"nospam" wrote in message
news:PNydnSQ4QbdIurnVnZ2dnUVZ_j-dnZ2d@internode...


Geeez I hadn't realized how thick you guys are.
Of course the tail, elevator and tab are taken into account - AOA tail is
wing AOA plus downwash, elevator AOA is wing AOA plus tail downwash plus
elevator angle, tab AOA is wing AOA plus wing downwash plus tailplane wash
plus elevator wash (at a particular elevator angle). Your comments on
elevator float position are irrelevant when one decides to do calculations
at a particular elevator angle. Float position is nice to know for stick
free stability measurements, but both the pilot and the engineer can set
the elevator angle at any they wish irrespective of float.
If you really believe that aircraft are not the sum of the parts I would
suggest that any study of serious aerodynamic theory is probably beyond
you.

References:
Duncan W. J. Control and Stability of Aircraft
Babister A. W. Aircraft Stability and Control
Perkins and Hage Airplane Performance Stability and Control

Get these out of your library you might actually learn something!
and
Course Notes Empire Test Pilot School.

The top 3 are widely used texts for aeronautical engineering degree
courses.
I know I wrote I would not be back and I now realize that this group is
not one where serious informed discussion can be had.
I really won't be back.



Hey, don't let these to assholes run you off. There are a lot of good and
reasonable people around here. You just have to learn who to ignore, and you
just met two of the three most troubled children.

Stick around. Just don't answer these two from now on.