par Zanus, Ludovico ;Pinna, Fabio
Référence 2018 Fluid Dynamics Conference, AIAA AVIATION Forum, Vol. 2018-3696
Publication Publié, 2018-06-27
Publication dans des actes
Résumé : Linear and weakly nonlinear stages of the laminar-to-turbulent transition process are investigated in supersonic and hypersonic flat plate boundary layers, by means of nonlinear PSE. Local thermodynamic equilibrium conditions are taken into account by proper modeling and coupling with the stability solver. Two transition mechanisms are considered: an oblique-type breakdown at Mach 3 and a secondary instability in the form of fundamental resonance at Mach 10. In the first case high temperature effects are confirmed to be negligible, while in the hypersonic regime they prove to be essential in order to reach simulation convergence and correctly reproduce the transition mechanism.