1.

For very high aspect ratio wings, the lift curve slope resembles that of the airfoil.(a) False(b) TrueI got this question during an interview.I would like to ask this question from Prandtl’s Classical Lifting-Line Theory in chapter Flow over Airfoils over Finite Wing of Aerodynamics

Answer»

Right option is (b) True

The EXPLANATION is: For any GENERAL wing planform lift slope is GIVEN by a=\(\frac {a_0}{1+\frac {a_0}{\pi AR}(1+\tau)}\) where τ is a function of the Fourier coefficients used to describe the planform area. As aspect ratio becomes very large (i.e. AR tends to ∞), we find a becomes A0 i.e. for very high aspect ratio wings, lift slope for wing and airfoil is the same. Prandtl verified this through experiments ALSO.


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