Originally Posted by
shdw
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.
We would probably both agree that I wasted money in the Aerospace Engineering program at ERAU. Obscure terms I likely don't understand is a slightly cheap shot though. Perhaps my garble and lack of understanding is evident in a previous conversation about indicated stall speed increasing with altitude. Several people complained that it was too technical - well AE is a technical subject and these subjects are under the technical thread.
Some of these things are hard to dumb down, and often require a proper premise to build upon.
So to aviod further strife I will give websites that explain the content which I am trying to convey. In this instance, we all know now that the ground effect has a relation to Vortices (or the lack thereof) - here is a website to explain them:
Vortices: Momentum and Energy Near a Wing
Now back to an obscure term I likely don't understand:
Kutta-Joukowski
Kutta-Joukowski Lift Theorem
basically lift is produced by creating downward momentum of the air flowing over the wing in any case
F=MA has everything to do with lift being created.... as a matter of fact all of Newtons laws are evident here.