Huijun GAO, Zhi hui WANG

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00175

Shear and compression are basic effects in fluid motions. For the new-generation near-space hypersonic vehicles, the flow and heat transfer in the wing-rudder-body interaction region have the characteristics of strong shear and compression simultaneously, resulting in severe local heat flux increment, as a great challenge for thermal protection techniques. A phenomenological decomposition method based on heat transfer mechanisms is proposed, to explain the reason why heat flux is highly increased in these regions. Generalized Rayleigh Flow is established as a theoretical flow model to quantitively illustrate the origin of the heat flux increment. Analytical results for the relative heat flux increment are derived for different angles of attack and the Mach number of freestream. Direct simulation Monte Carlo method is employed to validate the theoretical results. This paper provides a new physical understanding of the aeroheating mechanisms of hypersonic shear-compression flows and is proven to have the potential application value for more complex flows similar to their physical process.

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In Categories: 1.Events, HiSST 2024, Hypersonic Fundamentals and History
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