ESDU 89042:2012

ESDU 89042 gives simple empirical methods of predicting the
change in zero-lift angle and in pitching moment at zero-lift due
to adding a fuselage of approximately circular section to a swept,
cambered and twisted wing. The effects of wing height and of body
asymmetry in the aircraft plane of symmetry are considered. It was
found that the effects of neither Mach number below 0.4 nor
Reynolds number was important. Sketches compare both the predicted
changes and the values for the wing-body combination with
experimental results used in the correlation, and it is found that
zero-lift angle of attack is predicted to within 0.3 degrees and
pitching moment coefficient (based on equivalent (gross) wing area
and aerodynamic mean chord) to within 0.1. A worked example
illustrates the use of the method, using ESDU 87031 and 87001 to
predict wing alone values of zero-lift angle of attack and pitching
moment respectively, although of course experimental values could
be used if available. A computer program of the method is provided
as ESDUpac A8942.