[jp3g12]

Hello,

I am new to OpenFOAM (I have been using it for about two weeks now) and I decided to start learning the software by trying to simulate a simple case such as a NACA 0012 airfoil at an angle of attack of zero degrees. The specification of the problem can be found here: http://turbmodels.larc.nasa.gov/naca0012_val.html

I used the mesh they provide (I converted it to OpenFOAM format using pointwise).

I have been working for a number of days on this problem without much success. I have attached the residuals and the force coefficients. As it can be seen, the lift is pretty much converged after 6000 iterations. However, I have been experiencing difficulties with drag convergence. In essence, it is going down but it is taking forever to do so! Moreover, the residuals are not that great either (ignore the xlabel, the number of iterations should be 6000).

I am not sure what is wrong with my set up. I stumbled upon this thread http://www.cfd-online.com/Forums/ope...t-airfoil.html and I modified some of the files on the system folder accordingly but it did not help with convergence of results.

I suspect there may be a mistake or something wrong with the settings on the 0 folder. As I said, I am new to OpenFOAM and I am not used to this environment at all. I am using the Spalart-Allmaras. I have attached the system folder and the 0 folder, and perhaps someone can take a look and tell me possible mistakes or things you would do differently. On the nuTilda folder I am using a value that is suggested by Spalart and Rumsey for external aerodynamics calculations based on the velocity that I am using (52 m/s -- Reynolds number = 6,000,000). Spalart and Rumsey suggest a value of nuTilda/nut = 3.

Any help is very much appreciated, especially if someone has attempted the same NASA problem before!

Thank you very much for the help,

JP