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Drag, Lift and momentum plots

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Old   December 3, 2007, 02:08
Default Drag, Lift and momentum plots
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Hi Any one can tellme how to plot drag, lift and moment coeefficients vs for differnt postion of the airfoil along the wall in Fluent. I am having the convergence history file for Cd, Cl and Cm. I got Cp VS postion but i am not getting the option for the above mentiond problem
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Old   December 3, 2007, 04:20
Default Re: Drag, Lift and momentum plots
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You should use a UDF (in Define) to get that but I'm not sure about the formula you have to use (If you find it, I will be glad to see how it looks like ). (It is possible to use the node values for the pressure and for the force).
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