Abstract Shock-wave/boundary-layer interactions (SW–BLIs) play an important role in a wide range of transonic, supersonic and hypersonic applications. Fundamental studies on stationary interactions have been conducted extensively during the last 60 years. However, unsteady SWBLIs with traveling shock fronts have been little studied on canonical geometries. In the present experimental investigation, the influence of a uniformly moving impinging shock on the separated SWBLI flow is analyzed, with a freestream Mach number of 3 and a traveling Mach number in upstream direction of 0.5. To evaluate this effect, stationary reference SWBLIs have been investigated in a wide ranging study. A scaling method from the literature has been enhanced to drastically reduce the data scattering using a new approach accounting for the Reynolds number influence. The results gathered from the traveling interactions were within the spread of reference data, considering the true shock-wave Mach number of 3.5. The validity of the modified scaling approach to describe the interaction length in cases with steady and traveling shock-wave/turbulent-boundary-layer interactions is discussed. Graphic abstract

中文翻译：

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稳定和行进冲击波/湍流边界层相互作用的缩放

摘要 冲击波/边界层相互作用（SW-BLI）在广泛的跨音速、超音速和高超音速应用中发挥着重要作用。在过去的 60 年中，对静止相互作用的基础研究进行了广泛的研究。然而，关于典型几何结构的具有行进激波前沿的非定常 SWBLI 研究很少。在本实验研究中，分析了匀速运动冲击波对分离的 SWBLI 流的影响，其中自由流马赫数为 3，上游方向的行进马赫数为 0.5。为了评估这种影响，已经在广泛的研究中调查了固定参考 SWBLI。文献中的缩放方法已得到增强，使用考虑雷诺数影响的新方法显着减少了数据分散。考虑到 3.5 的真实冲击波马赫数，从行进相互作用中收集的结果在参考数据的范围内。讨论了在具有稳定和行进冲击波/湍流边界层相互作用的情况下描述相互作用长度的修正比例方法的有效性。图形摘要