Near-wall, Reynolds-stress model calculations of transonic flow configurations relevant to aircraft aerodynamics

The present work focuses on the application of two near-wall, wall-normal free, second-moment closure (SMC) models in the RANS (Reynolds-Averaged Navier–Stokes) framework in computing the (compressible) transonic flow past aircraft configurations and their elements (airfoils and wings). The flow geometries considered in this work include the transonic RAE 2822 profiles (cases 9 and 10), the ONERA M6 wing and the DLR-ALVAST wing-body configuration. The model results are analysed and discussed in conjunction with an available experimental database and the results of two widely used eddy-viscosity-based models, the one-equation Spalart–Allmaras model [Spalart, P.R., Allmaras, S.R., 1994. A one-equation turbulence model for aerodynamic flows. La Recherche Aérospatiale 1, 5–21] and the two-equation k–ω model of Wilcox [Wilcox, D.C., 1988. Reassessment of the scale-determining equation for advanced turbulence models. AIAA Journal 26, 1299–1310]. The SMC predictions show encouraging results with respect to the shock position, shock-affected flow structure and the strength of the wing-tip vortex.