I recently read in the manual for The Beechcraft T-6 Texan II (a turboprop aircraft) about engine failure during flight at different altitudes and the gains from pitching up after the engine failure occurs to trade airspeed for altitude.
They show graphs that depict the altitude gain from pitching 20° nose up attitude bleeding airspeed from 200 KIAS to 145 KIAS at different Pressure Altitudes. The not so intuitive part is that shows how the heavier the aircraft gets (by having more fuel) the more altitude gain by pitching the same amount of nose up (20°) until airspeed bleeds off from 200 to 145 KIAS in case of engine failure. could someone please explain how could this be possible? I doubt there is a mistake in their manuals. There are a couple of these graphs from 250 to 145 and 200 to 145 at different Pressure altitudes.
At a first glance, it may seem intuitive to think that, if the heavier aircraft encounters an engine failure and it pitches up (same amount nose up attitude as the lighter aircraft) it will produce the same amount of lift as the lighter one (at the same pressure altitude and same airspeed) but with more weight the less lift to bring the aircraft to a higher altitude compared to a lighter aircraft. I guess that is not right?
If there is a vector analysis/equations or any math proving this I would appreciate it a lot.
In other words: two identical turboprop aircraft, except A weighs less than B, fly at same KIAS, engine fails, both pitch up 20° nose up, which one gains more Alt?
The graph of weight vs altitude gain: