Hi everybody,

I was wondering if anybody can help me with this subject. I just finish a 3d simulation of a 3d wing geometry, with the following parameter: MACH=0.8 at 35000 feet, inviscid flow.

Now I want to postproccess the data and I was wondering how can I obtain the cp, cl and cm distribution for my configuration.

Thanks in advance,

Joel

Hi, Joel; I posted a question on the some subject days ago, but nobody replied....However, I've found the solution by myself, so I can help you. You should create a "2d-slice" of your 3d wing using the command: surface-> iso-surface; If the span of your wing is in the z-direction, you have to create a z-costant isosurface (surface of constant "grid..." "Z-coordinate") at the iso-value that you whant to use. now you can plot the Cd/cl/cp coefficient on the slice you created, obtaining a nice 2d-plot. Hope this helps; bye, Ugo

thansk a lot ugo