How heavy are modern cantilever monoplane wings? Aircraft need to reduce weight in order to reduce induced drag.  The modern shallow cantilever beam wings carry a massive weight penalty, as most of the material is wasted inefficiency absorbing the bending moment. However, with advancements in materials,  their mass has reduced to the point that parasitic drag benefits outweigh induced drag losses.
But I would like to know how much structural efficiency still influences wing design. Compared to the total empty weight of the aircraft, how heavy are the wings if modern cantilever monoplanes? This includes large airliners and small GA planes. An example of a design from each class is sufficient.
Wing structure is roughly 20% of empty weight, which is roughly half of gross weight. I clipped the two sources some time ago and no longer have references.