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I don't believe you will able to solve the problem in one step. I'm not an expert in aerodynamics, but it seems you will have to run FlOTRAN first (the ansys fluids package) to determine the pressure distribution across the wing surface. The pressure distubution can then be applied to your structural model composed of beam44 or beam189 elements for the spars and stringers, and shell63 elements for the sheet metal panel componets of the wings.
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