An experimental study of a 2D square prism with two rounded front edges is described. The purpose of the study, performed at roughly 10% full scale Reynolds number is to reduce the aerodynamic drag by means of Active Flow Control (AFC) of boundary layer separation. Highly efficient suction and pulsed blowing (SaOB) actuators array is installed inside a circular cylinder that forms the upper-front curved edge of the model, simulating one of the side-front-edges of a cab. In addition and for simplicity, steady suction is applied at the other rounded corner, both with corner radius to cab width ratio of 0.127. Both oscillatory blowing and steady suction are aimed to inhibit the separation from the front edges. The experimental results show complete suppression of separation, significant decrease in the form-drag, narrowing of the wake and a corresponding increase in the base pressure with the application of AFC. Overall system efficiency is also considered. Future studies will focus on higher Reynolds numbers lower radius corner geometries to improve the usefulness of cab designs.