Joined: Jan 30, 2010 - 03:27 AM
I read through some old threads here and I have some questions.
Why does the U-2 use an engine with a .87:1 bypass ratio when it is designed for high altitude?
Is the dropoff in thrust with altitude for a .7 and above engine really that bad compared to say, a .4 engine?
Is there a bigger difference in the dropoff at higher speeds vs the dropoff at lower speeds? That is, would a plane designed to fly faster than a U-2 suffer more with the higher bpr than with a bpr around .4?