You do not know what you are saying at all, one thing is exposed wing are and another reference wing area which uses the longitudinal symmetry reference line
For starters the Flankers like the F-14 has wider wing span why? simply because the engines are widely separated, thus the reference area has wider wing span thus more area and the Su-27 like F-14 has the pancake area which also generates lift.
Same is the F-14, you are dreaming the F-14 at lower speeds has higher lift than J-20, it has much wider area due to longer wing span thus using reference area the Tomcat is designed for lower speeds and will get much higher lift at landing approaching speeds.
F-14 also increases camber when it sweeps to lower angles thus it generates more lift.
You can see easily Deltas are not good naval fighters, but good interceptors
The exposed wing of the J-20 is not big, is the wetted area of the wing the real wing, and is not part of the fuselage, it is the actual wing.
J-20 is designed for higher cruising speeds than Flanker, you can see Su-57 also has more swept wings, but F-14, Su-27 and Su-57 have widely separated engines, F-14 did not use canards at landing or take off but Su-27 needed them during approach the landing speeds thus they made the Su-33.
J-20 uses bigger canards than Su-33, however Deltas lost lift in wing tip vortex generation.
This affects lift when they turn so deltas use canards to recover lift using the vortex of the canard to reinforce lift in the main wing.
Su-35 has high yield engines lower swept and TVC nozzles, the fighter will be superb at sustained turn rates, but is not that good as Rafale as instantaneous turn rates due to higher wing loading.
J-20 uses fuselage lift and the canards to compensate for the small wetted area and smaller wing span, with TVC will achieve STOL capability improving landing and take off speeds
. There is a reason why pointing to one lift coefficient value tells us nothing about performance. You need to look at the *whole* lift curve.
