How to plot the Cp distribution across an 3d aerofoil at any given location
 

Hi all

i was really wandering if anyone can tell me how to plot the Cp distribution across the surface of a 3d aerofoil for any given distance along the x-axis

when i try to plot the normal way by using the plot function and selecting a surface i get a graph that is full of multiple reference values for the same x-axis location, I assume this is due to the model being 3d, if so can you plz tell me how to plot it for a 2d cross-section.

thank you very much in advance of any help

Something to do with isoplanes if i remember clearly..
How did you get the values of cp in the right range..how to set reference values so that cp is is 0 to 1 or whatever...I get cp as 1.3e6 etc...?