Applications of Cartesian CutCell Method for Incompressible Flow on High Lift Devices

Along with the progress in computing capability and Computational Fluid Dynamics (CFD) algorithm development, the complexity of simulation models which can be analyzed has increased. The largest task in model development is mesh generation for the domain geometry; often very time consuming and therefore expensive activity. The engineer is often forced to compromise between merely an easily achievable level of accuracy and an increased level of accuracy obtainable at greater cost and time expenditure but with the promise of increased performance. Mesh generation has become a bottleneck.;In order to shorten product design time, engineers need to create high quality meshes around complex geometries within a few days or hours. Newer automated meshing techniques have been published in order to tackle this need and the CutCell is one of them. The current study is focused on the effect of different CutCell meshing strategies on the accuracy of aerodynamic performance predictions. The Cartesian method can be described as a methodology in which CutCells are applied to the geometry utilizing a process involving rectangular/hexagonal cells on a regular lattice cutting through the geometry.;In this work the CutCell numerical method approach was validated utilizing two aircraft wing models, NACA-0012 and NACA-23012 with a 0.2C Clark Y flap, in three dimensional viscous steady incompressible flows. The results used for the validation are lift and drag coefficients. The effect of the boundary layer thickness (inflation), mesh expansion ratio, and mesh density variation are also investigated.;The results for the NACA-0012 airfoil shape are computed using two models namely the 2-equation k-o SST (Shear-Stress-Transport) and the 3-equation k-kl-o. The results obtained for a NACA-23012 with 0.2C Clark Y flap-airfoil shape are computed using the one-equation S.A. (Spalart-Allmaras) and 2-equation k-o SST models. The outcomes obtained for the applications using the turbulent models are in a fair agreement with experimental data. The results of this work indicate that CutCell Meshing method is a promising method that can be used for the accurate prediction of aerodynamic coefficients.