Quote:
Originally Posted by aerohead
* On the NACA Report, I wanted you to see the polar diagram for the Clark-Y aerofoil, and it's zero-lift at negative 5.6-degrees angle-of-attack, negative lift at negative 8,2 degrees angle-of-attack, and maximum lift at positive 15.6 -degrees angle-of-attack.
|
You keep talking about wing profiles having the ability to develop zero lift at certain angles of attack. That's fine - there's plenty of data that shows that. Trouble is, it's another of your argument
red herrings.
For example, let's give The Template a negative 5.6 degree angle of attack (as you nominate for the Clark Y) and then let's add a suitable underfloor profile (red).
I'd be pretty confident that lift would now be waaaay down. Trouble is, it's also now a completely different shape...