Zero lift-drag at mach 1.42, 1.83, and 2.21 of a series of wings with variations of thickness ratio and chord

A series of wing configurations having various spanwise distributions of chord and thickness ratio but having the same effective thickness ratio was subjected to both a theoretical and experimental investigation of the zerolift drag characteristics in the Mach number range from 1.2 to 2.2.Semispan models of the wings were tested in the Langley 4by 4-foot supersonic pressure tunnel at Mach numbers of 1.42, 1.83, and 2.21 and a Reynolds number per foot of 4.3 x lo6.with the theoretical data, and indicate that the chord and thickness distributions may be arranged in such a manner as to provide higher wing volume without a wave drag penalty.An extension of the theoretical analysis indicated that the wave drag of a wing can be significantly affected by relatively minor changes in planform.Results of this experimental investigation were in good agreement