[sanboju]

I want to know how to get the lift and drag values in CFView and its coefficients in a 2D airfoil. How can I operate the pressure around the airfoil?

Does exits some kind of solution to plot the entire Cl-AoA, Cd-AoA, Cd/Cl - AoA curves? Do I have to do one simulation for every point of the graph?

Thanks,
Sanboju

[oldshoes81]

Hi,

Both lift and drag value could be found in .mf and .wall files in your computation directory. We do not compute the coefficient and it has to be calculated manually for the moment to consider your span area.

I hope this is useful.

[sanboju]

Originally Posted by oldshoes81

Hi,

Both lift and drag value could be found in .mf and .wall files in your computation directory. We do not compute the coefficient and it has to be calculated manually for the moment to consider your span area.

I hope this is useful.

Hi,

Thanks a lot because of your reply. I will read the documentation to find how extract that values. I've got the *.mf file empty with this advice "NO INLET AND / OR EXIT FOUND". I've used external boundary conditions on the limits. In the *.wall file I could see some parameters per block. Does It means I have as much pressure resultant as blocks (4 in my case as you can se on the picture)?

Another question… does the lift and drag that Fine/Turbo shows in the graph correctly computed depending on flow direction meanwhile the computation is on?

Thanks,
Sanboju

[oldshoes81]

Hi,

Your question is quite blur. Are you using FINE(TM)/TURBO or FINE(TM)/HEXA?

[sanboju]

I'm using Fine/Turbo, modeling with IGG. I refered to the convergence history values of lift and drag. In the picture I've uploaded you can see the nearest blocks around the blade, It exits another blocks defining the domain.