Approximate calculation of maximum lifting properties of wing-body combination

A solution is proposed for calculating the maximum lifting properties of the body-wing combination. A combination of a fuselage with a circular cross-section and a rectangular wing, installed according to the midplane scheme, is considered. It has been established that the optimal fuselage diameter can exceed 20% and more of the wingspan of the original wing which it have aspect ratio greater than approximately 7. It is also shown that with an increasing wing aspect ratio, the excess of the lift properties of the fuselage-wing combination over the original wing increases. This excess can reach 12% and more for wing aspect ratio greater than 10.