| 摘要 |
An aircraft swept wing which provides pitch stability during stall conditions. In a swept wing aircraft which has leading edge flaps which in their deployed position forms a slot between the slot and the leading edge portion of a fixed main wing structure, the configuration of said leading edge portion is varied spanwise to vary the localized aerodynamic pressure spanwise along the wing. Increased bluntness of said leading edge portion, or increased slot-gap width, creates a stall condition on an inboard portion of the wing which approximates, at increasing angles of attack, the lift and pitching moment changes simultaneously experienced on outboard portions of the wing. As a result, adverse nose-up pitching moment under stall conditions is avoided, and improved pitch stability is achieved in swept wing aircraft, without compromising maximum lift capability.
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