Originally Posted by
RetiredF4
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V/S can have been reducedby other factors as well like bank angle / roll to left and right, decaying airspeed, drag by deflected ailerons / rudder.
Concerning AOA: The relationship between AOA and pitch is not factual, theoretically a pitch of 90° with an AOA of 0° is achievable (not in an transport ac, but in a fighter ac).
retiredf4,
No disagreement here. The only thing which I did was to derive the Flight Path Angle:
Flight Path Angle = Pitch - AoA
And consequently VS = Sin(Flight Patch Angle) * TAS
All I wanted to show is that 700 fpm at 400kts TAS means a Pitch attitude of significantly less than 10°..
In fact it would mean a Flight Path Angle of ~1° and thus a pitch of ~5°.
Regarding Roll it was stated that it varied between 10 - 12° left/right, so you would have to multiply the V/S with the Cosine of 12°, which would drecrease the Vs by less than 5%. Doesn't change the whole picture though.
Any speed reduction is already included as i assumed the 215kts IAS to be correct at that moment.