Abstract
An aerodynamic s simulation code for the Reynolds averaged Navier -Stokes (RANS) equations is developed using the spectral volu me method for unstructured tetrahedral meshes . The turbulent viscousity is modeled by the Spalart -Allmaras (SA) one -equation model. Distributions of the state variables and their gradients in each grid cell are reconstructed using piece -wise linear polynomials with a modified SV limiter near shocks and steep gradients. For time integration, the non -linear LU -SGS scheme is employed to r educe total CPU times. The developed scheme is validated for turbulent flow over a flat plate and assessed for transonic flowfield over a wing compared with availab le CFD results . Then, RANS simulation around the JAXA high -lift configuration model is perfo rmed using developed scheme. By comparing with the numerical solutions obtained by the conventional finite volume solver, we examine the accuracy and the computational cost of the present SV method. Comparisons with the available experimental data are also attempted.
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