Abstract
A computational investigation of the impact of wing tip mounted engine nacelles was undertaken in order to quantify potential improvements in performance and reductions is wake vortex strengths as had been identified in previous wind tunnel tests by Patterson, et al. The results obtained indicated that the bulk of the performance gains are associated with the diameter of the wing tip body and not with the presence of axial flow in the tip vortex core. However, the tip vortex strength is reduced by such core flow and forced core blowing does enhance the viscous dissipation of the vortex. The possibility still exists to effect the tip vortex stability through blowing, but vortex breakdown was not observed in the computational analysis.
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