Computing aerodynamic coefficients on bidimensional sections in 3D problems
I have a problem calculating aerodynamic coefficients in a 3D simulation. I mean, the problem is a tridimensional one, but I need the value of the coefficients on a meridian line of the body I am studying (that is essentiallly an ellipsoid).
Is there a way to compute the value of aerodynamic coefficients on a line of a body using FLUENT? The only thing I know is that is possible to compute the value of the pressure coefficient on different sections of a body, starting from Fluent data and using Tecplot, but is it possible to do the same with lift, drag and moment coefficients?
Thanks everyone for the help you could provide.
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