Separated flow around an airfoil with a spoiler

Abstract

When a spoiler is erected rapidly on the upper surface of a wing, it brings about a long-term reduction in lift and an increase in drag. However, it has a transient effect of increasing the lift (usually referred to as the adverse lift) on the wing due to the creation of a starting vortex shed from the tip and convected downstream of the spoiler. This thesis is devoted to a numerical study of the unsteady separated flow around an airfoil with a spoiler.