Optimized Global Resolvent Analysis to Improve Plasma Actuator Control over the Airfoil Surface

This study explores the impact of a single dielectric-barrier discharge (SDBD) plasma actuator on the flow characteristics over a NACA0015 airfoil, focusing on the effects of varying forcing heights and frequencies. Using large-eddy simulation (LES) validated against experimental data, global resolvent analysis was integrated with spectral proper orthogonal decomposition (SPOD) to optimize the alignment between LES snapshots and resolvent response modes. Findings reveal that plasma actuator excitation below the response mode peak enhances trailing vortex structures, improving flow control. The study demonstrates that lower forcing frequencies and optimal plasma heights significantly enhance aerodynamic performance by reducing flow separation and improving lift-to-drag ratios. These insights contribute to developing more efficient active flow control strategies for applications in aircraft and wind turbine performance enhancement.