Minimum Drag Due to Lift for a Delta Wing with Sonic Leading Edges

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)
Subject Keywords:	Aeronautical Engineering
Degree Grantor:	California Institute of Technology
Division:	Engineering and Applied Science
Major Option:	Aeronautics
Thesis Availability:	Public (worldwide access)
Research Advisor(s):	Lagerstrom, Paco A.
Group:	GALCIT
Thesis Committee:	Unknown, Unknown
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:	13 Jun 2023 23:14

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