The performance of an aircraft is of extreme importance for its success. Much is invested in the aircraft industry to improve performance by the order of percents. The design of the conventional configuration of commercial aircraft composed by a tube fuselage, a cantilever wing, a vertical and a horizontal tail, has been improved over the decades since its introduction in the 1950s, and it might be unlikely that great improvements should occur without drastic changes. A non conventional configuration of aircraft is studied and compared to the conventional configuration in order to assess it. It is the truss-braced wing aircraft, which is very similar to the cantilever configuration, but for a truss connecting the wing to the fuselage. This truss reduces the bending moment of the wing and, consequently, its structural weight. Alternatively, the wing span could be increased, or even the wing thickness decreased, without great weight penalties. This combination of geometric changes has the potential to reduce drag. Parametric analyses are conducted regarding the mass, drag and aeroelastic characteristics of the truss-braced wing configuration and compared against the conventional configuration, based on regional aircraft dimensions. Drag and mass models appropriate for the truss-braced wing configuration are applied. An 11% drag reduction is observed for the truss-braced wing when compared to a conventional aircraft wing of the same mass. If a strut braced wing of aspect ratio 14 is considered, a 7% reduction in drag is observed and a 63% reduction in structural mass is observed when compared to a cantilever wing of aspect ratio 14.