Drag due to lift at Mach numbers up to 2.0

In NACA RM L53I15a, 1953 and NACA RM A53H18a, 1953,it has been shown that, if the "area rule" is utilized properly, it is possible to obtain values of zero-life drag which, for a wide variety of wing-fuselage configurations,approach that for the basic fuselage alone. This fact makes the selection of a wing less dependent on its zero-life drag and therefore allows a wider range of wings to be considered with regard to drag due to lift. The purpose of this paper therefore is to discuss the effect of wing geometry on the drag due to lift at Mach numbers up to 2.0 and the effect of application of the area rule on the drag at lifting conditions.