| 摘要 |
A tilt wing VTOL aircraft has an upper wing with a leading edge, a trailing edge, an inboard area adjacent the fuselage, spaced opposite end tip areas and an upper surface. The wing is pivotally mounted on the fuselage for rotation from a cruise position in which the upper surface of the wing is flush with the upper surface of the fuselage to a hover position in which the wing is perpendicular to the upper surface of the fuselage. The wing has a forward portion in the leading edge of the inboard area affixed to the fuselage and cut out of the wing and an aft portion in the trailing edge of the inboard area affixed to the fuselage and cut out of the wing. Thus, when the wing is in its cruise position it is whole, including the forward and aft portions, whereas when the wing is in its hover position it has a forward cutout at its leading edge in the inboard area corresponding to the forward portion and an aft cutout at its trailing edge in the inboard area corresponding to the aft portion so that the spanwise wing lift distribution is diminished when the wing is in a position other than its cruise position. The forward and aft cutouts produce a vortex along the sides of the fuselage which results in the spanwise wing lift distribution being diminished when the wing is in a position other than its cruise position. This vortex increases the wing tolerance to angle of attack and thus reduces the requirement for propeller bending of the air flow during mid-transition speeds. It also reduces the intensity of center section buffet.
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