aerodynamic characteristic of NACA0012
 

hello

I am new to Fluent. I am working on the NACA 0012 Airfoil. i am trying to match the coputed results with the experimental dat. i get very different drag coeff. whereas lift coefficient is good. i have computed this with invisid flow, and PRESTo for pressure under discretization. for this condition i get highr stall angle like 2o deg. but when i use second order for pressure under discretization... i get slightly lower lift coefficient witrhin 10% and getr stalling angle as 14 deg. can anybody explain me. i would like to know. what is the best way to get the experimental data matched