I'm trying to edit slightly the above post, but the computer wont let me
nor can I delete it as a copy
c=wing chord
cl = section lift coefficent
alpha [i]=downwash angle in degrees at span wise position 'y' measured from the center along dy
AoA e = effective aoa [as described by in HTBJ]
=Alpha-alphi
effective Aoa at is a function of cl
skipping a few steps we finally have [to just scratch the surface]
alphae =alpha -180/pi*b/2pi*int[d/dy(cl*c/4b)dy/y1-y],b/2,-b/2]
solving this equation for your chosen sections will determine both down wash and span wise distribution
a mathematical explaination of
Dolphin51's eloquent post
as far as the vortex effect on general circulation, in supersonic/non-ideal flows [as
BOAC mentions] well I'm not gettin on that bus
PA
