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Thread: Effect of Span-Loading on Aircraft Performance
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Old 3rd February 2012 | 16:31
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Pugilistic Animus
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From: The No Transgression Zone
Just in case anyone is interested the coefficient of drag varies with aspect ratio as follows: Cd'= Cd + Cl^2/pi( 1/A' - 1/A)

For computation of span-wise load distribution for non-elliptical loading Munk's integrals can be used with the help of computers...
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