On Mar 13, 9:57 pm, WingFlaps wrote:
On Mar 14, 2:46 pm, Dan wrote:



On Mar 13, 8:50 pm, WingFlaps wrote:

On Mar 14, 1:00 pm, wrote:

On Mar 13, 1:37 pm, WingFlaps wrote:

Nope, if the airspeed is constant, the lift from the two wings is not
the same. This is thought provoking discussion I was hoping to start!
Can you see why lift does not equal weight in both cases?

Common misconception: that a climbing wing is generating more
lift than a descending wing. If the flight paths are both straight
lines, whether climbing or descending, the lift is the same in both
cases. As Jim said, only a change in the direction of flight will
change the lift/weight ratio. A G-meter (such as in our Citabrias)
will prove it.
If the airspeeds are the same and the flight paths are both
straight, the AOAs are both the same, too. But change the speeds while
leaving the flight paths alone, and the AOA will change. It's why the
airplane has a nose-high attitude in level slow flight as opposed to a
lower nose attitude in level cruise.

Hi Dan see my rely to Jim. In fact, lift is reduced in a steady climb.

Cheers

The trust vector is added to the lift vector in a climb, as the drag
is added to weight.

Are you saying that wing lift does not change with attitude in a non-
accelerating frame?

Cheers

Of course it does.

However -- In a climb thrust acts contrary to drag some component of
weight (depending on the angle of climb). Thus the angle of attack is
not *necessarily* equal to the angle of climb.


Dan Mc