Abstract
The present work aimed at numerical simulation of a two-dimensional, incompressible and steady-state airflow over a NACA0015 airfoil with flap and Gurney flap using the standard turbulence models k-epsilon, k-omega and versions of these models with modified constants. All meshes used were structured. Comparison of the results of the turbulence models with experimental data from the literature shows differences between the results in the leading-edge region. The differences were minimized by adjusting the contents of the turbulence models. For validation, the k-epsilon turbulence model with modified constants was used in a new simulation of a profile (NACA0012), which agrees with several experimental studies; however, it does not show better results.
Highlights
The numerical simulation of flows is called computational fluid dynamics (CFD)
Other ways to simulate a flow with turbulent properties include mathematically modeling the smaller scales and solving for the larger turbulence scales (LES) or even fully modeling the turbulence scales, providing a way to circumvent the random properties of turbulence by relating them to average conditions and obtaining their time average after simulation [4].The use of turbulence models has its efficiency proved in several areas in engineering, having their results validated by experimental data
Numerical fluid dynamics was applied to an external, two-dimensional, incompressible subsonic airflow on an airfoil (NACA 0015 with flap and Gurney flap) in a structured mesh using k-epsilon and k-omega turbulence models
Summary
The numerical simulation of flows is called computational fluid dynamics (CFD). The use of this tool is based on the numerical solution of the conservation equations, since no general analytical answers for these equations are known, except for very simplified flows, which generally have limited application in engineering [1]. The size of the computational domain and the distribution of elements in sufficient density and concentrated in regions of high property gradient were studied to obtain answers that are independent of the mesh. This means that the domain is dimensioned so that the velocities at a very small distance from the boundary conditions practically all have the same value, and that from this point on there is no more disturbance of the flow by the obstacle (the airfoil), so that an optimal domain is created. Another hypothesis adopted for the methodology is that each turbulence model has its optimal domain, so the verification becomes necessary for each model. The differences in the regions marked A and B are highlighted
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