Abstract
in which CL is the wing lift coefficient, A the aspect ratio and a the induced-drag factor. Although valid for an untwisted wing (section zero-lift chords all parallel), Eq. (1) gives incorrect values for a twisted wing. For example, CDI = 0 in Eq. (1) when CL = 0, while the induced-drag coefficient of a twisted wing is never zero. The correct formula for the induced-drag coefficient of a twisted wing can be derived from the theory of spanwise air-load distribution given in references 1 and 2. In this theory the section lift coefficient Cx a t any airfoil section along the span is expressed as a Fourier series, namely (p. 7-29)
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