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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An experimental Study of a two dimensional inlet model in non-uniform supersonic flow are presented.

介绍一种二元进气道模型在非均匀超音来流中的初步研究结果。

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There is a difference between the numerical simulation results of two-dimensional and three-dimensional flow field in supersonic inlet, which shows the influence of boundary layer on the side wall.

超声速进气道的三维流场数值模拟结果与二维数值模拟结果存在较明显的差别，说明进气道侧壁附面层的影响不容忽略；

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