亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
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