Citation
Strand, Torstein (1954) Minimum drag due to lift for a delta wing with sonic leading edges. Engineer's thesis, California Institute of Technology. doi:10.7907/Y3KY-N097. https://resolver.caltech.edu/CaltechETD:etd-12122003-094215
Abstract
Using linearized theory a close approximation to the optimum camber and twist distribution of a Delta wing of zero thickness with sonic leading edges has been obtained.
The optimum wing has a camber line that is negative over the front quarter of the total planform area and is positive over the remaining area. A certain amount of washout is exhibited.
Compared to the flat plate a saving in induced drag of slightly over 7 percent is shown. The leading edges are relieved of a considerable portion of the total lift. It is shown that this lift has been re-distributed over the central part of the wing.
| Item Type: | Thesis (Engineer's thesis) |
|---|---|
| Degree Grantor: | California Institute of Technology |
| Division: | Engineering and Applied Science |
| Major Option: | Aeronautics |
| Thesis Availability: | Public (worldwide access) |
| Research Advisor(s): |
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| Group: | GALCIT |
| Thesis Committee: |
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| Defense Date: | 1 January 1954 |
| Record Number: | CaltechETD:etd-12122003-094215 |
| Persistent URL: | https://resolver.caltech.edu/CaltechETD:etd-12122003-094215 |
| DOI: | 10.7907/Y3KY-N097 |
| Default Usage Policy: | No commercial reproduction, distribution, display or performance rights in this work are provided. |
| ID Code: | 4956 |
| Collection: | CaltechTHESIS |
| Deposited By: | Imported from ETD-db |
| Deposited On: | 15 Dec 2003 |
| Last Modified: | 20 Dec 2019 19:45 |
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