Minimum drag due to lift for a delta wing with sonic leading edges
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 rem...
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ndltd-CALTECH-oai-thesis.library.caltech.edu-49562019-12-21T03:05:20Z Minimum drag due to lift for a delta wing with sonic leading edges Strand, Torstein 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. 1954 Thesis NonPeerReviewed application/pdf https://thesis.library.caltech.edu/4956/1/Strand_t_1954.pdf https://resolver.caltech.edu/CaltechETD:etd-12122003-094215 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 <https://resolver.caltech.edu/CaltechETD:etd-12122003-094215> https://thesis.library.caltech.edu/4956/ |
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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. |
| author |
Strand, Torstein |
| spellingShingle |
Strand, Torstein Minimum drag due to lift for a delta wing with sonic leading edges |
| author_facet |
Strand, Torstein |
| author_sort |
Strand, Torstein |
| title |
Minimum drag due to lift for a delta wing with sonic leading edges |
| title_short |
Minimum drag due to lift for a delta wing with sonic leading edges |
| title_full |
Minimum drag due to lift for a delta wing with sonic leading edges |
| title_fullStr |
Minimum drag due to lift for a delta wing with sonic leading edges |
| title_full_unstemmed |
Minimum drag due to lift for a delta wing with sonic leading edges |
| title_sort |
minimum drag due to lift for a delta wing with sonic leading edges |
| publishDate |
1954 |
| url |
https://thesis.library.caltech.edu/4956/1/Strand_t_1954.pdf 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 <https://resolver.caltech.edu/CaltechETD:etd-12122003-094215> |
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AT strandtorstein minimumdragduetoliftforadeltawingwithsonicleadingedges |
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1719304298496524288 |