Bill,
The F-14 features a variable camber wing as-well, LE flaps. The reason we can safely assume that the F-14's wing is more efficient is the much higher AR of the wing.
And as to Span-loading:
"Aspect ratio and planform are powerful indicators of the general performance of a wing, although the aspect ratio as such is only a secondary indicator. The wingspan is the crucial component of the performance. This is because an airplane derives its lift from a roughly cylindrical tube of air that is affected by the craft as it moves, and the diameter of that cylindrical tube is equal to the wingspan. Thus a large wingspan is working on a large cylinder of air, and a small wingspan is working on a small cylinder of air. The smaller cylinder of air must be pushed downward by a greater amount in order to produce an equal upward force; the aft-leaning component of this change in velocity is proportional to the induced drag. Therefore a large downward velocity is proportional to a large induced drag."
Mostly true and irrelevant to the discussion or the context in which you presented it.
Aerodynamically speaking, in the discussion of wing wakes, separation and related phenomena, it is useful to study the field properties of the field vorticity vector and with the concept of an instantaneous pattern of streamlines, drawn at a given time, everywhere tangent to that vector.
This concept leads to the idea of a vortex line and a vortex tube, the 'arrows' along such lines and tubes being directed according to the right hand rule of spin of fluid properties.
This concept led to the first two vortex theorems of Hemholtz - and while stated for the vortex field are purely geometrical in nature.
Net - you are confusing the notion of 'cylindrical tube of air' with a relevance to tip vortices and downwash?
If you believe that the smaller 'cylinder'/wingspan creates a 'stronger push down' I would invite you to a.) follow a J-3 on final approach and then b.) tuck under a 747 and tell us the results of your investigation.
Had you related lift load and AR per se you could have led into a discussion about increasing/reducing tip vortex strength - all other things being equal.
BTW - for an inviscous fluid (no friction), a stream tube, by Helmholtz's Second Theorem - must never end in the fluid itself but must close unto itself, end at a boundary or go to infinity. In other words the vortex line starts along the lifting line span wise to the tips, transition to a vortx tube at the tip and remain in decreasing strength at that point as the aircraft proceeds to its final destination, land, lose lift and close the vortex line at that point.
You experience this (the vortex, and a strong one depending on the strength of the lifting line) if you land short of that ship's point of touch down, but do not if you land past the point where the other ship 'lost lift'. After a minute or so the real world friction/viscosity dissipates the vortex.