[bharathlatchireddi]

hello everyone,
i've been trying to do wing analysis in fluent lately, and im using ansys student version software.
the wing analysis results giving me values as lift=12000 N and drag=2000N, but i need the lift value to be around 5000N according to the hand calculations and i am getting coeff of lift = around 7 in fluent but i need my coeff of lift value to be 1.6 which is at the stall angle 16 degree for speed of 61 m/s. can some one explain what is need to be done?
and my wing design have twist and dihedral angle in it.