Supersonic wave drag of nonlifting delta wings with linearly varying thickness ratio

Arthur Henderson, Jr.
naca-tn-2858
Dec 1952


The supersonic wave drag of a nonlifting, symmetrical, double-wedge-profile, delta wing the thickness ratio of which varies linearly in the spanwise direction is calculated by means of linear theory. In general it is found that a delta wing with linearly varying thickness ratio can have less wave drag than a constant-thickness-ratio delta wing of the same plan form when both wings have either the same projected frontal area or the same internal volume.

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