The global aviation industry currently faces the urgent challenge of mitigating its environmental impact by reducing pollutant emissions. One of the most effective strategies to minimize the carbon footprint of aircraft is the reduction of skin friction drag. It accounts for a significant portion of the total drag on commercial aircraft and it is intrinsically linked to the dynamics of the turbulent boundary layer. A well-established technique for drag reduction, validated by both numerical simulations and experimental studies, is spanwise wall oscillation. Despite its potential, this technique remains challenging to implement in practical applications. Consequently, this thesis represents a continuation of an ongoing characterization project, focusing on two distinct approaches to emulate this technique through plasma actuators, which were custom-fabricated via manual deposition of conductive paint over laser-cut stencils.