Need help with this lift-line theory application

[angel1601]

TL;DR

I'm calculating the lift coefficient of an elliptical wing while i'm changing the values of AoA. Then, i'm doing an CL vs AoA plot, but here it shows a straight line and i read that it's supposed to stall in one point, but it's not happening here. What can I do? Or how can i interpret this result?

 

[Lnewqban]

Welcome, angel1601!

The AOA should increase the value of CL, but only until the critical AOA (maximum value is reached).
The critical angle is normally found for a specific wing via experimentation.

Please, see:
https://en.m.wikipedia.org/wiki/Angle_of_attack