ESDU 90010 provides a method that applies to a rigid aircraft at low angles of attack and relies on summing the separate contributions of the body@ wing and tailplane with an allowance for the interference effect of the body on the wing. The body contribution to the pitching moment derivative is calculated from a semi-empirical equation in which the body lift-curve slope from slender body theory is modified for body fineness ratio and cross-section shape and for afterbody geometry. The body contribution to the lift derivative is negligible. For the wing contribution to both derivatives@ strip theory is also modified empirically for straight-tapered wings while for delta and cropped-delta wings it is found that data derived from Multhopp's lifting- line theory can be applied directly. Other wing planforms are converted to straight-tapered through the equivalent wing concept of ESDU 76003. The tailplane contribution is found most-closely to match the available data if it is treated as an isolated surface (with lift-curve slope derived from ESDU 70011). The body interference on the wing is accounted for by the use of the gross planform and a shift in aerodynamic centre position for the body carry-over lift. The accuracy of the predictions is discussed@ and sketches of experimental results plotted against predictions are given for the moment derivative@ for body and wing alone and for wing-body combinations. Two worked examples@ one for a typical transport configuration and one for a typical interceptor aircraft@ illustrate the use of the methods.