Abstract
We consider the high Reynolds number laminar flow of an incompressible fluid past a slender delta wing at incidence. The primary separation is represented by vortex sheets emanating from the leading edges. These sheets also carry a source distribution to represent viscous displacement effects. An interactive viscous-inviscid calculation is carried out to determine the secondary-separation flow properties on the wing. Agreement between the theoretical predictions and experiment is encouraging. For example, unlike the purely inviscid calculations, there is only a small pressure recovery beyond the suction peak, as is observed in experiment. Similarly the upward and inboard movement of the vortex core due to the secondary separation is in accord with experiment, as is the position of secondary separation.
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