par Pinna, Fabio;Zanus, Ludovico 
;Demange, Simon ; [et al.]
Référence 2018 Fluid Dynamics Conference, AIAA AVIATION Forum, Vol. AIAA 2018-3697
Publication Publié, 2018-06-27
;Demange, Simon ; [et al.]Référence 2018 Fluid Dynamics Conference, AIAA AVIATION Forum, Vol. AIAA 2018-3697
Publication Publié, 2018-06-27
Publication dans des actes
| Résumé : | Stability and transition predictions on arbitrary hypersonic vehicle geometries require expensive calculations. In order to include transition phenomena in early preliminary design, inexpensive and relatively accurate methods should be provided. Unfortunately, the few transition prediction methods currently applied during the design phase are strongly depending on empirical correlations, with limited ranges of validity. This paper describes a novel approach to retrieve boundary layer growth rates for hypersonic flows with a small computational effort. The final goal is to reduce the existing obstacles to the application of scientifically sound transition prediction methods to industrial cases. |
