JAA ATPL Test

SUBSONIC AERODYNAMICS

Basics, laws and definitions

Question	Correct	Score
1 of 63	0 of 0	0%

The term angle of attack in a two dimensional flow is defined as:

	A)	the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing.
	B)	the angle between the wing chord line and the direction of the relative wind/airflow.
	C)	the angle between the aeroplane climb path and the horizon..
	D)	the angle for maximum lift/drag ratio.