Experiments were conducted to explore the use of fluidic oscillators for improving the aerodynamic performance of the S903 airfoil. The tests were conducted at chord Reynolds numbers ranging from 4 x 105 to 1 x 106 in the Low-Speed, Mid-Size Tunnel at the Pennsylvania State University. The improvement in lift coefficient range from 10% to 20% and depends on the Reynolds number and the actuation level. It was observed that the higher the oscillator jet velocity with respect to the free stream velocity, the higher the gain in aerodynamic performance at a given Reynolds number. It was also observed that the gain in maximum lift was nearly constant for varying Reynolds numbers if the ratio of jet velocity to the free stream velocity is kept constant. Numerical simulations were performed to study the effect of frequency of actuation for a given velocity ratio and to better understand the physics of the flow control mechanism involved.