Plot Cp along airfoil NACA0012
 

Hello,

I've been trying for few hours now to plot the pressure coefficient along a NACA0012 airfoil with Paraview.

I have a 2D mesh so I do not manage to use the "Plot on intersection curve" feature.

I obtained my numerical results with Su², and I try to build the following graph which is included in the quickstart study case of SU2 :

https://camo.githubusercontent.com/7...5f63702e706e67
On this graph, there is the Cp on the upper and bottom line of the airfoil.

Does anyone knows how to do this in Paraview?

Thanks a lot.

Lucas