On Mon, 9 Jan 2006 23:27:10 UTC, "1MoClimb"
wrote:

: Bernoulli is not explaining 70% of the lift an ordinary airfoil
: generates. Bernoulli completely fails when using a flat plate which
: creates plenty of lift at normal angles of attack.

Rubbish. Bernouilli explains it perfectly well, as long as you have
the right velocity distribution. What Bernouilli's theore, does /not/
do is predict velocity distributions, and certainly not thos ebased on
fatupus ideas like "it's the different lengths of the top and bottom
surfaces that matter."

As you go on to say, rightly, it;s circulation that matters, and one
you know how big the bound vortex is a simply momentum equation on a
cylindrical control volume around the vortex/wing produces the
Kutta-Joukowski Theorem: lift = free stream velocity x circulation x
density. But do do that, no need the pressure distribution on the
control surface. Guess how you do that?

Yup. Bernouilli.

Ian

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