par Paciorri, Renato;Dieudonné, Walter;Degrez, Gérard 
;Charbonnier, Louis-Marie ;Deconinck, Herman
Référence Journal of spacecraft and rockets, 35, 2, page (121-126)
Publication Publié, 1998-03
;Charbonnier, Louis-Marie ;Deconinck, Herman Référence Journal of spacecraft and rockets, 35, 2, page (121-126)
Publication Publié, 1998-03
Article révisé par les pairs
| Résumé : | The Spalart-Allmaras turbulence model has been implemented in a finite volume code using an implicit finite difference technique. First, the implementation was validated on flat plate turbulent boundary-layer flows under various flow conditions. Then, three high-speed flow applications characterized by different turbulent phenomena were considered to investigate the behavior of the Spalart-Allmaras model in the hypersonic regime, namely, a hypersonic wind-tunnel flow, a Mach 5 flow over a hollow-cylinder flare, and a Mach 6.8 flow over a hyperboloid flare. Numerical results were found in excellent agreement with experimental data for the attached nozzle flow and the hyperboloid flow involving laminar separation and turbulent reattachment. For the hollow-cylinder flare configuration, which involves turbulent separation, the magnitudes of surface pressure and of heat transfer peaks were correctly predicted, whereas their positions were slightly incorrect due to the underprediction of the separation bubble size. |
