Originally Posted by CONF iture
...pretending that the airplane was at alpha max
Please excuse (or ignore) my intrusion into this discussion - I'm the least qualified to comment here, but I do have a question:
Would the extra couple of degrees of AoA, that are presumed to be held back by the s/w (is that your point, CONF iture?), have changed anything for the better in the outcome?
I understand that the lift coef curve is mostly flat near stall as it is. In addition, IF the extra increment in lift extended the flight long enough for the engines to spool up, wouldn't the go-around thrust-pitch couple just push the airplane into a stall? The crash would then be tail-first, perhaps.