[cfang]

Im a beginner in this field.. im doing my final year project about 3 dimensional airfoil analysis. But as 1st task, im ask to do 2 dimensional meshing and run analysis using fluent. so, i choose naca0012, with structured mesh.. however, when i run it in fluent, i just cant get the desired data. from experimental data, stall angle is around 13 deg for reynolds no 2x10^6. but i cant get it. my data shows stall at 45 deg. alot different with the experimental data. i tried using velocity inlet as boundary condition, then pressure far field.. but still cant get the correct result.. how??