Minimum drag due to lift for a delta wing with sonic leading edges

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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Bibliographic Details
Main Author: Strand, Torstein
Format: Others
Published: 1954
Online Access: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>

Internet

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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