Wing Lift and drag coefficient
 

Hi everyone!!!

I am trying to calculate the lift and drag coefficient of a 3D wing in CFX. I know CFX offers viscous force in X, Y and Z direction.

My flow is aligned with the the x-axis. Therefore, am I right saying that I can use the force in the x-axis to obtain Cd and the force on the y-axis can be used to obtain Cl ??!!

Thank you for your consideration.

No, CFX gives the total force in X/Y/Z directions. It does not calculate viscous forces separately. But you may be able to calculate it from integrals of wall shear stress.

Your question is correct. This is the standard definition for Cd and Cl.

Thank you so much!!

So basically the force in x-axis is also the drag force (skin friction + form drag etc.) and the y-axis is the amount of lift force produced by the wing.

From these forces I just have to work out, the Cl and Cd.

Thank you once more for your time

Kind Regards

That's right. force_x/y/z is the total force in that direction.