This paper presents a numerical investigation of active flow control cases conducted on the flap leading edge of a three-component high-lift configuration. A numerical method solving the unsteady Reynolds averaged Navier Stokes equations (URANS) is applied, combined with a numerical actuation boundary condition. Based on previous results, which have shown that the lift can be significantly enhanced by synthetic jet excitation, the effects of three-dimensionality are assessed. The influence of the spanwise width of the actuation segments is investigated, as well as the effect of varying the actuation angle. The active flow control mechanism is applied at a Reynolds number of Re = 750 000. As a test model, the industrially relevant Swept Constant Chord Half Model is used.
Numerical investigation of spatially distributed actuation on a three-element high-lift configuration
2010
15 Seiten
Conference paper
English
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