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): |
|
Group: | GALCIT |
Thesis Committee: |
|
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 |
Thesis Files
![]()
|
PDF (Strand_t_1954.pdf)
- Final Version
See Usage Policy. 696kB |
Repository Staff Only: item control page