Note presenting equations derived for the wave drag of sweptback untapered wings at zero lift with thin double-wedge sections and arbitrary chordwise location of maximum thickness. Calculations are presented for a representative supersonic plan form. Results regarding section wave drag, wing wave drag, comparison with two-dimensional theory, and comparison with tapered wings are provided.
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Note presenting equations derived for the wave drag of sweptback untapered wings at zero lift with thin double-wedge sections and arbitrary chordwise location of maximum thickness. Calculations are presented for a representative supersonic plan form. Results regarding section wave drag, wing wave drag, comparison with two-dimensional theory, and comparison with tapered wings are provided.
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National Advisory Committee for Aeronautics Collection
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Margolis, Kenneth.Effect of Chordwise Location of Maximum Thickness on the Supersonic Wave Drag of Sweptback Wings,
report,
March 1948;
(digital.library.unt.edu/ark:/67531/metadc54538/:
accessed February 22, 2019),
University of North Texas Libraries, Digital Library, digital.library.unt.edu;
crediting UNT Libraries Government Documents Department.