Pressure gradient turbulent boundary layers developing around a wing section

Abstract eng:
The results of a DNS of the flow around a NACA4412 wing section at Rec = 400, 000 and 5◦ angle of attack are presented in this study. The high-order spectral element code Nek5000 was used for the simulations. The effect of a strong adverse pressure gradient (β ≃ 4.1) on the turbulent boundary layer at xss /c ≃ 0.8 is assessed, including a more prominent wake region, and steeper logarithmic and buffer layers. Increased production and dissipation are observed across the boundary layer, as well as enhanced viscous diffusion and velocity-pressure-gradient tensor close to the wall.

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