then how do you resolve this conundrum?:
Alphai =180/pi (b/2pi)
∫d/dy(
cl*c/4b)dy/(yi-y) integrated between the semi-span bounds b/2 and -b/2....
oh for the F-35?
I'll take a chance and use
Guppy's answer..as it is always correct
No change. Again, raw thrust for vertical flight; the aircraft does not rise by producing airflow and blowing it over it's own wings to produce lift.
Still does nothing to illustrate PBL's argument.
We need a break
