Aerodynamic performance of high-turning supercritical compressor profile

The geometry characteristic and the aerodynamic performance of a 2D compressor profile with 60° turning angle under the high subsonic inlet condition is investigated by numerical simulation method. The effect of the geometry characteristics, including inlet curvature of the camber, position of the maximal thickness and value of the maximal thickness on the aerodynamic performance, is concluded by the comparison of the profile with different geometry conditions. Finally, an analysis of the fluid field on the profile is made while the profile keeps the low loss at high inlet Mach number above 0.83. The loss mechanism and the flow field characteristics are summarized. Results show that the flow with a higher turning angle and inlet Mach number can be realized by the profile formation method. The main loss source comes from the interaction between the shock and the boundary layer.