NASA NTRS · 19770016111
Spanwise variation of potential form drag
Abstract
The finite element method is used to calculate the spanwise variation of potential form drag of a wing at subsonic and supersonic speeds using linearly varying panels. The wing may be of arbitrary planform and nonplanar provided the wing panels are parallel to the aircraft axis.
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Clever, W. C.. 1977-05-18. Spanwise variation of potential form drag. https://ntrs.nasa.gov/citations/19770016111
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