During a 1.2g roundout, these are reasonable figures for an actual small aircraft (9000 kg gross weight) with a forward CoG:
Mainplane lift: 110 000 N
Stab lift: -3700 N
Once floating:
Mainplane lift: 91 000 N
Stab lift: -3050 N
This is without taking into account the moment of the airfoil itself, i e only considering the pure force moments of stab lift, mainplane lift and weight.
If we assume a doubling of the stab lift, we end up with -.03g of acceleration due to the lift at the elevator.
FullWings,
it seems you're right. That's hardly enough to make matters much worse or better. One plausible explanation for why the "boeing push" feels better down - time to look into the others!
411A,
"A couple of older types, it didn't work so well....Lockheed TriStar, for example, as a few (more than a few) found out."
Ouch!
Cheers,
Fred