A computerized math modeling routine providing approximation of Mach 1.0 aircraft area distribution has been developed to supplement and expedite the preliminary design process. This routine provides information that was heretofore considered to be impractical to produce with the frequency needed in design synthesis. This process is one of integrating dimensional characteristics of selectable components, comparing the results to a desired shape, and determining minimum practical body dimensions using configuration-dependent constraints. This process is of particular value to the mass properties engineer because of the interrelation between area curve shape and aircraft balance.