Spanwise lift distribution on 3D wing
I'm currently using Fluent and I'd like to carry out a spanwise lift analysis.
But the only thing I manage to do is a Cp analysis along the wing... (using the XY plot function). By any chance, is there a function to plot Cl in function of the spanwise location ?
Sorry, it's seem basics function, I obviously had a look at the user manual and other tutorials, but I haven't find anything !!!
Thanks for your help
Re: Spanwise lift distribution on 3D wing
please help me, I do need this lift distribution in order to end my MSc thesis .... :)
Thanks for any kind of help
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