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。
2
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。
3
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.