High-lift device for an aircraft

Details High-lift device for an aircraft High-lift device for an aircraft

B - Operations, Transporting

64

C

B64C 9/24 (2006.01) B64C 9/22 (2006.01)

Patent

CA 2565897

An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when the high-lift device is in the deployed position, air may flow through an opening (7) in the wing (2) and over the aerofoil surface. During flight, air preferably flows into the boundary layer (13) on the upper surface of the wing (2). This energises the boundary layer (13), aft of the trailing edge of the drooped leading edge flap increasing its stability allowing the maximum achievable lift coefficient to be increased and hence reducing aircraft take-off and approach speeds.

L'invention concerne un aéronef comprenant un aile (2) définissant une surface portante, l'aile (2) comprenant un bec de bord d'attaque basculant (1) pouvant passer d'une position repliée à une position déployée. L'aile (2) est conçue pour que, en vol, lorsque le dispositif hypersustentateur est en position déployée, l'air puisse circuler par une ouverture (7) située dans l'aile (2), par dessus l'extrados. En vol, l'air circule de préférence dans la couche limite (13), sur l'extrados (2). Ce phénomène alimente la couche limite (13), derrière le bord de fuite du bec de bord d'attaque basculant, ce qui permet d'améliorer la stabilité, d'augmenter le coefficient de portance et de réduire les vitesses de décollage et d'approche de l'aéronef.

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