The efficiency of transonic aircraft engines depend upon the performance of compressor rotor. to increase compressor rotors performance flow separation around rotor blades must be delayed and controlled. the aim was to control the flow separation of blades using suction boundary layer control method. rotor blade has been modelled in designing software catia and then a suction surface has been created on blade and then import these geometries to ansys-cfx 14.5 for computational analysis of flow around blades. suction slot has been applied at the trailing edge of suction surface and shear stress transport model has been used for computational analysis. two different mass flow rates 1 kg/s and 1.5 kg/s have been used here and boundary layer separation effects have been changed and this could be readily seen that the velocity vectors have reattached, preventing the boundary layer separation at the suction surface of the blade. increment in pressure ratio for suction, blowing and combination of suction and blowing were 0.052, 0.09 and 0.12.