A test program has been conducted to study tip leakage flows associated with cantilevered stator blades in axial flow compressor systems. A low-speed single-stage test rig has been developed to simulate flows characteristically found in middle-stage axial flow compressors. The test rig is designed specifically to accommodate flow visualization techniques in the study of cantilever stator blade tip leakage flows. Extensive testing demonstrates that the test rig simulates axial compressor stage performance characteristics. Data taken include both onand off-design operating conditions. Data reduction and analysis of high-speed film footage provides actual tip leakage path lines and velocities for four different tip treatments. The tip treatments investigated are baseline (no tip treatment), pumping groove, double winglet, and pressure side winglet. Of the four tip treatments tested, the pumping groove proved to be the most effective in reducing tip leakage.