The non-axisymmetric deviation of blade stagger angle and tip clearance has a significant impact on aerodynamic performance and stability in actual compressors. In this paper, three sets of compressor test, including the prototype with a uniform layout, as well as non-axisymmetric stagger angle and tip clearance layouts, were studied on a four-stage low-speed research compressor test rig. Experimental measurements and numerical simulations were conducted to obtain the overall performance, interstage aerodynamic parameters and non-axisymmetric properties. The test results show that the two non-axisymmetric layouts reduce compressor efficiency compared with the prototype, but the non-axisymmetric clearance layout increases the prototype stall margin by 0.67%. The reason for the numerical simulation analysis is that at the near-stall condition, when the low-energy fluid from the large clearance sector passes through the small clearance sector, the high-entropy region is decomposed and the unstable fluid is reconstructed, thus alleviating the stall characteristics. The original measurement data obtained in this paper calibrates the numerical simulation tool and provides a reference for further clarifying the actual flow field characteristics of high-pressure compressors.