Сверхзвуковой Гражданский Самолет С Пониженным Уровнем Звукового Удара

The paper presents the results of numerical investigation of the effect of relative area of the leading wing and nose part shape on the forming middle zone of the sonic boom (minimization region) with the tandem-location of the wings of the fuselage. It is demonstrated that the modified power-law body used as the nose part provides the middle-zone length above the cruising flight altitude, as well as the distance between the head and intermediate shock waves, which permits significantly reducing the sonic boom affect.