[sigfridovalentino]

Hello everyone,
I've recently started some CFD simulations in OpenFOAM 10, but I'm facing some problems with drag and lift coefficient calculation.
I'm basically using Openfoam's simpleFoam Airfoil 2D NACA0012 tutorial and have reproduced the conditions described here:https://www.openfoam.com/documentati...l-2d-resources. Inside the controlDict file I inserted the functions to calculate the drag and lift coefficient, but the values ​​obtained do not match the experimental data (https://turbmodels.larc.nasa.gov/NAC...on_expdata.dat), for example, using the configuration described in the first link, for an angle of attack of 0° I get cd=1.69e-02 instead of 0.809e-02.
There are similar discussions on the forum, but despite having tried what had been recommended to others (lowering the solver tolerances, increasing the number of iterations, checking the initial conditions several times, ...) it didn't work. What's strange is that this and other tutorials (like the rhoSimpleFoam airfoil one) don't give me results comparable to those of the experimental data.
You can find all the files in this repository of mine: https://github.com/sigfridovalentino/airfoil2dnaca0012
Thank you all