The inlet design calculating model was set up based on the theory of equal shock wave intensity and angle of supersonic airflow to get maximum total pressure coefficient.
以总压恢复系数最大为目标，采用等激波强度和等激波角设计方法建立进气道模型；
The inlet flow angle and diviation angle were confirmed which was applied to low cascade experiment result of American NACA, and controlled diffuser factor and flow deflection angle in design.
并应用美国NACA低速叶栅试验结果确定流入角和落后角，设计中控制扩散因子和气流折转角。
The inlet flow angle and diviation angle were confirmed which was applied to low cascade experiment result of American NACA, and controlled diffuser factor and flow deflection angle in design.
并应用美国NACA低速叶栅试验结果确定流入角和落后角，设计中控制扩散因子和气流折转角。
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