An airfoil requires a certain amount of velocity of airflow to create the pressure differential between the top and bottom surface required to equalise the lift and weight components. The actual difference in pressure is quite small. Aircraft are designed aerodynamically therefore less drag equals less thrust required.
Anyways, it is much easier to move horizonally than vertically.
So, you may notice that your rated output of thrust is quite a bit less than your weight (if you are able to convert the two into a single unit of measurement).
E.G. A mate and I only yesterday were considering thrust outputs on a 747-300 with RR RB211-524D4 engines which had a rated thrust of 51980lbs minimum times 4 engines.
Now if anyone figures something different I'm happy to listen and be corrected if I'm wrong.
This equates to a little over 94 tonnes of thrust total. Awesome.
The 747 MTOW is almost 400 tonnes. Awesome.
Hope that helps.
