A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

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.

A fluidic device for providing analogue output control includes a main channel, a first control channel, a second control channel, a comparator which receives respective input fluid flows from the main, the first and the second control channels. The first control channel is configured such that the input fluid flow therefrom carries an oscillating pressure wave signal, the second control channel includes a flow regulator controllable to vary the mass flow rate of the input fluid flow from the second control channel, and the main channel is configured such that the input fluid flow therefrom is at a reference mass flow rate. The comparator is configured such that the input fluid flows from the first control and the second control channels act in combination on the input fluid flow from the main channel to produce an output fluid flow from the comparator having a PWM mass flow rate characteristic.

Aspects of the disclosure are directed to a nacelle of an aircraft, comprising a surface that is profiled such that during cruise flight operation lines of constant static pressure of a boundary layer around the nacelle in a given region are substantially contained within a plane that is normal to an engine axis.

An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described.

An aircraft includes a fuselage body extending in a front-rear direction; a tail wing at a rear portion of the fuselage body in the front-rear direction; a main wing in front of the tail wing in the front-rear direction on the fuselage body; and a fan device on an outer surface of the fuselage body. The fan device includes a rotor shaft outside the outer surface of the fuselage body, a rotor blade on an outer side of the rotor shaft in a rotor radial direction with the rotor shaft as a center, a housing fixed to the fuselage body, extending in the front-rear direction, including respective openings at a front and a rear in the front-rear direction, and provided to cover the rotor shaft and the rotor blade, a stator blade.

A system includes a surface, an actuator, and processing circuitry. The surface includes one or more non-actuating zones and one or more actuatable zones. The actuator is configured to a flow property of a fluid that flows over the one or more actuatable zones of the surface. The processing circuitry is configured to obtain a value of a parameter of the fluid that flows over the surface, and operate the actuator to adjust the flow property of the fluid that flows over the one or more actuatable zones based on the value of the parameter of the fluid.

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.

A gas turbine engine anti-icing system troubleshooting method comprising providing an anti-icing system comprising a bleed air source coupled to a pressure regulating valve set having an upper valve coupled end-to-end in series with a lower valve; and an air pressure sensor coupled to the pressure regulating valve set downstream of the pressure regulating valve set; detecting at least one valve fault; checking the upper valve for the at least one valve fault; checking the lower valve for the at least one valve fault; deactivating at least one of the upper valve and the lower valve; and replacing at least one of the upper valve and lower valve.