The interaction of a laminar boundary layer with a shock wave at a Mach number M = 1.43 is studied by numerical simulation. The results obtained by direct numerical simulation are compared with the results of calculations using the Reynolds-averaged Navier–Stokes (RANS) equations supplemented with different turbulence models describing laminar–turbulent transition. The possibility of determining the position of the flow turbulence zone based on linear stability theory and the $$\mathrm{e}^{N}$$ -method is estimated. Comparison of the numerical simulation with experimental data shows that engineering RANS methods can be used to study supersonic flows in which transition to turbulence occurs in regions of shock wave–boundary layer interaction.

中文翻译：

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对可压缩分离流中层流-湍流转变的各种模拟方法的研究

通过数值模拟研究了层流边界层与马赫数 M = 1.43 的冲击波的相互作用。通过直接数值模拟获得的结果与使用雷诺平均纳维-斯托克斯 (RANS) 方程的计算结果进行比较，并辅以不同的湍流模型来描述层流-湍流转变。估计了基于线性稳定性理论和 $$\mathrm{e}^{N}$$ 方法确定流动湍流区位置的可能性。数值模拟与实验数据的比较表明，工程 RANS 方法可用于研究超音速流动，其中在激波 - 边界层相互作用区域发生湍流过渡。