An experimental study was performed on a 2D square prism with one rounded front edge with the purpose of reducing the aerodynamic drag by means of active flow control of boundary layer separation. Highly efficient suction and oscillatory blowing (SaOB) actuators were installed at the front curved edge, aimed to inhibit the separation phenomenon. The experimental results show significant decrease in the form-drag, narrowing of the wake and correspondingly an increase in the base pressure in the presence of the SaOB actuation. The mechanism of drag reduction is elimination of the separation from the front-cured edge of the model.