ESDU 90010:2014

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. A computer program of
the method is provided as ESDUpac A9010.