This paper describes experimental and computational studies performed on a 2D Clark-Y airfoil at high angle of attack with co-flow jet flow control. The test was performed at 6.5×104 and 1.3×105 Re and conducted with three different momentum coefficients Cμ: 0.08, 0.15, and 0.51. The CFJ Clark-Y airfoil was also tested on injection only, suction only, and no jet flow conditions. The computational study of the tested cases was performed using commercial CFD software. Results show that the co-flow jet method is applicable to a thin airfoil and able to increase the lift and delay the stall angle and flow separation depending on the momentum coefficient used. The increase of lift obtained by integrating the pressure distribution ranges from up to 15% in the lowest momentum coefficient tested, to up to 100% in the highest. The results also show that CFJ Clark-Y airfoil is more effective when both injection and suction are used in comparison to using injection and suction separately.