Abstract
The laminar breakdown in a swept-wing-generic, three-dimensional boundarylayer flow has been investigated by highly accurate direct numerical simulations under manifold conditions, including steady or unsteady crossflow modes, transitioncontrol scenarios, or late transition in the region of adverse pressure gradient. The work presented has been performed within the scope of the project “Numerical investigations of the spatial development of pulse-like disturbances in a swept-winglike boundary layer” as part of the national priority research program “Transition”, in the subgroup on “Transition mechanisms”. This paper represents a summary of the main results gained within the project.
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