Haoran YAN

DOI Number: N/A

Conference number: HiSST-2025-210

In this study, a modified polar curve method is proposed by incorporating the internal structure of the detonation wave. The result shows that the modified method can address planar and asymmetric ODW reflection, shock wave/detonation wave interactions, and dual solution domain issues. Secondly, it is found that behind the reflected wave and ahead of the expansion fan generated at the wedge trailing edge, the combustion zone, reverse reaction zone, and expansion zone coexist. The shape of the slip line (SL) is found to be more complex than that in typical shock wave flow fields. By adjusting the location where the expansion/shock wave acts, it is shown that this complex flow behavior can affect both the height of the Mach stem (MS) and the stability of the dual solution domain. Finally, the formation mechanisms of the different flow regions are analyzed, and the effects of chemical reactions on flow parameters and SL deflection are investigated.

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In Categories: 1.Events, 1.HiSST 2025, High-Speed Aerodynamics and Aerothermodynamics with application to hypersonic regimes
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