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

摘要

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 Aerospatiale 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.