In the present paper, we report on the results of a study that was performed as part of the program for developing a method for calculating the flow and the mass-flow-rate coefficient in narrow cylindrical bleed channels under conditions of impingement of a thick boundary layer. For setting the boundary conditions at the inlet boundary of the computational domain, we used the pressure and temperature profiles obtained at the outlet boundary of the simulation domain for the flow around the forebody of a hypersonic air inlet. Numerical modeling of the 3D flow around that forebody was carried out in the range of Mach numbers from 3 to 6 at an angle of attack of 6°. The distributions of static pressure calculated along the symmetry plane and in the transverse direction were compared with experimental data. A satisfactory agreement between the calculated and experimental data is shown. The simulation of the flow was carried out within the framework of the Reynolds-averaged stationary Navier-Stokes equations using the k-ω SST model of turbulence. The obtained distributions of flow parameters and flow streamlines have allowed us to perform an analysis of specific features of the flow structure on the forebody of the model air inlet and in a boundary-layer bleed channel. The calculations showed that, in the examined range of Mach numbers, a sonic flow in boundary-layer bleed channels could be realized to ensure a maximum rate of the mass flow of air through the channels.

中文翻译：

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流动条件对高超音速进气口前体的影响对边界层排放通道中的空气流动

在本文中，我们报告了一项研究结果，该研究结果是开发一种程序的一部分，该程序用于开发一种在厚边界撞击条件下计算窄圆柱状泄油通道中的流量和质量流率系数的方法层。为了在计算域的入口边界处设置边界条件，我们将在模拟域的出口边界处获得的压力和温度曲线用于高超声速进气口前体周围的流动。围绕前体的3D流动的数值模型是在6马赫数从3到6的迎角范围内进行的。将沿对称平面和横向计算的静压力分布与实验数据进行了比较。计算结果与实验数据之间显示出令人满意的一致性。在Reynolds平均平稳Navier-Stokes方程的框架内使用k - ωSST湍流模型。所获得的流动参数和流动流线分布使我们能够对模型进气口前体和边界层排放通道中流动结构的特定特征进行分析。计算表明，在检查的马赫数范围内，可以实现边界层排放通道中的声波流动，以确保通过通道的空气质量流的最大速率。