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

jingow · December 17, 2016, 01:46

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.

gkarlsen · December 17, 2016, 09:12

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

Problem calculating forces on blades 2 (for finding forces)

jingow · December 17, 2016, 11:34

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

December 17, 2016, 09:12		#2
gkarlsen Member Geir Karlsen Join Date: Nov 2013 Location: Norway Posts: 59 Rep Power: 13	Didn't review your case file, but it sounds a lot like this issue (see Tobi's response) Problem calculating forces on blades 2 (for finding forces) jingow likes this.

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December 17, 2016, 11:34		#3
jingow New Member Humayunn Asif Join Date: Oct 2016 Posts: 2 Rep Power: 0	Hi, Thanks for the link this pretty much solves the existing problem. Will bother you if something else comes up :P