Experimental base flow modification on a swept wing using plasma forcing

This work experimentally investigates plasma actuator (PA) forcing effects on the base flow and developing crossflow (CF) instabilities in a swept wing boundary layer. Spanwise-invariant near leading edge is configured according to modification (BFM) strategy. A simplified predictive model constructed by coupling an derived body force linear stability theory used infer characteristics of layer subject BFM. The velocity measured stereo particle image velocimetry (PIV) at various PA operating conditions. Similarly, CF instabilities, triggered through discrete roughness elements, are quantified planar-PIV. results demonstrate that can reduce component, whereas control authority shows high dependence momentum coefficient. dissimilar reduction between streamline-aligned component leads local re-orientation flow. Spanwise spectral analysis time-averaged indicates stationary be favorably manipulated BFM depend corresponding initial amplitudes instabilities. An evident spanwise shift trajectory vortices observed, which appears result from alteration due forcing. Despite overall amplitude unsteady disturbances found enhanced current shed light underlying principles BFM-based operation context laminar control.