On the Direct Computation of the Flow Field Developing Around NACA 0012 Airfoil at Moderate Reynolds Number

Abstract

The main of aim this work is to enable a previously developed solver to computations involving turbulent flows. Hence, the flow field developing around a NACA 0012 at Re = 5 ∙ 104, M = 0.4, α = 5° is adopted as benchmark. In this work we mainly address the correct definition of simulation settings in order to accurately capture the more relevant aerodynamic features of the aforementioned flow problem. Thus, all the results deriving from the iterative grid generation process are carefully described and discussed.