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978-3-8439-3540-1, Reihe Ingenieurwissenschaften
Numerical investigation of crossflow transition control using plasma actuators
144 Seiten, Dissertation Universität Stuttgart (2018), Softcover, A5
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.