Compared with the flap up configuration the maximum angle of attack for the flaps down configuration is
- unchanged.
- larger.
- smaller.
Explanation from PART66Online
Trailing-edge flaps increase camber, which raises the lift curve but causes the wing to reach its maximum lift coefficient at a lower angle of attack. So compared with flaps up, the maximum (stalling) angle of attack in the flaps-down configuration is smaller, even though the stall speed is lower because CLmax is higher.
V
vmartin asked · 2 Sep 2020
in Cl/aoa graphics, flaps-down line remains upwards parallel. so, why the answer is not unchanged?
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