According to the basic theory of aerodynamic stability and engineering experience

an aero-engine

for example

aerodynamic stability design method in the whole flight envelope was presented on the basis of GJB/Z 224-2005

and some experimental verification were performed.The results show that stability margin required of fan and compressor is larger at high-altitude and low-speed state

stability margin required of fan is larger at right boundary of the engine envelope and basically remains the same

affected by the nozzle subcritical

stability margin required of fan is larger during landing.Therefore

these conditions should be focused in the engine design and use.Engine should be designed to ensure that the stability margin available of fan and compressor is greater than the stability margin required.The design method can effectively meet the demand for complex engineering development.