The instant invention generally relates to a forwardly swept wing (10) for an aircraft comprised of a pair of opposed single piece machined aluminum alloy wing boxes (20 and 40). Specifically, the invention provides for a forward swept wing construction utilizing known in the art computer numerical control machining techniques to produce an aluminum allow wing (10) having an integral edge (24) thereby greatly reducing assembly time. A plurality of integral stiffeners (80) oriented at a forwardly swept angle of approximately 12 to 13 degrees between forward and rear spars (62 and 64, respectively) provides for a wing (10) that minimizes the effects of aeroelastic divergence.
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