Method of designing an aircraft shape of a supersonic aircraft, method of producing a supersonic aircraft, and supersonic aircraft

A method of producing a supersonic aircraft, the method comprising:

• a) designing an aircraft shape of the supersonic aircraft by performing the following steps:
• calculating an equivalent cross-sectional area distribution, which is a distribution of an equivalent cross-sectional area at a position in an airflow, of an initial shape of the supersonic aircraft at an off-track position;
• calculating a target equivalent cross-sectional area distribution, which is a distribution of a target equivalent cross-sectional area in the airflow, at the off-track position of the supersonic aircraft for reducing sonic booms on a basis of the equivalent cross-sectional area distribution;
• calculating a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution;
• calculating, on the basis of the required additional cross-sectional area distribution, a first required additional cross-sectional area and a second required additional cross-sectional area,
• wherein the first required additional cross-sectional area is a required additional cross-sectional area of a cross-section of the supersonic aircraft on an off-track Mach plane that is a Mach plane at the off-track position, where the cross-sectional shape for calculating the equivalent cross-sectional area of the supersonic aircraft is asymmetric, that extends through an arbitrary position in the airflow direction,
• wherein the second required additional cross-sectional area is a required additional cross-sectional area of a cross-section of the supersonic aircraft on an on-track Mach plane that is a Mach plane at an on-track position, where the cross-sectional shape for calculating the equivalent cross-sectional area of the supersonic aircraft is symmetric, that is located near the off-track Mach plane;
• converting the first required additional cross-sectional area into the second required additional cross-sectional area;
• and
• adding the first required additional cross-sectional area, which is converted to the second required additional cross-sectional area, to the equivalent cross-sectional area distribution of the initial shape of the supersonic aircraft;
• and
• b) manufacturing the supersonic aircraft having the aircraft shape based on a result of the designing of the aircraft shape.