Abstract:

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 ESDU 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.