Airbus Operations (s.a.s.)

Airbus France

Airbus UK Limited

Airbus Operations Gmbh

Thierry Fol

Philippe Jimenez

Arnaud Namer

Cyril Bonnaud

Stephanie Dantin

Marjorie Defos

Neil John Lyons

Anne Dumoulin

Tom Gibson

Ludovic Gerard

According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.

Engine pylon for the suspension of a turbo engine under an aircraft wing

A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.

Airplane engine pylon comprising at least one protruding element to generate a vortex of the airflow

An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing.

Aircraft comprising a central fairing that adjusts the pressure on the wing structures by means of local geometric deformations

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.

Aircraft comprising a device for reducing the induced drag

The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container () is provided successively with a front portion () in the vicinity of its leading edge (), then with an intermediate portion (), and then with a rear portion () in the vicinity of its trailing edge (), said rear portion () tapering progressively in a direction going from the leading edge () of the container towards its trailing edge (). Furthermore, said rear portion () is extended by connection means () enabling the container () to be connected under the wing () in such a manner that said tapering rear portion () is partially upstream from the leading edge () of the wing ().

Method of reducing the compressibility drag of a wing, and container implementing the method

An aircraft wing arrangement including a wing and at least one strut for attaching the aircraft engine suspended under the wing and including a front zone situated projecting towards the front with respect to a leading edge of the wing. The front zone includes a lateral projection delimiting a lateral air flow channel while being projected towards a proximal end of the wing.

Growing community of inventors

Grenade, France

Thierry Fol