Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude

Based on characterizations of the structure and aerodynamic stability, the experimental investigation on the inlet total pressure distortion of the middle-bypass ratio turbofan engine at high altitude was carried out. The detailed available distortion project designs, distortion installations selection, and data processing standard were introduced. The test results showed that within the range of flight height less than 14 km, the height affected the steady state comprehensive distortion index a little. When flight height was 11km, and flight Mach number was 0.8, under the comprehensive distortion index less greater than 12%, the middle-bypass ratio turbofan engine could work steadily at military cruising regime and military climbing regime with air bleeding, and power extractions was 136 kW, when the flight height was 14 km, and flight Mach number was 0.39.