The paper presents the results of a numerical study of gas dynamics and integral parameters of the flow at the channel entrance located behind a conical or plane shock wave. The freestream Mach number range is M = 2–4 and the range of the angles of the compression surfaces of the wedge and cone is δ= 10–90°. Data on the flow structure at the channel entrance, mass-averaged Mach numbers, total pressure loss coefficient, and flow rate coefficients are obtained. A comparative analysis of these parameters is performed, and the advantages and drawbacks of the channel entrance positions in various types of the flow are noted.

中文翻译：

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流入圆锥形或平面冲击波后面通道的气体动力学数值模拟

本文介绍了对圆锥形或平面冲击波后面的通道入口处的气体动力学和流动积分参数进行数值研究的结果。自由流马赫数范围为 M = 2–4，楔块和圆锥体压缩表面的角度范围为δ = 10–90°。获得了通道入口处的流动结构、质量平均马赫数、总压损失系数和流量系数的数据。对这些参数进行比较分析，指出各种流型中通道入口位置的优缺点。