Aircraft stall deteriorates the lift force for normal flight at a specific angle of attack(AOA), and dramatically reduces the speed of airplane. A vortex generator (VG) is a useful device for retarding the aircraft stall. In this study, the vortex generator was applied to control the stall location of micro-air vehicle(MAV), and the aerodynamic characteristics at low Reynolds numbers were numerically analyzed using ANSYS FLUENT. Reference model was composed of the fixed wing, and various vortex generator configurations were used as design parameters. In order to confirm the flow characteristics, the velocity vector field and pressure distribution were calculated and the results were graphically depicted according to the angle of attack on each configuration of the vortex generator.