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首页> 外文期刊>Journal of Fluid Mechanics >On unsteady boundary-layer separation in supersonic flow. Part 1. Upstream moving separation point
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On unsteady boundary-layer separation in supersonic flow. Part 1. Upstream moving separation point

机译：关于超音速流中的非稳定边界层分离。第1部分。上游移动分离点

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This study is concerned with the boundary-layer separation from a rigid body surface in unsteady two-dimensional laminar supersonic flow. The separation is assumed to be provoked by a shock wave impinging upon the boundary layer at a point that moves with speed Vsh along the body surface. The strength of the shock and its speed Vsh are allowed to vary with time t, but not too fast, namely, we assume that the characteristic time scale t Re~(-1/2)/V_w~2. Here Re denotes the Reynolds number, and Vw = Vsh is wall velocity referred to the gas velocity V∞ in the free stream. We show that under this assumption the flow in the region of interaction between the shock and boundary layer may be treated as quasi-steady if it is considered in the coordinate frame moving with the shock. We start with the flow regime when V_w = O(Re ~(-1/8)). In this case, the interaction between the shock and boundary layer is described by classical triple-deck theory. The main modification to the usual triple-deck formulation is that in the moving frame the body surface is no longer stationary; it moves with the speed V_w = V_(sh). The corresponding solutions of the triple-deck equations have been constructed numerically. For this purpose, we use a numerical technique based on finite differencing along the streamwise direction and Chebyshev collocation in the direction normal to the body surface. In the second part of the paper, we assume that 1 V_w O(Re~(-1/8)), and concentrate our attention on the self-induced separation of the boundary layer. Assuming, as before, that the Reynolds number, Re, is large, the method of matched asymptotic expansions is used to construct the corresponding solutions of the Navier-Stokes equations in a vicinity of the separation point.
机译：这项研究涉及在二维非定常层流超声速流动中从刚体表面的边界层分离。假定该分离是由冲击波在沿身体表面以速度Vsh移动的点处撞击边界层引起的。允许冲击的强度及其速度Vsh随时间t变化，但不要太快，即我们假设特征时间标度t Re〜（-1/2）/ V_w〜2。在此，Re表示雷诺数，并且Vw = Vsh是壁速度，指自由流中的气体速度V∞。我们表明，在此假设下，如果在随冲击运动的坐标系中考虑冲击和边界层之间相互作用区域中的流动，则可以将其视为准稳态。我们从V_w = O（Re〜（-1/8））时的流动状态开始。在这种情况下，冲击层和边界层之间的相互作用通过经典的三层理论来描述。对常规三层甲板配方的主要修改是，在移动框架中，车身表面不再固定;它以V_w = V_（sh）的速度运动。三层甲板方程的相应解已通过数值构造。为此，我们使用基于沿流方向的有限差分和沿垂直于体表的方向的契比雪夫搭配的数值技术。在本文的第二部分，我们假设1 V_w O（Re〜（-1/8）），并将我们的注意力集中在边界层的自感应分离上。像以前一样，假设雷诺数Re大，则采用匹配渐近展开法在分离点附近构造Navier-Stokes方程的相应解。

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