Abstract:
Some interference effects between fuselage and wing are studied for two classes of configurations. The fuselage is an infinite cylinder of circular cross section with the axis parallel to the main stream. The wings have constant chord and infinite span, they are attached in a midwing position to the fuselage. In the first group of configurations, the wings are non-lifting and have the same symmetrical section shape across the span; in the second group the wings are warped such that, when attached to the fuselage, they produce the same chordwise load distribution across the span. For the first class of wings, the Report deals with the change of the pressure distribution caused by the body interference, and, for the second class, with the change of the required shape of the mean surface. The problems are solved by considering first the flow field past a single kinked infinite swept source line or a vortex, in the presence of the fuselage, and by computing some velocity components. From the tabulated values of these velocity components, the interference velocities for wings of given thickness distribution or load distribution can be derived by chordwise integration. A few examples demonstrate how the interference effects can vary with the angle of sweep, with the ratio between body radius and wing chord and with the spanwise distance from the wing-body junction. The present Report summarises the work published previously in four separate reports.
