For CG calculations, where is the root chord located on a swept wing aircraft? With a swept wing aircraft (specifically a MiG-25 I am modelling) where is the root chord taken from to calculate the location of CG?
Is it the root chord of the wing (where it attaches to the fuselage) or a projected line extended from the the leading / trailing edge to the centreline of the fuselage?
It's expressed in Mean Aerodynamic Cord. On a swept back wing, you can construct it as follows.