[ajayvarma5]

iam doing 2D analyses on a wing in fluent. ive done modeling in icem took square doman of 10x10 , i have given a mesh of 16L in fluent im using 2414 aerofoil, velocity 30 m/s, Re number is 2e+6,
im using velocity inlet and pressure outlet as boundary conditons, remaining are walls even curve of the aerofoil , ive used
turbulence models: k-w SST
solver settings: coupled, lease squared and second order upwind equation
although solution are converging around 80 iterations im getting very low CL and CD values.
i think i have created a good quality mesh in icem ,( premesh quality
determinant was 1 , and aspect ratio was also below 50 ) where am i going wrong pls help me im new to fluent