Effect of fuselage and engine nacelles on some aerodynamic properties of an airplane wing

摘要

With the aid of the method of J. Lotz, the writer undertook to solve theoretically the lift distribution along the span of an airplane wing, when the outline of the wing is uneven. This problem arises in the case of a mid-wing monoplane with embedded engine nacelles. The fuselage and the nacelles were considered as aerodynamically profiled, that is, as lift-producing parts. The task was therefore to determine not only the disturbance caused by the fuselage and nacelles, but also their share in the total lift of the wing. After the above-mentioned calculations, the induced velocity, due to the vortex system by which the wing was replaced, was also calculated and measured at the points corresponding, in an airplane, to the location of the horizontal tail surfaces.