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Gap-induced transition via oblique breakdown at Mach 6

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Abstract

It is well known that hypersonic boundary-layer transition is sensitive to a surface roughness since the roughness may either trigger an early transition or delay the transition. Hypersonic transition is still poorly understood as there are a very limited number of studies in the literature. In the present work, we conduct a computational study on the transition process of a hypersonic Mach 6 flow over a flat plate with a gap. An implicit large eddy simulation approach based on the flux reconstruction/correction procedure via a reconstruction method is used to investigate the interaction between the hypersonic boundary layer and a gap. Flow structures with and without the gap are compared to analyze the local skin friction coefficient overshoots before and after the gap. Two inlet angles of attack are investigated. The evolution of the skin friction coefficient shows that the gap has a very limited influence on the oblique transition at a zero angle of attack. In contrast, the gap can trigger an early transition at a negative angle of attack. In this case, the transverse feedback mechanism is believed to be the main cause, which amplifies the broadband instability waves.

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Acknowledgements

The first author acknowledges the support by the Tsinghua Scholarship for Overseas Graduate Studies and thanks the University of Kansas (KU) for hosting her visit to KU. This work is also partly supported by NSFC Grant 11572176.

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Authors and Affiliations

  1. School of Aerospace Engineering, Tsinghua University, Beijing, 100084, China

    Y. Xue, L. Wang & S. Fu

  2. Department of Aerospace Engineering, University of Kansas, Lawrence, KS, USA

    Z. J. Wang

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  1. Y. Xue
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Correspondence to S. Fu.

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Communicated by C.-H. Chang.

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Xue, Y., Wang, L., Wang, Z.J. et al. Gap-induced transition via oblique breakdown at Mach 6. Shock Waves 29, 1181–1190 (2019). https://doi.org/10.1007/s00193-019-00926-y

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