft, and the nozzles are oriented to eject the pressurized air in a substantially streamwise direction. The method further includes activating the nozzles to eject the pressurized air in sequence to create a wave of air moving in a spanwise direction across the control surface.

Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.

Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.

Abstract: A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

Abstract: A nacelle assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan nacelle bounding a bypass flow path. The fan nacelle includes a first nacelle section and a second nacelle section. The second nacelle section includes a moveable portion movable relative to a forward portion to define a secondary flow passage. The first nacelle section includes an inlet lip. A thrust reverser is configured to selectively communicate a portion of bypass airflow between the bypass flow path and the secondary flow passage. A pump is configured to selectively communicate airflow between the inlet lip and the secondary flow passage. A method of flow distribution for a gas turbine engine is also disclosed.

Abstract: An anti-icing apparatus includes an anti-icing piccolo tube for an aircraft component with a plurality of self rotating elements. Each self rotating element of the plurality of self rotating elements includes a first inlet to receive a working fluid, a second inlet to receive the working fluid, a peripheral layer that connects the first inlet and the second inlet, and a plurality of outlets placed on the peripheral layer that expulses the working fluid through jets. The jets rotate each self rotating element and dynamically impinges the working fluid on an internal surface of the aircraft component.

Abstract: A rotor blade for a reaction drive type helicopter is provided. The rotor blade includes a main duct extending from a proximal end, couplable to and for fluid communication with a rotor hub, to a distal end for ducting a first air/gas stream from the rotor hub to the distal end. A nozzle is attached to an outlet of the main duct at the distal end for receiving the first air/gas stream from the main duct and releasing the first air/gas stream to propel the rotor blade. A circulation control is carried at a trailing edge of the blade. A trailing edge duct is carried intermediate the trailing edge and the main duct and is in fluid communication with the main duct by a partition with a plurality of orifices formed therein to bleed air from the main duct and generate a second air/gas stream therein with a pressure less than the pressure of the first air/gas stream. The trailing edge duct supplies the second air/gas stream to the circulation control.

Abstract: An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.

Abstract: A system to improve jet engine powered aircraft performance and efficiency includes a jet engine having a pressurized air port configured to convey a pressurized airflow from a compressor or a bypass fan disposed in the jet engine. A primary airfoil has a trailing edge, a top surface, and a boundary region. The system further includes a secondary airfoil disposed at a distance from the top surface of the primary airfoil. The secondary airfoil has a bottom surface and a trailing edge. An exhaust region is formed by the trailing edge of the primary airfoil and the trailing edge of the secondary airfoil. A primary airfoil ejector port and a secondary airfoil ejector port are pneumatically coupled to the pressurized air port. The primary airfoil ejector port is disposed proximate the boundary region and the secondary airfoil ejector port is disposed on the bottom surface.

Abstract: Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise.

Abstract: Provide is an anti-icing system that can cause anti-icing devices to properly operate even if a breakdown occurs in a switch after a pilot sets the switch. An anti-icing system of the present invention that controls operations of anti-icing devices provided in an aircraft includes: operation mode selecting means that selects an operation mode of the anti-icing devices; and control means that controls the operations of the anti-icing devices according to the operation mode selected by the operation mode selecting means. The operation mode includes at least a manual mode, an automatic mode, and a stop mode, and the control means controls the operations of the anti-icing devices in the automatic mode if detecting that a breakdown occurs in the operation mode selecting means when the manual mode or the stop mode is selected by the operation mode selecting means.

Abstract: A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.

Abstract: A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated.

Abstract: A diffuser assembly is provided herein. In certain embodiments, the diffuser assembly may include an outer boundary member and an inner boundary member, with the inner boundary member being positioned radially inward of the outer boundary member. The diffuser assembly also may include an exhaust flow path defined between the outer boundary member and the inner boundary member. Further, the diffuser assembly may include at least one flow deflecting member operatively attached to the outer boundary member. The flow deflecting member may be adjustable about the outer boundary member to produce a substantially uniform velocity distribution within the exhaust flow path.

Abstract: Disclosed are methods and systems for controlling spread and/or depth in a geophysical survey. An embodiment discloses a submersible deflector, comprising: an upper portion comprising an upper fin section and upper foils disposed below the upper fin section, wherein at least one slot is defined between the upper foils; and a lower portion coupled to the upper portion and disposed below the upper portion, wherein the lower portion comprises a lower fin section and lower foils disposed above the lower fin section, wherein at least one slot is defined between the lower foils. Also disclosed are marine geophysical survey systems and methods of performing geophysical surveys.

Abstract: A method for actively manipulating a primary fluid flow over a surface using an active flow control system including an active fluid flow device to provide lift enhancement and lift destruction. The method including the disposing of an active fluid flow device in the surface. The active fluid flow device is then operated to generate at least one of a steady blowing secondary fluid flow, a pulsed secondary fluid flow or an oscillating secondary fluid flow. While flowing the primary fluid over the surface to create a primary flow field, a secondary fluid flow is injected in an upstream direction and substantially opposed to the incoming primary fluid flow. The injecting of the secondary fluid flow in this manner provides for influencing of the primary flow field by manipulating a momentum of the secondary fluid flow to influence the incoming primary fluid flow and resultant lift.

Abstract: An example method of aircraft engine control includes detecting a difference between a temperature detected by a first temperature sensor and a temperature detected by a second temperature sensor. Anti-icing activity is initiated in response to the difference.

Abstract: A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes.

Abstract: A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.