Originally Posted by
HazelNuts39
BEA Update 27/05/2011
Time 2:10:05 2:10:16 2:11:06 2:11:40 2:14:28
FL ... 350 ... 375 ... 380 ... 350 .... 0
Mach . 0,81 . 0,68 .. 0,60 ... 0,40 .. 0,23 ???
kCAS . 275 ... 215 ... 185 ... 130 ... 151 ???
kTAS . 479,5 . 399,6 . 350,6 . 233,5 . 151 ???
V/S - fpm 0 .. 700 .... 0 ... -10000 . -10912
alpha . 2,7 ... 4 .... 16 ..... 40 .... 61,2
gamma . 0 ..... 1 ..... 0 .... -25 .... -45
theta . 2,7 ... 5 .... 16 ..... 15 .... 16,2
TE-FL . 452 .. 446 ... 435 .... 374 .... 10
Thanks HazelNuts !
Interesting Data Point!
Back in the old thread I did a calculation based on projected surface of an A330 and a weight of 210t:
You would have to enter the L/D diagram of the A330 at an Alpha of ~45° with 85 kts and see if the combined Lift and drag higher than the 2100 kN (+ thrust of the engines).
That would mean ~1500kN along the trajectory, if no thrust of the engines available (idle, stalled) and ~ 1800kN at Cruise Thrust along the 45° path.
The projected surface at 45° being roughly 520 sqm, at 44m/s you get a resisting force of 620 kN at Cd = 1.
This means the Fuselage + wing would have to have a drag coefficient of ~ 2,5 - 3.
That's definitely too much.
I would expect something around 1.
At Cd = 1 it would mean ~80m/s => ~160kts along the trajectory. =>
~110kts horizontally + 110 kts vertically
I have now new empirical data which is difficult to get from the books
Basically this indicates that the drag coefficient of an airliner in a deep stall (AoA ~ 45°) appears to be close to 1.