With advances in computing power and Computational Fluid Dynamics (CFD) algorithms, the complexity of CutCell based simulation models has significantly increased. In this study three dimensional numerical simulations were carried out for steady incompressible flow around an airfoil shape. The authors extended their previous work on more complex geometries; a NACA-23012 wing with 20 percent C Clark Y flap was used for this study. The boundary layer thickness, mesh expansion ratio, and mesh density variation parameters were examined. The skin friction coefficient vanishes where the flow separation starts. Although there is no experimental data available to compare the simulation work the results can be subjected to future work experimentally.

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