The incorrect choice for the general lift distribution for a finite wing is ________(a) Circulation is assumed a Fourier series(b) 0 &leq; θ &leq; 2π(c) Coordinate transformation is for spanwise direction to θ(d) Coefficient of lift depends on aspect ratio directlyI got this question during an interview for a job.The query is from Prandtl’s Classical Lifting-Line Theory topic in section Flow over Airfoils over Finite Wing of Aerodynamics

The incorrect choice for the general lift distribution for a finite wi

1.	The incorrect choice for the general lift distribution for a finite wing is ________(a) Circulation is assumed a Fourier series(b) 0 &leq; θ &leq; 2π(c) Coordinate transformation is for spanwise direction to θ(d) Coefficient of lift depends on aspect ratio directlyI got this question during an interview for a job.The query is from Prandtl’s Classical Lifting-Line Theory topic in section Flow over Airfoils over Finite Wing of Aerodynamics
Answer» Correct option is (b) 0 &LEQ; θ &leq; 2π To elaborate: For a general lift distribution of a FINITE wing, the circulation is assumed a Fourier series from the expression obtained for elliptic lift distribution. The transformation involves spanwise coordinate TRANSFORMED to θ, where 0 &leq; θ &leq; π. Using this the lift coefficient obtained depends DIRECTLY on the aspect ratio.

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