SU2 and OpenFOAM validation for high lift configuration using HLPW5 cases

Running Computational Fluid Dynamics (CFD) simulations include multiple parameters that influence numerical results such as grid type and refinement level, turbulence model, solver type, numerical scheme and other elements. For studying these parameters and their influence on CFD results, NASA organized Drag Prediction Workshop (DPW) and High Lift Prediction Workshop (HLPW). These events are attended by multiple research and industry entities that collaborate to improve industrial CFD simulation by studying the effect of various parameters on results. Such studies lead to new guidelines - best practices for numerical simulation engineers around the globe that would result in best accuracy with respect to experimental data. HLPW is focusing on aircraft configurations at low speed (M=0.2) with deployed slats and flaps. The current paper follows two configurations, one of a simple aircraft without high lift devices, in order to establish grid convergence for solvers at near stall angle of attack and the second configuration featuring a deployed slat, for which experimental results are available. For these two cases custom grids where generated and RANS simulation were performed with SU2 and OpenFOAM with respect to HLPW committee guidelines and suggestions. The set of results, comprising aerodynamic coefficients, pressure coefficient and flow patterns were analysed and compared with experimental data and selected results from the mentioned workshops.