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


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.


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.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1954
Record Number:CaltechETD:etd-12122003-094215
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4956
Deposited By: Imported from ETD-db
Deposited On:15 Dec 2003
Last Modified:13 Jun 2023 23:14

Thesis Files

PDF (Strand_t_1954.pdf) - Final Version
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