Described and illustrated is a wing (3) for an aircraft (1), comprising a main wing (7) and a wing tip device (9), wherein a front blade (21) and a rear blade (27) of the wing tip device (9) extend away from an attachment end (19) in a diverging manner, wherein a front blade leading edge (23) extends in front of a rear blade leading edge (29) and a front blade trailing edge (25) extends in front of a rear blade trailing edge (31), when viewed in a chord direction (33), wherein at a front blade tip (35) the front blade (21) extends under a different dihedral angle (v) than the rear blade (27) at a rear blade tip (37), wherein the front blade leading edge (23) and the front blade trailing edge (25), as well as the rear blade leading edge (29) and the rear blade trailing edge (31) all have a tangent-continuous developing. The object of the present invention, to provide a wing for an aircraft, wherein for a predetermined span dimension the induced drag can be significantly reduced, is achieved in that the front blade leading edge (23) extends tangent-continuously with the wing leading edge (11), and the rear blade trailing edge (31) extends tangent-continuously with the wing trailing edge (13), and the front blade trailing edge (23) at least partially extends behind the rear blade leading edge (29), when viewed in the chord direction (33).
A WING FOR AN AIRCRAFT, AND AN AIRCRAFT COMPRISING SUCH A WING
FLÜGEL FÜR EIN FLUGZEUG UND EIN FLUGZEUG MIT EINEM DERARTIGEN FLÜGEL
AILE D'UN AÉRONEF ET AÉRONEF COMPORTANT UNE TELLE AILE
2018-07-25
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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