An experimental investigation was performed to study the three-dimensional flow structures and interactions of a finite-span synthetic jet (located near the tip on the wing) with the flow over a finite and swept back wing (cross-sectional profile of the NACA 4421, AR = 4, sweep angle of 30°), at a Reynolds number of 10~5 and two angles of attack, 0° and 9°. Three blowing ratios of the jet were considered, 0.8, 1.2 and 2. SPIV data were collected at multiple 2-D planes, which were then used to reconstruct the flow volume. The effect of the blowing ratio was analyzed based on the three-dimensional flow field using time-averaged and phase-averaged statistics. The study showed that the flow field in the vicinity of the synthetic-jet orifice becomes highly three-dimensional and is governed by the streamwise structures that are associated with the finite span of the jet (edge vortices). The presence of a spanwise boundary layer over a swept wing enhances the development of three-dimensional flow structures, where the interaction domain and the secondary flow structures are less pronounced at α = 9° than at 0° due to the increased velocity and pressure gradient in the vicinity of the synthetic jet.
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