ESDU 91042 presents a method that applies to delta, cropped delta, or rectangular wings mounted on an axisymmetric body at mid-height. It applies to Mach numbers between 1.2 and 5 to configurations with thin, sharp-edged wings with aspect ratio between 0.2 and 4 at angles of attack up to 60 degrees. The method takes the isolated wing normal force (from ESDU 90013), factored to account for body interference on the wing and wing interference on the body (using ESDU 91007) and to account for interference from the body vortices, and adds the body contribution (from ESDU 89014 or 90034). The vortex interference factor is provided graphically and depends on the point of separation of the vortices for which another graph provides data. The method applies for zero or near zero roll angle to both cruciform and monoplane wings. When predicted values were compared with experimental values extracted from the literature an accuracy of 10 per cent was indicated. This is illustrated for results in the angle of attack range of 20 to 25 degrees, and the ranges of experimental parameters used are tabulated. A worked example illustrates the use of the method.