Plasma actuators are all electrical devices capable of altering flow paths and preventing separated boundary layers. The application to low pressure turbine stages in axial turbine engines offers further fuel eficiency improvements at low Reynolds numbers. Validated against wind-tunnel experiments, a numerical plasma model via steady-state RANS tur- bulence modeling simulations was developed. Reasonable agreement has been observed in the calibration of the numerical plasma model to experimental data. Further parametric studies are considered, aiming to optimize control, reduce pressure loss for turbine stages, and offset actuator power consumption. Results indicate that optimum flow control and positioning can prevent flow separation, reducing aerodynamic drag by 70% and offset power consumption inclusive of the actuator by up to 20 ± 4 %.