METHOD FOR DESIGNING SHAPE OF FUSELAGE OF SUPERSONIC AIRCRAFT, SUPERSONIC AIRCRAFT PRODUCTION METHOD, AND SUPERSONIC AIRCRAFT

摘要

[Problem] To improve design accuracy and reduce design time in the process of matching the equivalent cross-sectional area of the design shape of a supersonic aircraft with a target equivalent cross-sectional area in the sonic boom reduction method based on the equivalent cross-sectional area. [Solution] In this technology: the initial shape of the fuselage and the target equivalent cross-sectional area of the fuselage are set; a near-field pressure waveform for the initial shape of the fuselage on the assumption that the supersonic aircraft flew at cruising speed is estimated; an equivalent cross-sectional area is evaluated from the estimated near-field pressure waveform for the initial shape of the fuselage; a Mach plane according to the cruise speed is set; and the design curve corresponding to an initial curve where the initial shape of the fuselage and the Mach plane intersect is set on the Mach plane so that the equivalent cross-sectional area approaches the target equivalent cross-sectional area. Then the shape of the fuselage is designed on the basis of the design curve.