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；

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.

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对超声速冲压发动机进气道—喉道段进行了二维稳态流场数值模拟，给出了反压与攻角变化对冲压发动机进气道起动状态影响的数值模拟结果。

The prevailing software numerically simulates a 2-D internal steady flow of the ramjet inlet-isolator; the numerical simulation results of the state of start in the ramjet inlet are presented.

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