Numerical investigation of crossflow transition control using plasma actuators
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Beschreibung
The applicability of dielectric barrier discharge (DBD) plasma actuators to delay the laminar-to-turbulent transition in swept-wing-type boundary-layer flows has been investigated by direct numerical simulations.
Three different methods using plasma actuators have been examined in detail to control the laminar breakdown induced by steady crossflow vortices: Base-flow manipulation, direct attenuation of nonlinear crossflow vortices, and upstream flow deformation. For all three methods it has been shown that a significant transition delay can be achieved, however with differing efficiency. The transition delay yields a reduction of the skin friction and hence lowered aerodynamic drag.
Autor*in
Philipp Dörr
Themen in »Numerical investigation of crossflow transition control using plasma actuators«
Transition to turbulence Crossflow vortices Plasma actuators