Abstract
This paper gives an insight into the corner flow around a wing mounted on a flat plate. Reynolds Averaged Navier Stokes (RANS) simulations and experimental data are compared for a global Reynolds number (Rec) equal to 3 × 10 and an angle of attack of 12. The flat plate and wing boundary layers are fully turbulent and the Reynolds number based on the momentum thickness of the incident boundary layer is equal to Reθ = 2, 200. It is shown that the RANS simulation using the Spalart-Allmaras (SA) model with the Boussinesq closure predicts a massive corner flow separation while on the experimental data the separation is confined to a small area. Better predictions are obtained when resorting to the SA model with the Quadratic Constitutive Relation (QCR) closure. A comprehensive investigation of the numerical results using the experimental data is performed in order to get a better understanding of the behaviour of the SA-QCR model for the present corner flow.
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