stalling angle

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stalling angle

[′stȯl·iŋ ‚aŋ·gəl]
(aerospace engineering)

stalling angle

The angle of attack at which the flow of air over the wing begins to separate from the wing surface, resulting in a significant reduction in the lift and an increase in the drag. The lift coefficient of an airfoil is maximum at this angle and begins to decrease rapidly at angles beyond it. A stalling angle is fixed for an airfoil, whereas the speed at which it will stall is not. Also called the critical angle of attack* See stall.
References in periodicals archive ?
It gives good performance with a stall angle between 10 to 15 degrees compared to NACA0012.
1) The agreement between computed and experimental values of lift coefficient is very good up to stall angle.
Maximum lift coefficient and stall angle of attack increases are the result of an overlap effect between opposite effects: trailing edge thickness increases both, but airfoil thickness and lower camber decrease them both.
The improvement in the lift coefficient of blunt trailing edge airfoils was studied, as they have a larger maximum lift coefficient and a larger stall angle of attack than unmodified airfoils.
What the Kenyan pilots had no concept of is the relationship of bank angle and load factor to stall angle of attack.
The main performance killer is drag and the effect icing has on the stall angle of attack and, indirectly, stall speed.
The company does not call it an angle of attack instrument, but does state that the LRI identifies the absolute stall angle for any aircraft.