부산대학교 도서관

A computational model has been implemented that is capable of accurately predicting the flow patterns around a vortex generator. The aim in development was the resolution of small-scale flow features. By observing the progression of the vortex structure along the wing, the causes of flow separation could be ascertained. It was found that flow separation occurred when the vortex structure produced by the generators broke down. This caused a localized flow separation that, at high angles, extended to cause globalized separation and generator engulfment. The computational fluid dynamics model was tested with a wind tunnel model and found to accurately describe the aerodynamic characteristics of the wing in the unstalled and lightly stalled condition. It was found that the severity of stall, experienced by wings fitted with ramp-type vortex generators, is largely due to a feedback loop mechanism that is created by the flow being drawn through the generators by attached trailing flows. An additional consequence of this was the increase in sensitivity to Reynolds number of the wing, resulting from the addition of vortex generators. Results indicate that the knowledge of these effects could be successfully applied to other wing profiles and designs.