Some divergence characteristics of low-aspect-ratio wings at transonic and supersonic speeds /
The problem of chordwise, or camber, divergence at transonic and supersonic speeds is treated with primary emphasis on slender delta wings having a cantilever support at the trailing edge. Experimental and analytical results are presented for four wing models having apex half-angles of 5 deg, 10 deg...
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| Other Authors: | , |
| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce,
[1960]
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| Series: | NASA technical note ;
D-461 |
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| Summary: | The problem of chordwise, or camber, divergence at transonic and supersonic speeds is treated with primary emphasis on slender delta wings having a cantilever support at the trailing edge. Experimental and analytical results are presented for four wing models having apex half-angles of 5 deg, 10 deg, 15 deg, and 20 deg. A Mach number range from 0.8 to 7.3 is covered. The analytical results include calculations based on small-aspect-ratio theory, lifting-surface theory, and strip theory. A closed-form solution of the equilibrium equation is given, which is based on low-aspect-ratio theory but which applies only to certain stiffness distributions. Also presented is an iterative procedure for use with other aerodynamic theories and with arbitrary stiffness distribution |
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| Item Description: | Cover title This WorldCat-derived record is shareable under Open Data Commons ODC-BY, with attribution to OCLC "September 1960."--Cover |
| Physical Description: | 43 p. : ill ; 26 cm |
| Bibliography: | Includes bibliographical references |