The conceptual design of a low-boom and low-drag supersonic aircraft remains a challenge despite significant progress in recent years. Inverse design using reversed equivalent area and adjoint methods has been demonstrated to be effective in shaping the ground signature propagated from computational fluid dynamics off-body-pressure distributions. However, there is still a need to reduce the computational cost in the early stages of design to obtain a baseline that is feasible for low-boom shaping, and in the search for a robust low-boom design over the entire sonic-boom footprint. The proposed design method addresses the need to reduce the computational cost for robust low-boom design by using surface-pressure distributions from computational fluid dynamics solutions to shape sonic-boom ground signatures propagated from computational fluid dynamics off-body pressure.