How to find Lift/Drag ratio of a compelx wing in FLUENT
 

Hello

I am investigating the aerodynamic performance of a commercial aircraft wing with a dihedral sweep and varying aerofoils with and without a raked wing tip. So how do you find the Cd and Cl does fluent take in to account the induce drag when finding the Cd

Thanks

Under report-forces you can find lift and drag forces. but you must set reference values correctly to find coefficients. fluent calculates forces, and by setting all variables(density, velocity, ref area) in the force equations, you can find coefficients.

Thanks a lot