Abstract
In this paper, validation and assessment of various turbulence models are performed in transonic flows, including an algebraic Baldwin Lomax model, Spalart Allmaras one equation, and two equation (k-e, k-ω and SST k-ω) turbulence models. The NACA 0012 airfoil has been chosen for the turbulence model validation studies. The three test cases selected here included both attached and separated transonic flows. This study shows that the five turbulence models provide satisfactory results for transonic attached flows. However, all models, fail to predict the location of the shock correctly when a strong shock and a shock induced flows separation are present. Compared to other models, it has been shown that the SST k-ω model is the most robust model in the prediction of lift coefficient for all cases. Computed results are performed with the CFD-FASTRAN code by using the fully implicit scheme for time integration, and the upwind Roe flux difference splitting scheme for space discretization augmented by a high order Min-Mod limiter to damp spurious oscillations and to allow for sharp shock resolution
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