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.