The present study investigates the effectiveness of the vortex generator with plasma actuator on NACA 23012 airfoil models. The airfoil was constructed in CATIA V5R19 software. The subsonic wind tunnel was set at the velocity of 5m/s equivalent to low Reynolds number 50 000. The plasma actuator was located at 1/3 leading-edge, 1/2 leading-edge and 1/3 trailing edge from the main wing. The 39 deg deflected flap was used to test the effectiveness of flow control devices with the presence of a triangular vortex generator and plasma actuator. The deflected flap with vortex generator attached at 20% chord gives an increment of CL by 2%, decrease CD by 1% and increase CL/CD by 5%. From the result of the analysis, the vortex generator with a plasma actuator at the location of 1/3 from trailing-edge reduced CD approximately by 2% and gave a better performance for CL/CD by almost 5 %. Overall, the vortex generator with a plasma actuator improved the aerodynamic performance by almost 5 % at a low Reynolds number.