Review and assessment of turbulence models for hypersonic flows

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Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown (2015, methodology): “Since this value is not known, it has to be estimated using the turbulent recovery factor (White 2006; Roy & Blottner 2006), rturb ∼ (Pr)1/3 ∼ 0.9.”
Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3 (2011, methodology): “…value is not known from the simulation, but it can be estimated using the recovery factor for turbulent flow of air over a flat plate (White 1991; Roy & Blottner 2006): rturb = T aw − T e T 0 − T e ≈ (Pr)1/3 ≈ 0.9, (3.12) where T 0 is the so-called stagnation temperature, i.e. the temperature an…”