Item description

3D simulation of airflow around NACA airfoil 0012

Airfoil is referred to the section of everybody that is in the air. The airfoils you see in the figure are sections that are used for the wing of the aircraft or in the locomotive blades. Here we are going to examine technical and professional information about Airfoil. The front part of the airfoil is called the edge of attack, and it’s the first contact with air, it’s delicate and sensitive to design. The end portion is called the trailing edge and it is like a sharp edge. At the end of this place, the air reaches the upper and lower parts.

In this analysis, it has been tried to simulate and analyze the airflow around the 3-dimensional Airfoil NACA 0012 using Ansys Fluent software.

Geometry and Mesh

The geometry for this analysis was generated by Ansys Design Modeler software, meshing for this analysis was also generated by Ansys Meshing software. The cell type used in this analysis is unstructured. The total number of cells produced for this geometry is 4924012.


In this analysis, an equation has been used to determine the flow around the airfoil, using the Spalart-Allmaras Viscosity Model. This model is used to analyze the strain/Vorticity-Based function better. Density-Based solver has been used, therefore it is necessary to solve the energy equation with the equations of momentum and continuity.

Boundary Condition

The flow input for this analysis is defined as the Pressure Far-Field and its value is 73048 Pa relative to the air at the temperature of 283.24 K. The rest of the walls around the domain of the solution are considered Symmetry.

Discretization of equations

In this analysis, the Explicit algorithm is used for the formulation and discretization of equations. The flow equation is discretized as Second Order Upwind.

The results are presented as velocity contours as well as streamlines.

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