Typically in Hypersonic Re-entry flows of Blunt Body objects and at an angle of attack which leads to the laminar-turbulent transition in the boundary layer on the leeward side(caused by roughness) which then causes flow separation in the afterbody flow.
The transition from laminar to turbulent regime is very difficult to simulate using turbulence modelling. If a DNS is not possible, you can try the LES formulation using the dynamic modelling, the mixed model should perform better
@ Filippo Maria Denaro... Sir is there any significance of studying the Laminar-Turbulent transition in the afterbody flow of re-entry blunt body vehicles?
Have a look here
https://arc.aiaa.org/doi/abs/10.2514/1.22594?journalCode=jsr
You can try the WALE model from this paper "Subgrid-Scale Stress Modelling Based on the Square of the Velocity Gradient Tensor".
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