Vortex leading edge flap assembly for supersonic airplanes

Details Vortex leading edge flap assembly for supersonic airplanes Vortex leading edge flap assembly for supersonic airplanes

1995-12-26

1997-10-28

Kashnikow, Andres

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244218, 244219, B64C 350

Patent

active

056810130

ABSTRACT:
A leading edge flap (16) for supersonic transport airplanes is disclosed. In its stowed position, the leading edge flap forms the lower surface of the wing leading edge up to the horizontal center of the leading edge radius. For low speed operation, the vortex leading edge flap moves forward and rotates down. The upward curve of the flap leading edge triggers flow separation on the flap and rotational flow on the upper surface of the flap (vortex). The rounded shape of the upper fixed leading edge provides the conditions for a controlled reattachment of the flow on the upper wing surface and therefore a stable vortex. The vortex generates lift and a nose-up pitching moment. This improves maximum lift at low speed, reduces attitude for a given lift coefficient and improves lift to drag ratio. The mechanism (27) to move the vortex flap consists of two spanwise supports (24) with two diverging straight tracks (64 and 68) each and a screw drive mechanism (62) in the center of the flap panel (29). The flap motion is essentially normal to the airloads and therefore requires only low actuation forces.

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