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Reduction Of Drag Due To Lift At Supersonic Speeds

Report Number: WADC TR 54-524 Part 1
Author: Graham, E. W.
Author: Lagerstrom. P. A.
Corporate Author: Douglas Aircraft Company, Inc.
Laboratory: Aeronautical Research Laboratory
Date of Publication: 1954-04
Pages: 10
Contract: AF 33(616)-2170
Project: 1366
Task: 70166
PB Number: PB157269
AD Number: AD0063453

Abstract:
SEVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.


Provenance:
Lockheed Martin Missiles & Fire Control
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