[erayerisik]

I am analysing naca2412 3D model in fluent I get Cd=0.8 and Cl=1.5 airfoil chord lenght is 0.3708m depth1.9m projected area along flow is 0.38(m2) are these values make sense or not?? I cant find any experimental data for my simulation.
thank you

[rvl565]

try using XFLR 5 to get Cl/Cd vs alpha and Cl vs alpha graph for the airfoil if you cant find the data

[lovecraft22]

What is the angle of attack? Cd looks high to me…

[erayerisik]

its aoa is 7.25degree and it is twisted wing 1.9m, chord size is 0.3708m and this analysis is 3D model I think thats why it is seems too much!! Is it impossible value for wind turbine??
thanks

[erayerisik]

Why Cd value is too high (0.5-0.9) in my model? Could anyone give me some advice why is that?? I could also share my model here. Please help guys!!!!

[lovecraft22]

First of all, why did you use 0.38 as reference surface? If you wing size is 1.9*0.37 that would give you 0.7m^2…

[erayerisik]

Originally Posted by lovecraft22

First of all, why did you use 0.38 as reference surface? If you wing size is 1.9*0.37 that would give you 0.7m^2…

The chord lenght of the airfoil is not same between station 0-1.9. The chord lenght is 0.37m at first station and it narrows along wing the last station's chord lenght is 0.09m. So I calculated the projected area in fluent. Thats how I get the result which is 0.38m^2

[lovecraft22]

Do you have big separated regions in your wing?

[erayerisik]

Originally Posted by lovecraft22

Do you have big separated regions in your wing?

Sorry I dont understant, what do you mean ''separated regions'' ??

[lovecraft22]

Stalled regions.

[erayerisik]

Originally Posted by lovecraft22

Stalled regions.

No its not.