How to calculate drag at max AoA (moduleliftingsurface)

[K.Yeon]

For ModuleLiftingSurface, especially in the wing parts, i know the stock deflectionLiftCoeff is calculated by the area*0.284.
But how is the dragAtMaxAoA and dragAtMinAoA calculated?

the drag at max AoA for wings seems to never go over 1, so does this mean it's a multiplier of some sort?

Also if you look at stock's big delta wing, and the aeroplane main wing, both have different surface area, but have the same dragAtMaxAoA=0.6 and dragAtMinAoA=0.0, why?

If anyone know how these values work, please let me know!

Thanks!