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The term angle of attack in a two dimensional flow is defined as:
  • A
    the angle between the aeroplane climb path and the horizon.
  • B
    the angle for maximum lift/drag ratio.
  • C
    the angle between the wing chord line and the direction of the relative wind/airflow.
  • D
    the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing.

Refer to figure.
The angle subtended between the chord line of an airfoil and the oncoming airflow is the angle of attack.It is represented by α or alpha and can also be referred to as Aerodynamic Incidence.

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