Abstract
Nonlinear area ruling procedures based on the transonic slender body and lift-dominated theories are described as a means of providing low-cost wave drag estimates and optima for basepoint definition. The computational implementation is capable of accurately predicting drag rise of realistic configurations and shows applicability to moderate supersonic Mach numbers. An analogy between the zero-lift and liftdominated case establishes a basis for sizeable wave drag due to lift reduction through planform and sectional shaping. Results illustrating the potential benefits are shown for a fighter configuration in which a small movement of the maximum thickness location of the equivalent body of revolution with the volume fixed gives a fourfold reduction in zero-lift wave drag. This benefit can be translated into similar reductions in transonic wave drag due to lift.
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