This paper presents flow simulation results of the DLR-F11 multi-element wing confguration, obtained with CIAM's in-house Reynolds-averaged Navier-Stokes multiblock structured mesh code Cobra, based on implicit 2-nd order in space finite-difference scheme, being updating of well known Godunov's method . This work was a part of the 2nd High Lift Prediction Workshop. In-house meshes were constructed with increasing mesh density for analysis. Comparisons between the numerical solution and available experimental results are provided.
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