[musman]

hello i need help to get result like cl cd and cm from cfx post process and cp curve urgent thanks

[Jules]

Muhammad,
please describe your problem more clearly. What are you simulating? An airfoil?
Besides that, reading the manual to CFX Post would definitely answer the question for you.
A little hint: Use a CEL expression like:
force_y()@airfoil_surface to calculate the vertical force. Replace "airfoil_surface" with whatever name the airfoil surface wall boundary has in your simulation. Use inlet velocity and density at inlet and the definition of cL to calculate cL. Do the same with force_x for the drag coefficient. Use a similar approach for cM. (Not sure if there's a direct function for calculating the moment, refer to the manual)

Good luck,

Jules

[LSC]

Hi, just to clarify that the inlet velocity refers to free stream velocity right?

[Jules]

Originally Posted by LSC

Hi, just to clarify that the inlet velocity refers to free stream velocity right?

Of course. Sorry for my sloppy writing. But in a usual airfoil simulation setup, these two are equivalent.

Jules