ESDU Aero A.06.01.01 presents graphs plotting the rolling moment derivative as a function of aspect ratio, quarter-chord sweep angle, section lift-curve slope at the required Mach number, and Prandtl-Glauert compressibility factor. Four graphs are given for taper ratios of 0, 0.25, 0.5 and 1, and they were derived from Weissinger's simplified lifting-surface theory extended to cover the effects of viscous, compressible flow over wings of finite thickness provided the flow is attached. The curves predict the rolling moment coefficient to within 10 per cent for lift coefficients up to 0.5 and up to the critical Mach number.