ESDU Aero B.S.02.03.08 gives curves for the interference wave drag, as a function of freestream Mach number and body geometry, that results from the disturbance to the flow over an afterbody caused by the flow over the forebody if the afterbody is preceded by only a short midbody. The data plotted are for pointed conical and parabolic arc forebodies joined to corresponding afterbodies by midbodies, ducted conical forebodies and truncated afterbodies of equal length and with equal open nose and base areas, also joined by midbodies, and pointed parabolic forebodies and truncated afterbodies with no midbodies. The curves were derived by use of slender-body theory and assume the flow is everywhere supersonic. Data for the wave drag coefficient of afterbodies preceded by an infinite midbody are given in ESDU Aero B.S.02.03.02 and the values of interference wave drag coefficient obtained from the curves here should be added to those values.