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Interaction theory of hypersonic laminar near-wake flow behind an adiabatic circular cylinder

机译：绝热圆柱体后高超声速层流近尾流的相互作用理论

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The separation and shock wave formation on the aft-body of a hypersonic adiabatic circular cylinder were studied numerically using the open source software OpenFOAM. The simulations of laminar flow were performed over a range of Reynolds numbers () at a free-stream Mach number of 5.9. Off-body viscous forces were isolated by controlling the wall boundary condition. It was observed that the off-body viscous forces play a dominant role compared to the boundary layer in displacement of the interaction onset in response to a change in Reynolds number. A modified free-interaction equation and correlation parameter has been presented which accounts for wall curvature effects on the interaction. The free-interaction equation was manipulated to isolate the contribution of the viscous-inviscid interaction to the overall pressure rise and shock formation. Using these equations coupled with high-quality simulation data, the underlying mechanisms resulting in Reynolds number dependence of the lip-shock formation were investigated. A constant value for the interaction parameter representing the part of the pressure rise due to viscous-inviscid interaction has been observed at separation over a wide range of Reynolds numbers. The effect of curvature has been shown to be the primary contributor to the Reynolds number dependence of the free-interaction mechanism at separation. The observations in this work have been discussed here to create a thorough analysis of the Reynolds number-dependent nature of the lip-shock.
机译：使用开源软件OpenFOAM对高超声速绝热圆柱体的分离和冲击波形成进行了数值研究。在自由流马赫数为5.9的雷诺数（）范围内进行层流模拟。通过控制壁边界条件可以隔离体外粘性力。观察到，与边界层相比，体外粘滞力在响应雷诺数变化的相互作用开始位移中起主要作用。提出了一种修正的自由相互作用方程式和相关参数，该方程解释了壁曲率对相互作用的影响。操纵自由相互作用方程式以分离粘性-无粘性相互作用对整体压力上升和冲击形成的贡献。使用这些方程式并结合高质量的模拟数据，研究了导致唇冲击波形成的雷诺数依赖性的潜在机理。在广泛的雷诺数范围内进行分离时，已经观察到相互作用参数的常数值，该常数代表由于粘性-不粘稠相互作用而引起的压力上升的一部分。曲率的影响已被证明是分离时自由相互作用机理的雷诺数依赖性的主要因素。这里讨论了这项工作中的观察结果，以对口感的雷诺数相关性质进行全面分析。

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