Abstract
Time-accurate numerical solutions is obtained for equations modeling turbulent subsonic flows over a slender ogive-cylinder body of revolution in the high-angle-of-attack regime where a large asymmetry in the mean flow is observed experimentally. A modified algebraic eddy-viscosity turbulence model is utilized to correctly compute the effects of the asymmetric vortices on the underlying viscous layers. To reproduce any one of the experimentally observed asymmetric flowflelds, it is necessary to add a small geometrical disturbance near the body apex
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