Strand, Torstein (1954) Minimum drag due to lift for a delta wing with sonic leading edges. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-12122003-094215
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|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1954|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||15 Dec 2003|
|Last Modified:||26 Dec 2012 03:13|
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