Cp over an airfoil using fluent
 

How to calculate/determine the Cp at upper and lower surface of an airfoil at user-defined points (at upper and lower surface), instead of cslculating Cp at each grid point (cell/node).

I have experimental data at some certain locations, I want to compare at those locations.

How can I do this either by using Fluent or tecplot?


Regards

Ali

maybe you can define upper and lower surface as different walls.
than you can plot Cp for both surfaces and you can compare with experimental data.