Need Help in generating Lift and Drag coefficients over airfoil (2D)
 

Hi guys,
I am doing simulation of an airfoil (naca23012) in OpenFoam and my task is to compare the Drag and Lift coefficients of the simulation to the real experimental data adjusting the velocity.
It has taken me countless attempts in order to get to the point in the files attached. The basic problem that I am having right now is that I am using the "Force" and "ForceCoeffs" function in order to generate the .dat file for post-processing. But unable to do so.

If I involve the function in the controlDict then the error I get is error of unable to find the value of rho

Need your help guys.
P.S The attached file has the function in controlDict "Disabled" making it comment.

Didn't review your case file, but it sounds a lot like this issue (see Tobi's response)

https://www.cfd-online.com/Forums/op...tml#post626241

Hi,
Thanks for the link this pretty much solves the existing problem. Will bother you if something else comes up :P