| 摘要 |
An extendable leading edge (20a,20b) for the fuselage (12) and wings (14) of an aircraft (10) is disclosed. The leading edge (20a,20b) may be extended from a retracted position adjacent to the fuselage (12) and wings (14) to an extended position. In the extended position, the leading edge (20a,20b) increases lift of the aircraft (10) at low speeds. In the retracted position, gaps associated with the leading edge (20a,20b) are avoided.
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