This report summarizes the work accomplished as part of a conceptual design study to investigate the application of advanced composite materials to the wings of Navy aircraft. A baseline aluminum wing was designed to serve as the baseline for comparison of the composite designs. The composite concepts studied were based upon the metal baseline structural arrangement. Each of the composite systems was investigated for each of the structural components. The wing which showed the greatest weight saving used graphite/epoxy for wing skins, ribs and a large portion of the spars. The concept of using a graphite/epoxy skin over a conventional aluminum structure is attractive from both the cost and weight savings standpoints.


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