| 摘要 |
It is an object of the present invention to provide the entire airplane shape of a supersonic aircraft that can realize low sonic boom characteristics, and that can also minimize wave-drag. In order to achieve both sonic boom suppression and a reduction in wave-drag, the entire airplane shape of the supersonic aircraft of the present invention uses a variable forward swept wing configuration having a mechanism that can vary a forward sweep angle as the main wing configuration, rather than forming the fuselage shape with a blunt nose.
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