Abstract— The results of numerical simulation of the interaction between a shock and the laminar boundary layer on a flat plate in motion in supersonic perfect-gas flow at Mach number М ∞ = 3 are considered. The shock is preassigned using the Rankine—Hugoniot boundary conditions, which corresponds to a shock wave produced by a wedge with a given semi-vertex angle in an inviscid gas flow. The simulation is based on the numerical solution of the time-dependent, two-dimensional Navier—Stokes equations by time marching to steady state. The numerical results are verified by means of comparing the results for separation flow past a flat plate at rest with experimental data. The numerical data are used to investigate the effect of the plate velocity of the separation flow structure and the basic laws governing the problem. It is shown that the motion of the plate downstream diminishes the separation zone length, whereas the opposite motion leads to its increase.

中文翻译：

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运动平板上激波与边界层相互作用的数值模拟

摘要— 考虑了马赫数 М ∞ = 3 下超音速完美气流中激波与运动平板上层流边界层相互作用的数值模拟结果。冲击是使用 Rankine-Hugoniot 边界条件预先指定的，它对应于由具有给定半顶角的楔形物在无粘性气流中产生的冲击波。模拟基于时间相关的二维 Navier-Stokes 方程的数值解，通过时间推进到稳态。通过将通过静止平板的分离流的结果与实验数据进行比较来验证数值结果。数值数据用于研究分离流动结构的板速度的影响和控制问题的基本规律。