The use of pure twist for drag reduction on arrow wings with subsonic leading edges / Frederick C. Grant.
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington :
National Advisory Committee for Aeronautics,
[1957]
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
4104. |
| Subjects: |
| Abstract: | Linearized-theory calculations of the drag reduction achieved by applying the first three terms of a power series for twist to flat delta wings are presented. In addition, the reductions due to applying linear twist to a family of flat arrow wings are presented. The results cover the speed range of subsonic leading edges. The results show a 6-percent drag reduction due to twisting a flat delta wing with sonic leading edges and a steady decrease in the gains as sweepback increases. For the family of linearly twisted arrow wings investigated (that with sonic trailing edges), the maximum drag reduction is 2 percent in the medium sweepback range with a steady diminution in both directions. A beneficial effect of increasing aspect ratio obscures the twist effects in this case. The convergence to the optimum-power-series twist appears to be rapid. |
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| Item Description: | "August 1957." NACA TN Number 4104. |
| Physical Description: | 28 pages : illustrations ; 27 cm. |
| Bibliography: | Includes bibliographical references. |
| Action Note: | committed to retain |