I am currently working on a final year project which involves the aerodynamics around an airfoil.
while I am familiar with the post processing activities with CFD software, I am not entirely sure how I can attain the Lift Coefficient (Cl) data from the CFD pressure and velocity data.
I know the mathematical relationship between Cl and Cp (pressure coefficient) but surely there must be a way to directly extract Cl from the Cp calculated by the software.
Thanks.
As such there is no direct extract of this parameter. You need to extract all the known variables either area-weighted average or volume-weighted average and use in correlation to predict lift coefficient
As colleagues replied, you have to consider the dimensional aspects of the wing which are already influencing Cp results. Here, this is an easy sheet to aid you.
http://mercury.pr.erau.edu/~hayasd87/AE301/AE301_Group_Assignment_1b_Hints.pdf
Certain CFD software tools like StarCCM+ or also Fluent have integrated features that calculate force coefficients from the obtained solution. Essentially in that way you can directly get a lift coefficient from the simulation witout further work. However, those algorithms do nothing else than what was previously mentioned already. Calculate the forces of a body by extracting the pressure (or wallshear stresses for friction) on each of the surface cells and usign this to calculate discretized forces which are integrated to a total force. That force is then normalized to a force coefficient
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