A simplified procedure is presented for the design of a symmetrical wing-body fairing. The design aims at optimizing the design of the fairing, which is to serve the double purpose of eliminating the separation near the wing body junction, as well as minimizing leading edge contamination of the laminar wing. The design optimization procedure is based on the analysis of the viscous-flow performance of a fairing of prescribed geometry. First, a panel method is used to determine the inviscid flow around the fairing. This is then followed by an integral-method calculation of the boundary layer development on the attachment line along the body and the fairing, so only in the symmetry plane of the flow. As an application a fairing was designed for a straight NACA0015-wing mounted on a flat plate. Tests in the wind tunnel confirmed the effectiveness of the fairing.
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