[aleix.de.toro]

Hi friends!

Im new on this forum, I've started learning fluent because i need to make a final project designing a plane for my final degree.

I am starting with a NACA 0012 (in 3d ). Firstly i am introducing a velocity inlet of 30 m/s, and inviscid flow model.

I have done it with 0 AngleOfAttack ( on boundary conditions X=-30 m/s)

With 5 AOA (X=-30 cos (5), Y=0, Z=-30sin (5))

and with 10 AOA (X=-30cos(10), Y=0, Z=-30sin(10))

I have attached 3 plots of velocities for the three angles, I think it is really strange that the stagnation point (where the velocity is 0 m/s), when I change the angle of attack does not varies. Are these results bad?

The other two plots show the coefficients of pressures around the naca (for this part I have created an Iso surface, selecting mesh and Y coordinate from the airfoil surface). For the results, I think there is almost no difference and it should be more difference.

Moreover, the results for 5 AOA (Cd=0.027117317 and Cl=0.30893708)
10 AOA (Cd= 0.10493012 and Cl=0.59508828 )
I think that the value of the Cd (0.10492012) is not very reasonable.


What do you think about the results?

Thank you