A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.

A fuselage for an aircraft. The fuselage has a control element with an integrated engine outlet. The control element is integrated at a rear end of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage. An outer wall of the control element surrounds the engine outlet wherein the engine outlet is directed towards an open rear side of the control element. The control element is connected to the fuselage such that the control element jointly the engine outlet is pivotable about a rotation axis with respect to the fuselage. The rotation axis runs transversely to a longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

A device for reducing aerodynamic disturbances in the wake of an aerodynamic profile. The device comprises a first air ejection nozzle arranged on the top side of the profile and a second air ejection nozzle arranged on the underside of the profile. A first blowing chamber is fluidically connected to the first nozzle and a second blowing chamber is fluidically connected to the second nozzle. Air supply means are configured to vary the distribution of air between said first blowing chamber and second blowing chamber. The distribution of the blown air can thus be adapted depending on the situation in which the profile is used, for example depending on the flight phase of an aircraft equipped with such a profile. Also, an aerodynamic profile, a pylon supporting a propulsion assembly for an aircraft comprising such an aerodynamic profile, and an aircraft.

A device for reducing aerodynamic disturbances in the wake of an aerodynamic profile. The device comprises a first air ejection nozzle arranged on the top side of the profile and a second air ejection nozzle arranged on the underside of the profile. A first blowing chamber is fluidically connected to the first nozzle and a second blowing chamber is fluidically connected to the second nozzle. Air supply means are configured to vary the distribution of air between said first blowing chamber and second blowing chamber. The distribution of the blown air can thus be adapted depending on the situation in which the profile is used, for example depending on the flight phase of an aircraft equipped with such a profile. Also, an aerodynamic profile, a pylon supporting a propulsion assembly for an aircraft comprising such an aerodynamic profile, and an aircraft.

A sealing system may include a bulb seal coupled to a first component and a spring coupled to a second component. The bulb seal may contact the spring to form a seal between the first component and the second component. The bulb seal may be relatively stiff when new and cause the spring to compress. The bulb seal may be relatively flexible as it ages, and the spring may cause the bulb seal to compress. The bulb seal and the spring may maintain a seal throughout the life of the sealing system. The sealing system may maintain a constant separation between the first component and the second component throughout the life of the sealing system.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.