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The stagnation point is the point:

  • A

    where the velocity of the relative airflow is reduced to zero.

  • B

    of the intersection of the total aerodynamic force and the chord line.

  • C

    relative to which the sum of all moments is independent of angle of attack.

  • D

    of the intersection of the thrust vector and the chord line.

Refer to figure.
As we can see in the figure, the stagnation point is that point where the airflow goes from freestream speed to a standstill (velocity reduced to zero). Any airstream above will flow over the wing, and any airflow below will pass under the wing. It is not a fixed position on a wing, it moves upwards when the angle of attack reduces, and moves downwards when the angle of attack is increased.

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