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Obtain the lift and drag coefficients from the FLUENT results on the two meshes. Compare these with experimental or expected values (present this comparison as a table). The experimental values for 0 degree angle of attack are: Cl = 0.025; Cd = 0.0069, and the experimental values for 10 degree angle of attack are: Cl = 1.2219; Cd = 0.0138.

2. Alternate Meshing Strategy in ANSYS Mechanical

Watch the following video for a demonstration on how to create a more accurate mesh of our flow domain. 

<iframe width="560" height="315" src="https://www.youtube.com/embed/Q-Yzr0Yw0HU" frameborder="0" allowfullscreen></iframe>

Conclusions

Comment on the comparison with experiment for the two angles of attack. Also,comment on the effect of mesh refinement. How does the pressure distribution over the airfoil change on increasing the angle of attack?

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