A generic rectangular blown wing model (17.8 cm chord, and 45 cm span) that can rotate 360
◦ along spanwise axis equipped with a control surface and a propeller is studied experimentally to define the optimum propeller position to recover the generation of pitching moment. Particular interest is given to the moment generation capability at high angles of attack with big flap deflections. A flap is placed in the mid-section of the wing, submerged in the propeller slipstream. Flow separation around the wing model is investigated using Digital Particle Image Velocimetry (DPIV) method with simultaneous force and moment measurements. The blown wing is considered both at static angles of attack and in a transition from 0
◦ to 90
◦, and 90
◦ to 0
◦ . The results provide a better understanding of the lift-drag-moment equilibrium, flow separation from the upper surface of the wing and the flap, and additionally the control reversal limits during reverse flow.