a method for designing a non - waisted fuselage for supersonic wing / fuselage configurations that increases the fuselage volume and improves the supersonic aerodynamic performance compared to a conventional waisted - fuselage configuration . the method entails removing the waisted region of an existing waisted - fuselage configuration by linearly reconstructing cross - sections between the endpoints representing the waisted cross - sectional area portion to create a modified fuselage configuration without waisting . this configuration will have increased fuselage volume and improved supersonic aerodynamic performance . the fuselage camber can then be optimized using non - linear aerodynamic methods to further increase the supersonic aerodynamic performance .