If I may cut in ...
The distribution of lift across the span from fuselage centreline to wing tip on a typical subsonic airplane looks like this:
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The bit over the fuselage is usually described as 'wing/body carryover' It comes about because the airflow cannot tolerate a sudden drop in pressure where the wing root flow 'passes by' the fuselage so there is a 'smearing' of the pressure through a spanwise pressure gradient. Where the LH gradient meets the RH gradient pressures are equal.
You can have any definition you like for wing reference area so long as you stick to it. Some use a line across the fuselage joining the two wing root LE points (and/or TE root) others use the projection of LE and TE through to the centreline.
Wing body lift is just that - wing plus body without tail or nacelles. Just a remark that at normal civil aircraft AoAs, even up to stall, the fuselage lift
per se is pretty small, although there is lift in the wing region as above.
That picture of the F14 is showing condensation in the wing vortices. This is associated with the drop in static pressure in those vortices. The drop is biggest at the centre of the vortex so the 'outer' boundary is just a region where the pressure has not dropped enough to cause condensation - it doesn't mean that there is no lift from the aircraft surface underneath that point.