The Spalart and Allmaras turbulence model has been implemented in a finite volume code using an implicit finite difference technique. A wide range of turbulent flows have been computed to validate the implementation and numerical results are shown. A special attention is paid to hypersonic applications. A hypersonic wind tunnel flow, a Mach 5 flow over a hollow-cylinder-flare and a Mach 6.8 flow over a hyperboloid-flare have been considered. The critical comparison between the numerical results and experimental data has given useful elements to evaluate the model behaviour in high speed flow modeling.
Validation of the Spalart-Allmaras Turbulence Medel for Application in Hypersonic Flows / Paciorri, Renato; Dieudonne, W.; Degrez, G.; Charbonnier, J. M.; Deconinck, H.. - In: AIAA PAPER. - ISSN 0146-3705. - (1997). (Intervento presentato al convegno 28th AIAA Fluid Dynamics Conference tenutosi a Snowmass Village (Colorado - USA) nel June 29- July 2 1997).
Validation of the Spalart-Allmaras Turbulence Medel for Application in Hypersonic Flows
PACIORRI, Renato;
1997
Abstract
The Spalart and Allmaras turbulence model has been implemented in a finite volume code using an implicit finite difference technique. A wide range of turbulent flows have been computed to validate the implementation and numerical results are shown. A special attention is paid to hypersonic applications. A hypersonic wind tunnel flow, a Mach 5 flow over a hollow-cylinder-flare and a Mach 6.8 flow over a hyperboloid-flare have been considered. The critical comparison between the numerical results and experimental data has given useful elements to evaluate the model behaviour in high speed flow modeling.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
