Aircraft equipped with a device for reducing induced drag

Details Aircraft equipped with a device for reducing induced drag Aircraft equipped with a device for reducing induced drag

B - Operations, Transporting

64

C

B64C 7/02 (2006.01) B64C 1/14 (2006.01) B64C 23/06 (2006.01) B64D 29/02 (2006.01)

Patent

CA 2650194

The invention relates to an aircraft comprising 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 (18), characterized in that at least one profiled bearing rod (20; 30) is positioned on each of the engine support pylons so as to generate a propulsive resultant force under the action of an oblique air flow.

L'invention concerne un aéronef comportant un fuselage longitudinal, au moins deux ailes latérales raccordées symétriquement de part et d'autre du fuselage et au moins une nacelle de réacteur fixée à chaque aile latérale par l'intermédiaire d'un mât de support de réacteur (18), caractérisé en ce qu'au moins un corps portant profilé (20 ; 30) est agencé sur chacun des mâts de support de réacteur, de façon à générer une force résultante propulsive sous l'action d'un écoulement d'air oblique.

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