An actuator disc type of analysis is carried out to determine the effect of a nonuniformity in the circumferential velocity profile entering an axial flow stage of turbomachinery. The analysis is restricted to study of incompressible, inviscid flow with the assumption of hub/ t ip ratios close to unity reducing the problem to two dimensions. Expressions are derived giving the attenuation of the velocity distortion through the stage, the circumferential shift in the profile, and the fluctuation in load felt by the rotor blades passing through the nonuniform velocity field, all as a function of stage geometry. Results are given for compressor, turbine, and free wheeling stages as a function of wheel speed, stage loading, and mean stagger angle. General conclusions and design recommendations are made with respect to minimizing blade load fluctuation and optimizing distortion attenuation.