Climb at constant pitch attitude
Hello,
If an aircraft is climbing to cruising level at constant pitch attitude (= constant body attitude ??) with max climb thrust (no supercharger) the following parameters change that way :
* Flight path decreases,
* angle of attack increases,
* IAS decreases
* IAS :
I understand that for a constant body attitude ant full power, at a higher altitude we'll have a lower IAS because the thrust is decreasing as altitude increases however the Drag may be assumed constant (which I believe is not 100% correct because Rho decreases thus D too). Thus if you want to maintain IAS you must lower the nose. And if you don't, IAS decreases.
* Flight path :
The flight path will decrease because (Thrust - Drag)/Weight decreases as altitude increases and thus the angle of climb (= flight path ??) decreases.
But what about the Angle of attack ? Why does it increase ?
Could someone confirm that my understanding is correct for IAS and Flight path. And could someone explain the change in angle of attack ?
Thank you,
Emmanuel Cordier.