On 16 Jul 2004 07:03:55 -0700, (Andy Durbin)
wrote:


Isn't it also true that lift will be reduced if a highly flexed wing
increases its angle attack beyond the critical angle of attack. If
the wing is producing less lift it cannot maintain the flex that
existed before the critical angle of attack was exceeded. As the wing
unflexes the tip angle of attack increases.

Which of those assumptions is invalid?

All of threse assumptions are valid.
But if the tip is already stalled it doesn't matter a lot if it has
exceeded its maximum AoA by 2 degrees or 6 - the resulting stall is
the same.

But to stall a 20 with sufficient g-load to get significant wing flex,
you need a lot of speed and a nearly fully pulled-back stick.

I havent's flown a 20 for a couple of years now - maybe one of the
current 20 drivers could check this out, but I doubt that at 4g the
wing flex is more than three ft compared to level flight. The
resulting AoA change as the wing reflexes will be less than 1.5
degrees then.... neglectable.

Bye
Andreas