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Theoretical Calculation of the Pressure Distribution, Span Loading, and Rolling Moment Due to Sideslip at Supersonic Speeds for Thin Sweptback Tapered Wings with Supersonic Trailing Edges and Wing Tips Parallel to the Axis of Wing Symmetry
Author(s): Margolis, Kenneth, Sherman, Windsor L., Hannah, Margery E.Corporate Author(s): Langley Aeronautical Laboratory
Laboratory: National Advisory Committee for Aeronautics
Date of Publication: 1953-02
Report number: NACA TN 2898
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