Aircraft comprising a device for reducing the induced drag
View Patent ↗An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.
1. An aircraft comprising:
a longitudinal fuselage;
at least two side wings connected symmetrically to opposite sides of the fuselage;
at least one engine nacelle fixed to each side wing by an engine support pylon; and
at least one profiled lifting member disposed on each of the engine support pylons along a crestline of each of the engine support pylons, and a base of the at least one profiled lifting member attached to a top surface of the engine support pylons, so as to generate a propulsive resultant force under action of an oblique air flow.
2. An aircraft according to claim 1 , wherein the at least one profiled lifting member extends from an end fixed to the engine support pylon, departing from the end in an extension direction inclined by at least 30° relative to the top surface of the side wing in question.
3. An aircraft according to claim 1 , wherein the at least one profiled lifting member is disposed along the longitudinal direction of the engine support pylon at a distance, from a part of the pylon fixed to the side wing, of between 10% and 70% of a local chord of the wing.
4. An aircraft according to claim 1 , wherein the at least one profiled lifting member includes a wetted area and an extension dimension or height, measured from one end of the member fixed to the engine support pylon, the wetted area and the height being in an area-to-height ratio of between 1 and 4.
5. An aircraft according to claim 1 , wherein the at least one profiled lifting member includes a wetted area that is adjusted as a function of gain in desired drag reduction and of general dimensions of the aircraft.
6. An aircraft according to claim 1 , wherein the at least one profiled lifting member includes a free end opposite an end fixed to the engine support pylon, the free end being oriented toward downstream relative to an upstream position of the fixed end, thus conferring on the member an inclination toward downstream in a longitudinal direction.
7. An aircraft according to claim 1 , wherein the at least one profiled lifting member has a shape of a fin.
8. An aircraft according to claim 1 , wherein the at least one profiled lifting member includes a wall defining an internal duct for evacuation of a fluid flow, the duct communicating, at one end, with an interior of the engine support pylon from which the fluid flow originates and, at a distance from that end, with at least one aperture implemented in the wall of the member and discharging to the outside of the member.