Abstract
An interactive zonal method for the numerical simulation of viscous transonic airfoil flows with passive shock control is presented. The approach is based on a global viscous-inviscid interaction procedure including a local shock boundary layer interaction solution. The predicted shock control effects on the airfoil characteristics result not only in wave and viscous drag reductions but also in a lift increase. The results show that the transonic performance of a typical supercritical airfoil can be substantially improved by a passive shock control device consisting of a perforated surface with a cavity underneath. Furthermore, it is demonstrated that a perforation with inclined holes is more effective than that with normal ones.
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