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

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).