Abstract
By means of spatial direct numerical simulations (DNS) based on the complete Navier-Stokes equations the effect of three-dimensional discrete suction on the spatial development of a laminar boundary-layer flow generic for the front part of a swept-back airliner wing has been investigated. The baseflow is an accelerated Falkner-Skan-Cooke boundary layer, on a swept wedge with semi-opening angle of 45° (Hartree parameter β H = 0.5) which is mainly characterised by crossflow instability. The simulations of the microscale phenomena confirm that 3-d suction at the wall can excite unstable crossflow disturbances that have to be minimised by using either slot arrays or hole arrays with high porosity, otherwise the stabilising (2-d) effect of suction is compromised. Premature transition through oversuction could be identified as a convective secondary instability of the flow field deformed by strong steady crossflow vortices emerging from the suction panel.
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