Abstract
Forward swept wing aircraft may have superior aerodynamic performance for certain missions. Algebraic expressions to predict the static aeroelastic divergence characteristics of forward swept wings constructed of composite materials have been developed using a laminated box beam model to describe the wing structure and aerodynamic strip theory to predict the loads due to wing bending and torsional deformation. The expressions presented show that, because of elastic coupling between wing bending and torsion, wing divergence may be precluded for reasonably large forward sweep angles if the composite structure is properly tailored. The structural parameters that maximize divergence speed are readily identified. Two illustrative examples are presented. ao b
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