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

Author: Strand, Torstein

Year: 1954

Degree: Engineer's thesis

Advisor: Lagerstrom, Paco A.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/Y3KY-N097

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.

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