Abstract
A computational method developed to provide a transonic analysis for upper/lower surface wing-tip mounted winglets is described Winglets with arbitrary planform, cant and toe angle and airfoil section can be modeled The embedded grid approach provides high flovvfield resolution and the required geometric flexibility In particular coupled Cartesian/cylindrical grid systems are used to model the complex geometry presented by canted upper/lower surface winglets A new rotated difference scheme is introduced in order to maintain the stability of the small disturbance formulation in the presence of large spanvvise velocities Wing and winglet viscous effects are modeled using a two dimensional strip boundary layer analysis. Correlations with wind tunnel and flight test data for three transport configurations are included
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