Flow structure of supersonic flow past backwardfacing step with perpendicular injector
Flow structure of supersonic flow past backwardfacing step with perpendicular injector
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DOI：
10.2514/6.1998-939
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发表时间：
1998-01
期刊：
影响因子：
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通讯作者：
A. Matsuo;M. Mizomoto
中科院分区：
文献类型：
--
作者：
A. Matsuo;M. Mizomoto
在二维理想气体条件下，数值研究了带垂直引射器的后台阶超声速绕流结构。来流马赫数为2.5，喷流为音速喷流，位于台阶后24mm处。计算中考察了台阶高度（0，2，3，6mm）和射流与主流动压比（0.0，0.2，0.4，0.6，0.8，1.0）。当引射器足够远以使主流恢复超声速时，引射与后向台阶的影响无关。然而，射流与台阶后面的回流相互作用，回流区扩展到射流。当回流区扩大时，回流区高度与动压比成钟形关系。当回流区高度大于台阶高度时，台阶拐角处的膨胀波转变为压缩波。当台阶高度为6mm时，流场出现非定常振荡。在数值模拟中阐明了振荡的机制。
Flow structures of supersonic flow past a backward-facing step with perpendicular injector are numerically investigated under the perfect gas condition in two-dimensional space. The incoming main flow is Mach number 2.5 and the injection is sonic jet, located 24mm behind the step. A step height (0, 2, 3, 6mm) and dynamic pressure ratio of the jet flow to the main flow (0.0, 0.2, 0.4, 0.6, 0.8, 1.0) are examined in the calculations. When the injector is far enough for the main flow to recover supersonic, the injection is independent of the effect of the backward-facing step. However, the jet interacts with the recirculation behind the step, the recirculation region expands to the jet. Once the recirculation region expands, the height of the recirculation region is clocsely related with the dynamic pressure ratio. The expansion waves from the step corner change to the compression wave when the height of the recirculation region becomes higher than the step height. For the step height 6mm, the unsteady oscillation appears in the flowfields. The mechanism of the oscillation is numerically clarified in the simulations.