hi guys im currently doing my level 8 thesis on obtaining accurate figures of lift and drag in solidworks however i am far from it and i only have 3 weeks left to submit my thesis so any helo would be appreciated. i am doing it on a naca wortman 76-100 airfoil. for an angle of attack of zero my drag should be 0.037 according to naca however i am getting 0.02. if you require any pictures please let me know.