CL-alpha plot

[Alastair Lai]

Hi, is it possible to output the CL - alpha data generated by SUAVE during its analysis of the  aircraft aerodynamics? I am looking to generate a CL - alpha plot.

Kind regards,

Alastair

[Hu gePanic]

there is for sure a "better" way to do this, but what I would do:

define a mission that flies the alpha-angles (and other parameters) you are interested in.

then analyse the results-file to extract all alpha/cl combinations. then make a plot

check this function to find where alpha and cl are stored:

\SUAVE\Plots\Performance\Mission_Plots.py

basically:

        cl   = segment.conditions.aerodynamics.lift_coefficient[:,0,None]
        cd   = segment.conditions.aerodynamics.drag_coefficient[:,0,None]
        aoa  = segment.conditions.aerodynamics.angle_of_attack[:,0] / Units.deg
        l_d  = cl/cd

[Emilio]

There's also an example here. If anyone out there wants to make this into it's own method with a prescribed velocity/mach, altitude, and aoa range that would be appreciated. It's not much work.

-Emilio

[Alastair Lai]

Thank you all, I will have another try at outputting the data.