An aircraft having distributed fans for boundary layer ingestion is provided. In one aspect, an aircraft includes a fuselage extending between a forward end and an aft end. The aircraft includes a plurality of boundary layer ingestion fans arranged in an array. Each fan of the array is mounted to and arranged circumferentially around the aft end of the fuselage. The fans are positioned so as to ingest boundary layer airflow flowing along the fuselage. At least two fans of the array are different sizes. Each fan of the fan array is operatively coupled with an electric machine. The electric machines are operable to drive their respective fans to produce thrust. The fans of the array are independently controlled in accordance with the boundary layer suction requirements of the aircraft.

An aircraft having a fuselage with a nose and a flat tail at opposite ends and a pair of wings extending therefrom. A pair of nacelles are detachably connected to the top of respective ones of the wings to be spaced from the fuselage to establish an air flow space therebetween. Each wing-mounted nacelle includes a plurality of fans, a corresponding plurality of electric motors to drive the fans, and dividers that separate the fans from one another. Each wing-mounted nacelle also includes a pair of rotatable air inlet slats at an air intake end and a pair of rotatable air exhaust flaps at an air exhaust end that are rotated relative to one another to control horizontal propulsive thrust, thrust vectoring and thrust reversing of the aircraft. A third nacelle is mounted on top of the flat tail of the fuselage between a pair of horizontal turbo generators.

An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.

An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.

A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (r.sub.hub) to a tip defining a 100 percent span position (r.sub.tip) and a plurality of span positions therebetween (r∈[r.sub.hub, r.sub.tip]). The hub has a negative hade angle (γ) with respect to the rotational axis at an axial position coincident with the leading edge of the blades.

A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (r.sub.hub) to a tip defining a 100 percent span position (r.sub.tip) and a plurality of span positions therebetween (r∈[r.sub.hub, r.sub.tip]). A plurality of outlet guide vanes are positioned aft of the fan. An afterbody is located aft of the plurality of outlet guide vanes and which tapers to an apex having an apex angle with respect to the rotational axis of between 35 and 45 degrees.

Presented are flush-mounted fluid inlets, methods for making/using such fluid inlets, and aircraft equipped with flush-mounted air inlets for engine intake/cooling, bleed air flow, etc. A fluid inlet device is presented for improving vehicle aerodynamic performance. The fluid inlet device includes an inlet base that rigidly mounts to the vehicle, laying substantially flush with a washed outer surface across which fluid flows. The inlet base has a mouth that fluidly couples with a vehicle duct. Two sidewalls are attached to the inlet base, extending between leading and trailing edges of the inlet mouth. An inlet ramp, which is interposed between and attached to the sidewalls, projects inward at an oblique angle from the mouth's leading edge. A highlight is attached to the inlet base, projecting forward from the trailing edge towards the leading edge of the mouth. The highlight has a waveform plan-view profile and undulating outer surface.

Presented are flush-mounted fluid inlets, methods for making/using such fluid inlets, and aircraft equipped with flush-mounted air inlets for engine intake/cooling, bleed air flow, etc. A fluid inlet device is presented for improving vehicle aerodynamic performance. The fluid inlet device includes an inlet base that rigidly mounts to the vehicle, laying substantially flush with a washed outer surface across which fluid flows. The inlet base has a mouth that fluidly couples with a vehicle duct. Two sidewalls are attached to the inlet base, extending between leading and trailing edges of the inlet mouth. An inlet ramp, which is interposed between and attached to the sidewalls, projects inward at an oblique angle from the mouth's leading edge. A highlight is attached to the inlet base, projecting forward from the trailing edge towards the leading edge of the mouth. The highlight has a waveform plan-view profile and undulating outer surface.

An example of a deflected slip stream wing system with coflow jet flow control includes a wingbox, a flap, a compressor, and a propulsor. The wingbox has a root and a tip. The flap is moveably attached to the wingbox and has a leading edge, a trailing edge, an injection opening, a suction opening, and a channel. The injection opening is disposed between the leading edge and the suction opening. The suction opening is disposed between the injection opening and the trailing edge. The channel extends from the injection opening to the suction opening. The compressor is disposed within the channel. The propulsor is disposed on the wingbox between the root and the tip. The propulsor has an off state and an on state. When in the on state, the propulsor is aligned relative to the flap such that fluid accelerated by the propulsor contacts the flap.

An example of a deflected slip stream wing system with coflow jet flow control includes a wingbox, a flap, a compressor, and a propulsor. The wingbox has a root and a tip. The flap is moveably attached to the wingbox and has a leading edge, a trailing edge, an injection opening, a suction opening, and a channel. The injection opening is disposed between the leading edge and the suction opening. The suction opening is disposed between the injection opening and the trailing edge. The channel extends from the injection opening to the suction opening. The compressor is disposed within the channel. The propulsor is disposed on the wingbox between the root and the tip. The propulsor has an off state and an on state. When in the on state, the propulsor is aligned relative to the flap such that fluid accelerated by the propulsor contacts the flap.