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In this study three dimensional numerical simulations were carried out for steady incompressible flows around complex airfoil shapes. NACA-0012 and NACA-23012 wing with 20 percent-c Clark Y flap were used for this study. This work shows that the CutCell mesh method has the ability to generate high quality mesh which captures the details of the viscous boundary layer.

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 created for steady incompressible flow around airfoil shape. The NACA-0012 airfoil was used for this study. Boundary layer thickness, mesh expansion ratio, and mesh density variation parameters were investigated. Drag and lift coefficients were compared to experimental data. Use of the CutCell method results in a good agreement between CFD results and experimental data.