A device is provided for attenuating the vortex wake created in the zone behind an aircraft, the aircraft having at least one wing and an afterbody having a strong upward asymmetrical reduction of section of the rear fuselage. The device is positioned downstream of the wing of the aircraft symmetrically relative to the longitudinal plane of the aircraft. The device includes vortex-generating aerodynamic appendages capable of being deployed between a folded-down position in which the aerodynamic appendages are folded down substantially in the direction of the fuselage, capable of switching from a folded-down position in which they are folded down substantially in the direction of the fuselage, and a deployed position calculated to generate vortex structures having an intensity and a trajectory which modify the local pressure field in order to interact with the vortex wake to attenuate it and separate the upsweep vortices from the longitudinal plane of the aircraft.
DISPOSITIF D'ATTENUATION DE SILLAGE TOURBILLONNAIRE
VORTEX WAKE ATTENUATION DEVICE
VORRICHTUNG ZUR WIRBELWALZENDÄMPFUNG
2020-04-22
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
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