For subsonic

supersonic and transonic axial-compressors

comprehensive explanation was made for the low reaction aerodynamic design principle of the aspirated compressor stages.The specific implementation form of this principle was put forward

while the application conditions and mutual interactions between aerodynamic parameters

such as twist speed and axial velocity

were analyzed.For subsonic axial-compressors

the diffusion factor could be reduced by increasing the rotor exit axial velocity or by enlarging the positive pre-swirl of the rotor entrance flow.For transonic or supersonic axial-compressors

the flow in the rotor could attain large turning efficiently by increasing the axial velocity after the entrance shock.The specific value of the outlet axial velocity could be chosen depending on the rotor efficiency and the requirements of the entrance Mach number and absolute flow angle of the downstream stator.At last

the progresses made on this design principle were summarized.