A method of selecting the thickness, hollowness, and size of a supersonic wing for least drag and sufficient bending strength at specified flight conditions

James L. Amick
naca-tn-2754
Jul 1952


This paper considers a wing-selection problem sometimes encountered in the preliminary design of supersonic airplanes and missiles. The problem is to determine the span, section thickness ratio, and skin thickness or hollowness ratio of the wing of least drag when the plan form, section shape, wing lift requirement, and flight conditions are assumed known.

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