Abstract
It has been shown that, using the concept of a discrete vortex filament shedding, Weissinger’s method can be modified to determine the span-wise loading for wings with a sweep discontinuity. The sweep discontinuity is modelled by the introduction of a discontinuity in the equivalent vortex pattern chosen to replace the wing. The total lift, induced drag, pitching moment coefficients and span-wise location of the centre of pressure have been found for a few wing geometries using De Young and Harper’s procedure. An increase in the outboard sweep shifts the maximum load position outboard besides decreasing the overall lift and induced drag coefficients. High suction peaks appear at the pivot.
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