Abstract
PurposeTo compute the Navier‐Stokes equations of a non‐equilibrium weakly ionized air flow. This can help to have a better description of the flow‐field and the wall heat transfer in hypersonic conditions.Design/methodology/approachThe numerical approach is based on a multi block finite volume method and using a Riemann's solver based on a MUSCL‐TVD algorithm. In the flux splitting procedure the modified speed of sound, due to the electronic mode, is implemented.FindingsA good description of the shock standoff distance, of the wall heat fluxes and of the peak of electron density number in the shock layer.Research limitations/implicationsThe radiative effects are not included in this paper. For the very high Mach numbers, this can modify the shock layer parameters.Practical implicationsThe knowledge of the wall heat transfer in the re‐entry body problems.Originality/valueThe building of a robust numerical code in order to well describe hypersonic air flow in high Mach numbers.
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