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[General] Plot Cp along airfoil NACA0012

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Old   May 16, 2017, 10:58
Smile Plot Cp along airfoil NACA0012
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Lucas
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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 SuČ, and I try to build the following graph which is included in the quickstart study case of SU2 :


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
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