Compared to subsonic civil aircraft, one of the most critical factors restricting the market operation of supersonic civil aircraft is the sonic boom issue. For supersonic civil aircraft, when performing land-based flight missions, determining the cruising flight state parameters requires comprehensive consideration of aerodynamic characteristics, engine performance, flight altitude, mission requirements, and economic factors, while also taking into account their impact on the aircraft's sonic boom characteristics to minimize ground-level sonic boom loudness during cruising. For this purpose, a study on the sensitivity of flight state parameters to sonic booms was conducted: first, based on the modified linearized sonic boom prediction theory, the influencing factors of ground-level sonic booms during supersonic civil aircraft cruising were analyzed. Then, using a sonic boom prediction method based on CFD numerical simulation, a sensitivity analysis of flight state parameters regarding sonic booms was performed. The findings from the study are as follows: When the cruising weight is constant, within the calculated cruising altitude range, lower sonic boom design Mach numbers result in relatively low ground-level sonic boom loudness during cruising. Under conditions of low sonic boom design Mach numbers and cruising altitudes, within the calculated angle-of-attack range, ground-level sonic boom loudness decreases nonlinearly as the angle of attack reduces, with a corresponding decrease in cruising weight. Additionally, under conditions of low sonic boom design Mach numbers and cruising angles of attack, within the calculated altitude range, ground-level sonic boom loudness decreases approximately linearly with increasing altitude. Specifically, for every 1000 m increase in altitude, the sonic boom value reduces by about 1.7 PLdB, accompanied by a decrease in cruising weight. Furthermore, under conditions of low sonic boom design cruising altitudes and cruising angles of attack, within the calculated Mach number range, ground-level sonic boom loudness differences are minimal near the cruising Mach number, resulting in the lowest ground-level sonic boom loudness. This research provides valuable insights into optimizing flight parameters to mitigate sonic boom effects, thereby facilitating the practical application of supersonic civil aircraft.