Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips. : Subsonic leading edges and supersonic trailing edges / Margery E. Hannah and Kenneth Margolis.
On the basis of the linearized supersonic-flow theory and theoretical spanwise distributions of circulation (which are proportional to the span load distribution) resulting from constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips, subson...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1952.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2831. |
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| Summary: | On the basis of the linearized supersonic-flow theory and theoretical spanwise distributions of circulation (which are proportional to the span load distribution) resulting from constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges. The results of the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with aspect ratio, taper ratio, Mach number, leading-edge sweepback, and axis-of-pitch location are also included. |
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| Item Description: | "December 1952." NACA TN Number 2831. |
| Physical Description: | 221 pages : illustrations ; 28 cm. |
| Bibliography: | Includes bibliographical references. |