The thesis aims to create a MATLAB program capable of generating a conceptual design for a liquid hydrogen-powered supersonic civilian aircraft at Mach 2, extending its appli- cability to a broader range, specifically between Mach 1.5 and Mach 2.5. The program begins with a statistical analysis of aircraft concepts that do not yet exist due to both regulations that do not permit them and the fact that liquid hydrogen as aircraft fuel is a developing technology. Afterward, all aerodynamic aspects, fuel weight considera- tions, and operational empty weight are calculated. The verification of wing loading and thrust-to-weight ratio requirements is then carried out, concluding with the design of the tanks, which is crucial for an aircraft of this type because LH2 has a much lower density compared to conventional fuels, necessitating larger storage space.