The paper presents experimental and numerical studies on the rotating disturbance at near-stall condition in a low-speed axial compressor rotor with large tip clearance. The distributions of casing pressure and its fluctuation, and unsteady flow fields downstream of the rotor are analyzed. The experimental results are compared with those of small tip clearance case, and show notable differences in the flow field at near-stall condition between the two tip clearance cases. In the case of large tip clearance, the region with high pressure fluctuation appears on the pressure side near the rotor leading edge. In addition, at the downstream of the rotor, the region with high turbulence intensity is found near the casing wall. The experimental results suggest that the spiral-type vortex breakdown should occur in the tip leakage vortex. Since the spiral-type vortex breakdown has an unsteady nature, the tip leakage vortex fluctuates with time inside the rotor passage, interacting with the pressure surface of the adjacent blade, which produces the unsteady phenomena in the flow field. The numerical study has been conducted. The simulation shows that the vortex breakdown leads to the rotating disturbance, generating the asymmetric flow field in the compressor rotor.