Rotordynamic effects caused by nonaxisymmetric rotor-tip clearance in an axial compressor stage have been analyzed. Two coupled actuator discanalyses are carried out at blade (meridional plane )andradius(radial plane ) scales. Continuity, axial, and tangential momentum equations are used to connect upstream and downstream e ows across the compressor stage, and a small perturbation analysis is used to obtain e owe eld nonuniformities. Predictions indicate the following. Relative to the passage e ow, the e ow associated with the rotor-tip clearance is axially retarded and tangentially underturned. Furthermore, the compressor blades near the smaller tip gap are more highly loaded. Thus, the tangential force asymmetry promotes a backward whirl. However, the pressure asymmetry causedbyazimuthal e ow redistribution inducesa forwardwhirl. Thenetresultis abackward-whirling force whose magnitude is much smaller than that of the forward-whirling force found in turbines.