Lifting Surface Theory for Wing-Fuselage Combinations

A lifting-surface method has been developed that accounts for the presence of the fuselage. Wing and fuselage chordwise and spanwise loadings and moments are determined. Also, aerodynamic-center location and overall lift and moment coefficients are calculated. The wing may have variable camber and twist as well as partial-span control surfaces, and its vertical position is not restricted. A modified vortex-lattice lifting-surface theory is used as the basis of the method. The modification of the lattice theory consists in eliminating the spanwise and chordwise loading functions. Such a modification eliminates many restrictions peculiar to loading-function methods. A generous number of comparisons of the present method with analytic results shows that elimination of loading functions is justified.