Figure 10


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Comparison of the modelled Reynolds stresses and the results of a wall resolved LES. Plotted in wall-normal direction on the suction side of a NACA 64418 airfoil. The used values for the scaling tensor Sij are S11 = 0.8, S22 = 0.55, S33 = 0.65 and S12 = 0.3. The area where the ALF is applied is indicated in blue.

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