Abstract
A design method is presented whereby the flow separation in the wing-fuselage juncture of aircraft is eliminated by the use of a leading-edge fillet. The design method uses a design rule that relates a change in skin friction to a change in surface slope. After determining the current skin friction distribution on the plate ahead of the leading edge of the wing, a target skin friction distribution that will eliminate flow separation is calculated. Using the design rule, the current skin friction distribution is moved toward the target distribution by extending the leading edge of the wing to form a leading-edge fillet. The new leadingedge fillet is then analyzed by the flow solver and the process is iterated until convergence is achieved. Nomenclature
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