DYNAMICS OF CONTROLLED BOUNDARY LAYER SEPARATION

The results of experimental study on a boundary layer separation control are given in the paper. The boundary layer on a flat wall is subjected to adverse pressure gradient. Three control strategies have been chosen for the study, both passive (rough wall, vortex generator) and active (synthetic jet). The separation process is investigated using TR-PIV method. Dynamical aspects of the phenomenon are analyzed in details. Experimental setup The blow-down aerodynamic rig of IT has been used for the experiment. The test section for generation of adverse pressure gradient in channel was designed and manufactured. In Fig. 1 the schema of experimental setup is shown. The section A represents the starting point of adverse pressure gradient region as well as the origin of the streamwise position coordinate x. The cross-section in A position is 100 x 100 mm2. Downstream of this section, the upper wall is inclined with angle α = 16°, while the bottom plane wall is used to study the boundary layer separation. To prevent separation from the upper wall, this is permeable and aspirated. The section B represents the “mean” position of a boundary layer separation (please note, that the separation point is not stable). Fig. 1 – Schema of the experimental setup A