two-dimensional inlet 二维进气道
three-dimensional inlet 三元进气道
three-dimensional sidewall inlet 三维侧压式进气道
two-dimensional supersonic inlet 二元超声速进气道
three-dimensional sidewall hypersonic inlet 三维侧压式高超声速进气道
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。
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。
And three-dimensional sidewall compression inlet with 25 percent cowl position has high mass capture and total pressure recovery coefficient and isolator exit flow flied is homogeneous.
整流罩位置为25%的三维侧压进气道可以获得较高质量捕获和总压恢复系数，且隔离段出口流场比较均匀。
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