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Study on the Terminal Shock Wave/Boundary Layer Interaction within a High Offset Supersonic Inlet

  • Oct 11, 2020
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Proceedings of ‏The 3rd International Conference on Modern Research in Engineering, Technology & Science

Year: 2020

DOI:

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Study on the Terminal Shock Wave/Boundary Layer Interaction within a High Offset Supersonic Inlet

He-xia Huang, Zhong-qi Luo, Jia Cai and Zhi-xiang Xiao

 

ABSTRACT: 

In this paper, a three-dimensional high-offset supersonic inlet is designed, and the terminal shock wave/boundary layer interaction of this inlet in critical and subcritical conditions is numerically investigated. The results show that in the critical state, a “λ” shock wave and a separation zone are generated near the lip, and the low-energy fluids at the first bend of the diffuser section flow, affected by the pressure gradient, will accumulate on the lower wall, thus forming a larger recirculation zone. In the subcritical state, there will be a backflow phenomenon at the symmetry plane adjacent to the entrance of the diffuser section, and the separation zone caused by interaction is smaller on both sides and larger in the middle.

Keywords: Three-dimensional High-offset Supersonic Inlet, Terminal Shock Wave/Boundary Layer Interaction.