By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensionalinlet 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。
2
An experimental Study of a twodimensionalinlet 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。
3
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.