ESDU 92024 applies to a parallel-sided axisymmetric body with a truncated rear end and a straight-tapered mid-set wing in subsonic or supersonic flow at low angles of attack. The wing may have moderate trailing-edge sweep of up to 10 degrees. The method is that of Pitts, Nielsen and Kaatari (NASA Rep. 1307) expanded and adapted. The calculation of the aerodynamic centre requires the pitching-moment-curve slope for the body alone (for which ESDU 89008 or 90034 may be used), the wing-alone lift-curve slope (for which at subsonic speeds ESDU 70011 may be used or supersonically ESDU 70012), and the lift-curve slope of the configuration together with interference factors for the effect of body lift on the wing and wing lift on the body (for which ESDU 91007 may be used). The other quantity required is the aerodynamic centre of the interference load, for which this document provides both graphically and as a complete set of equations the required data. For missile-type configurations the method is accurate to within 2 per cent of body length. The use of the method is illustrated by means of a fully worked example. For configurations with smoothly tapered afterbodies, such as found on transport aircraft, ESDU 76015 provides a method for subcritical speeds.