The lift
DATCOM's lift slope, Polhamus's vortex lift, and vortex breakdown.
Every part of the field is driven by lift: the circulation the tip vortices carry, the strength of the leading-edge vortices, the suction over the wing. So the lift is worked out first, from the airframe and the flight.
Attached flow
DATCOM's lift slope gives the lift of the attached flow for the wing's aspect ratio, sweep and Mach number.
The leading-edge vortex
A sharp, swept leading edge doesn't hold its flow at any useful angle of
attack. The flow separates off it and rolls up into a vortex lying over the
wing, whose low pressure adds lift. Polhamus's suction analogy turns the
leading-edge suction an attached flow would have had into that vortex lift.
leadingEdgeSharpness says how much of it a given edge sheds: all of it for
a chined fighter or a delta, about half for a round-nosed wing.
Breakdown and the stall
Vortex breakdown marches up the wing as the angle of attack grows, sooner for
a less swept edge. Behind it the vortex's core swells and stops lifting, so
the vortex lift goes with it: that is the stall, and why
angle_of_attack_for_load stops at the wing's maximum.
Circulation
The tip vortices hold the wing's circulation once the sheet behind it has
rolled up, by Kutta–Joukowski over the rolled-up pair, Γ = L / ρ V b′, with
the pair π/4 of the span apart. The leading-edge vortices hold what slender-wing
theory says the vortex lift needs.
Rolls and sideslips
A roll at rate p raises the angle of attack of the wing going down by
p y / V, about p s / V over the angle the whole wing flies at. A sideslip
turns the leeward wing's sweep against the flow and the windward wing's into
it, 2β tan Λ between them for a swept edge. Each side's vortices and each
half of the sheet take that side's share.
These are a loading per side, not a recomputed lattice: good for the trends, not the last ten per cent.