The induced angle of attack in terms of flow parameters for a wing is_____(a) αi=\(\frac {w}{V_∞}\)(b) αi=\(\frac {2w}{V_∞}\)(c) αi=\(\frac {V_∞}{w}\)(d) αi=\(\frac {w}{V_∞}\)The question was asked at a job interview.This is a very interesting question from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics

The induced angle of attack in terms of flow parameters for a wing is_

1.	The induced angle of attack in terms of flow parameters for a wing is_____(a) αi=\(\frac {w}{V_∞}\)(b) αi=\(\frac {2w}{V_∞}\)(c) αi=\(\frac {V_∞}{w}\)(d) αi=\(\frac {w}{V_∞}\)The question was asked at a job interview.This is a very interesting question from Prandtl’s Classical Lifting-Line Theory in portion Flow over Airfoils over Finite Wing of Aerodynamics
Answer» The correct choice is (a) αi=\(\frac {w}{V_∞}\) To elaborate: The induced angle of attack at an ARBITRARY POSITION ALONG SPAN, for a finite wing can be given as αi=\(\frac {w}{V_∞}\) where V∞ is the free-stream velocity and w is the DOWNWASH (modulus only).

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