Transition mechanisms in hypersonic wind-tunnel nozzles: a methodological approach using global linear stability analysis
Base-flow computations and stability analyses are performed for a hypersonic wind tunnel nozzle at a Mach number of 6. Isothermal and adiabatic wall boundary conditions are investigated, and moderate stagnation conditions are used to provide representative scenarios to study the transition in quiet...
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| Hoofdauteurs: | , , , , , |
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| Formaat: | Artigo |
| Taal: | Inglês |
| Gepubliceerd in: |
Cambridge University Press
2025-01-01
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| Reeks: | Flow |
| Onderwerpen: | |
| Online toegang: | https://www.cambridge.org/core/product/identifier/S2633425925100330/type/journal_article |
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