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The angle of attack is the angle between…

  • A

    The undisturbed airflow and the longitudinal axis of an aeroplane.

  • B

    The chord line and the longitudinal axis of an aeroplane.

  • C

    The chord line and the oncoming airflow.

  • D

    The wing and the fuselage of an aeroplane.

Refer to figure.
Angle of Attack (AoA, α or alpha) is the angle between the Relative Airflow and the Chord line.

AoA constitutes one of the elements of the Coefficient of Lift (CL) and affects its value. More specifically, Lift increases (up to a point) as AoA increases.

The maximum lift point is called "Critical AoA" or "Critical alpha" and the relationship is roughly linear up to 15° approximately for a symmetric airfoil.

Beyond this point, the amount of lift produced decreases as the AoA increases further. The AoA beyond the point which lift starts to decrease is known as "Stalling AoA".

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