> True, all good points. The induced drag equation, also listed as the span
> efficiency factor (e) for all wings is
>
> CL^2 / PI * AspectRatio
Tim, I just read my earlier post, this is not correct.
A span efficiency factor e can be defined such that,
induced drag coeff = lift Coeff ^ 2 / PI * e * AspectRatio
For elliptical planforms, e = 1; for all other planforms e < 1. Typical
subsonic planes are 0.85-0.95.
Thomas C.
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