Implementation and Validation of the Spalart-Allmaras Turbulence Model for Application in Hypersonic Flows

The Spalart and Almaras turbulence model has been implemented in a finite volume code using a implicit finite difference technique. A wide range of turbulent flows have been computed in validation phase and numerical results are shown. A special attention is paid to the hypersonic applications. A hypersonic wind tunnel flow and a Mach 5 flow over a hollow-cylinder-flare have been considered and a critical comparison between the numerical results and experimental data is reported.