Would love for you to give me a demonstration on how Kutta?Joukowski theorem - Wikipedia, the free encyclopedia can be used "a little bit" with F=MA.

What the formula shows you is that fluid flow is effected based on AOA. As you tilt back a higher AOA you change the flow pattern around the wing creating a higher pressure above and increasing the Cl. This increase in Cl also occurs due to the changes on airflow around a wing when it is in ground effect, in the case in point it increases.

Stop arguing with obscure terms you likely don't understand, not claiming I do, and read first, then reply. You are going to confuse every single person you have that reads this forum with your garble, some right, some not, and tons of added junk.

PS Further confusing people with discussion on net versus total lift doesn't change the fact that lift, the aerodynamic force perpendicular to path, goes up when Cl goes up. If it didn't, AOA would not make the aircraft gain lift, that you can pretty accurately see is false, AOA does change lift.