Abstract
Abstract
Highlights
Wake–boundary layer interactions are common in multi-element aerofoil and turbomachinery flows
This choice of forcing source may have been inspired by the study of Pfeil & Herbst (1979), who reported that, in the case of turbomachinery studies, the global wake characteristics of blade and circular cylinder cascades were nearly the same, making it reasonable to choose the circular cylinder for the generation of the wake
It can be reasoned that, if the aerofoil height is increased, the initial interaction near the flat-plate leading edge occurs at a lower turbulence intensity and that, at some point, the non-modal forcing ceases to dominate. These results reveal the interesting transformation of the disturbance profile from modal type to non-modal type at these particular geometric and flow conditions, a hybrid behaviour not reported in any other experimental study in the literature
Summary
Wake–boundary layer interactions are common in multi-element aerofoil and turbomachinery flows. In most of the fundamental studies, the upstream wake was generated by a circular cylinder rather than an aerofoil/blade (Kyriakides et al 1999; Ovchinnikov, Piomelli & Choudhari 2006; Pan et al 2008; Coull & Hodson 2011; Mandal & Dey 2011; He, Wang & Pan 2013). This choice of forcing source may have been inspired by the study of Pfeil & Herbst (1979), who reported that, in the case of turbomachinery studies, the global wake characteristics (mean velocity profile and drag) of blade and circular cylinder cascades were nearly the same, making it reasonable to choose the circular cylinder for the generation of the wake. A detailed review of transition due to unsteady wake interactions can be found in Hodson & Howell (2005) and Durbin & Wu (2007)
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