reversers and a/c speed
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.
Still does nothing to illustrate PBL's argument.
Last edited by Pugilistic Animus; 9th Jan 2011 at 19:29. Reason: lowercase 'cl and c'...ay ay ay
