Airfoil CFD Validation Using a NASA-provided Mesh

Created using ANSYS 14.5

Learning Goals:

In this exercise, you will learn to:

• Import mesh in plot3d format.
• Split boundaries in Fluent by creating region registers.
• Apply Spalart-Allamaras turbulence model.

Problem Specification:

Consider the same problem encountered in the main tutorial.

A tremendous amount of effort has been put into the numerical study of this case of turbulent flow around the NACA 0012 airfoil and results have been reported on the NASA site for comparison. For a more detailed description of this problem, click the link below.

http://turbmodels.larc.nasa.gov/naca0012_val.html

In this case study, we will be solving the same problem using ANSYS FLUENT version 14.5. We set the inflow angle at 10 degrees. At the end of this case study, we will compare our results with the reported results as a step for validation. Published results can be found on this page below:

http://turbmodels.larc.nasa.gov/naca0012_val_sa.html

Getting Started:

We will use the exact mesh that was used in the NASA study. The mesh grid for the flow space around the airfoil are given in the link below:

http://turbmodels.larc.nasa.gov/naca0012_grids.html

The meshing files are provided in different formats (plot3d format and CGNS format) at different meshing resolutions. In this tutorial, we will be using the medium 2d grid (449*129, 257 points on airfoil surface) in plot3d format as an example. The meshing file we will be using can be downloaded here.

Instructional Videos: