Abstract
A theoretical and an experimental analysis was performed to determine the effect that the wing geometry and the boundary layer on the lower surface of the wing have on the trailing rolled-up tip vortex. Model test results are presented for the vortex structure downstream of wings of varying aspect ratio and taper ratio. The geometry and strength of the rolled-up tip vortices were measured over a range of lift coefficients. In general, it was found that the strength of the vortex is less than one would predict on the basis of the midspan circulation about the wing. Conclusions are given with regard to the size and strength of a vortex as they relate to the wing aspect ratio, taper ratio, and lift coefficient.
Published Version
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