Zonal direct-hybrid aeroacoustic simulation of trailing edge noise using a high-order discontinuous Galerkin spectral element method

Topical Issue - Aeroacoustics: state of art and future trends

Open Access

Figure 10

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 S_ij 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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