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。
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。
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。
Mixed convection heat transfer in open-ended enclosures was studied numerically for two different inlet angles of attack.
研究了两种不同外界来流方向的开口方腔内的混合对流换热问题。
By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensional inlet are superior to frontal inlet.
对不同布局的总压恢复系数进行比较，颌下及两侧进气则较头部进气有好的攻角特性。
By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensional inlet are superior to frontal inlet.
对不同布局的总压恢复系数进行比较，颌下及两侧进气则较头部进气有好的攻角特性。
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