The wing's lift coefficient is an average, and no section is at it

The section lift coefficient across a tapered wing, with the wing's own C_L drawn as a flat line and the chord distribution behind it. The wing is at C_L = 0.696 and the sections range from nearly nothing at the tip to 298 pixels of the axis at the peak — the point being that a single number for the wing tells nobody which section is closest to its limit. Everything that matters about a stall, an aileron and a twist distribution lives in the difference between these two curves.

2 essays call span-load. The drawing above is what it returns with no arguments at all; every call below passes it something, because a placement that passes nothing draws whichever member of the family the generator happens to default to rather than the one its essay argues about.

It is also the blast radius. Changing span-load changes every figure listed here at once, and on this site it may change what they assert as well as what they show — which is what has to be rebuilt and looked at before the change is believed.