Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet
Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet
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DOI：
10.24200/sci.2016.3928
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发表时间：
2016-08
期刊：
影响因子：
1.4
通讯作者：
M. Soltani;A. Daliri;J. S. Younsi
中科院分区：
文献类型：
--
作者：
M. Soltani;A. Daliri;J. S. Younsi
进行了实验，以研究轴对称混合压缩入口的各种冲击波/边界层相互作用（SBLI）。此外，在可能的情况下比较了某些实验发现并通过数值解决方案进行了验证。进行了与混合压缩入口相关的不同类型的SBLI的分类。使用Schlieren和Shadowgraph流动可视化以及不稳定的压力记录，研究了亚临界和流行条件下驱动的正常冲击波/边界层的相互作用。将数据与CFD预测进行比较。乳头唇的相互作用反映了倾斜冲击和末端正常冲击与尖峰边界层在关键和超临界作战处的相互作用，从而导致冲击序列和伪震电现象。在这种情况下，使用数值模拟结果来说明流场。实验压力记录用于验证和进一步讨论。入口中SBLI流的结构高度取决于节流值。对于接近临界的节流值，内部压缩冲击与边界层和伪震动现象的相互作用是主要的。增加入口背压会将正常冲击波从入口管中推出。还研究了由于分离的边界层与正常冲击波的相互作用而形成的Lambda休克。数值和实验结果表明，存在与超音速入口相关的不同类型的冲击波边界层相互作用。这些流相互作用现象中的每一个都对入口的稳定性和性能都有不同的影响。末端正常休克与内导管边界层的相互作用会导致伪震现象，从而导致流动失真增加和总压力恢复的减少。另外，正常冲击波与外锥边界层的相互作用会导致嗡嗡声不稳定性和降解入口性能。
Experiments were conducted to study various kinds of shock wave/boundary layer interaction (SBLI) in an axisymmetric mixed-compression inlet. Further, some of the experimental findings were compared and verified by numerical solutions where possible. A classification of different types of SBLI relevant to the mixed-compression inlets is performed. Interactions of expelled normal shock wave/boundary-layer at subcritical and at buzz condition is investigated using Schlieren and shadowgraph flow visualization as well as unsteady pressure recordings. The data is further compared with the CFD prediction. Interactions of cowl lip reflected oblique shock and the terminal normal shock with the spike boundary-layer at both critical and supercritical operations that leads to shock trains and pseudo-shock phenomena are also studied. In this case numerical simulation results were used to illustrate the flow field. Experimental pressure recordings are used for validation and further discussion. The structure of SBLI flow in an inlet depends highly on the throttling value. For near critical throttling values, interaction of internal compression oblique shocks with boundary-layer and pseudo-shock phenomenon is dominant. Increasing the inlet back pressure pushes normal shock wave out of the inlet duct. Formation of lambda shock due to interaction of separated boundary-layer with normal shock wave is also investigated. The numerical and experimental results show that there exist different kinds of shock wave boundary-layer interactions relevant to the supersonic inlets. Each of these flow interaction phenomena has different effects on the stability and on the performance of the inlet. Interaction of terminal normal shock with internal duct boundary-layer causes pseudo-shock phenomenon that leads to increase of flow distortion and reduction of total pressure recovery. In addition interaction of normal shock wave with external cone boundary-layer causes buzz instability and degrades inlet performance.