The values of lift slope for elliptic wing (ae) and general planform wing (a) is less than that for airfoil (a0).

Question

McqOptions · Accepted Answer

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Mark the false statement.

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ae=$\frac {a_0}{1+\frac {a_0}{\pi AR}}$

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a=$\frac {a_0}{1+\frac {a_0}{\pi AR}(1+\tau)}$

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a0 is always 2π

McqOptions · Answer

τ is a function of Fourier coefficients

1.	The values of lift slope for elliptic wing (ae) and general planform wing (a) is less than that for airfoil (a0).
A.	Mark the false statement.
B.	ae=\(\frac {a_0}{1+\frac {a_0}{\pi AR}}\)
C.	a=\(\frac {a_0}{1+\frac {a_0}{\pi AR}(1+\tau)}\)
D.	a0 is always 2π
E.	τ is a function of Fourier coefficients
Answer» D. a0 is always 2π

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