Luigi CUTRONE, Francesco CASCONE, Antonio SCHETTINO

DOI Number: N/A

Conference number: HiSST-2025-280

The prediction of boundary-layer transition in hypersonic flows is a critical challenge in aerodynamic design, influencing heating rates, skin friction, and overall vehicle performance. The transition process, governed by a complex interplay of instability mechanisms, is particularly relevant for atmospheric entry capsules and hypersonic vehicles, where accurate modeling is essential for thermal protection system (TPS) design. Moreover, in high-enthalpy conditions, the boundary-layer stability is strongly influenced by chemical and thermal non-equilibrium phenomena, including wall catalysis. To address these complexities, this study evaluates intermittency-based transition models within the Reynolds-Averaged
Navier-Stokes (RANS) computational fluid dynamics (CFD) framework, incorporating non-equilibrium effects to improve transition prediction.

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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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