Fluent 3d wing simulation cp, cl and cm
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,
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