Abstract: The aerodynamic configuration design of low sonic boom is a key technology in the research and development of supersonic civil aircraft. Based on Cartesian inviscid solver, the design and selection of typical civil aircraft configuration for low boom are carried out. The influence of the curvature of fuselage axis, the plane shape of wing on the distribution of near-field overpressure is mainly studied. Finally, a supersonic aircraft aerodynamic configuration with parallel shock design characteristics is selected. On the basis of this aerodynamic configuration, combined with AMDEsign, a flow field sonic boom coupled with optimization design software, under the condition of specified sonic boom signal with low perceived level noise, the large-scale design variable numerical optimization of the supersonic aerodynamic configuration is realized through the efficient reverse design of far-field sonic boom signal, and the perceived noise level is greatly reduced. The optimized configuration shows multiple weak waves. The effectiveness of design techniques has been verified. The research work can provide a positive reference value for the researchers who are engaged in the low sonic boom aerodynamic configuration design, and provide technical support for the future research and development of supersonic civil aircraft.