SimCafe

Space shortcuts

Child pages
  • Flow over an Airfoil - Exercises

Versions Compared

Old Version 7

changes.mady.by.user user-6c822

Saved on

compared with

New Version 8

changes.mady.by.user user-6c822

Saved on

Key

  • This line was added.
  • This line was removed.
  • Formatting was changed.

...

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. The , and the experimental values for 10 degree angle of attack are: Cl = 1.2219; Cd = 0.0138.

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?