Another stall spin
Am Montag, 3. September 2012 01:38:50 UTC+2 schrieb unkown:
Am Donnerstag, 30. August 2012 22:13:31 UTC+2 schrieb (unbekannt):
I like Bruno and his videos, but some of what he does and shows do not reflect examples of how we should all fly. This is such an example.
So- what does Crabby UH say he did wrong?
1- Obviously exceeded the critical angle of attack of the inboard wing- gust likely a factor- could happen to any of us, and does.
2- As the wing starts to drop, adds top aileron, obviously as an automatic and likely habitual reaction. This has the effect of increasing the angle of attack on the most critical portion of the wing at exactly the wrong time.
3- No obvious use of opposite rudder.
4- No forward stick to reduce angle of attack, in fact it appears the stick is positively held back.
The dumping of flaps seems to be well practiced in recovering from this maneuver- I wonder who taught him this.
When I have just stalled a wing, I'm just above the critical AoA and my wing produces hardly any lift, so my AoA will increase further. But when I detect this early enough I might be able to get below the critical AoA by just moving the flaps forward. This is the most direct and the fastest way to change my AoA. If I mange to reduce my AoA below the critical AoA by moving the flaps forward, I produce more lift than with the flaps in the original position, so my increase in AoA is slower. If the gust, which caused my stalled wind, ends before I read the critical AoA in the new configuration this might be sufficient to regain control.
Reducing my AoA with the elevator is only my second but long term option, because I have to rotate my ship around the lateral axis and this rotation takes time.
With the flaps I can reduce the AoA for only a short period of time, but it quite often buys sufficient time to stay unstalled during the gust. If it is not sufficient, I have to use the conventional slow indirect method with the elevator.
"stalled wind, ends before I read" = "stalled wing, ends before I reach"
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