At different attack angles, Mach Numbers and ramp angles, the numerical calculations of inner and external flow field are performed for an adjustable mixed compression inlet.

对某可调混压进气道在不同攻角、不同马赫数、不同斜板角度下进行了大量的数值计算。

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By using CFD software flow characteristics of S-shaped inlet are analyzed. Furthermore, the effect of fuselage on the inlet by means of the Angle of attack is given.

利用计算流体力学(CFD)方法分析了S形进气道的内流特性及机身对S形进气道性能的影响。

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Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.

得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。

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