ESDU Aero A.S.06.03.02 presents graphs plotting the ratio of the rolling moment derivative for wing alone to that for the wing in the presence of a body as a function of wing aspect ratio, the ratio of body diameter to wing span, and compressibility factor. Two graphs are given, for delta and rectangular wings. They are based on slender wing theory and on calculations in which the body on the wing is represented by a source distribution. For the rectangular wing, when the product of the compressibility factor and the aspect ratio is zero, the method is restricted to flows in which the Mach line from the wing root leading edge does not cross the tip. Comparison of predictions by the method with experimental data suggests it is accurate to within 7 per cent. It is suggested that for other planforms a similar trend with the ratio of body diameter to wing span may be assumed. The derivative for the wing alone may be found from ESDU Aero A.S.06.03.01.