The invention belongs to the technical field of
aviation, and particularly relates to a supersonic civil aircraft
layout. According to the supersonic civil aircraft
layout, the engine
nacelle is installed above the rear
fuselage between the wing and the horizontal
tail, the lower portion of the air inlet is shielded by the rear edge of the wing, the lower portion of the air outlet is shielded by the
front edge of the horizontal
tail, shock
waves generated by the engine are prevented from spreading to the ground through the
shielding effect of the wing and the horizontal
tail, and the ground sound explosion
loudness of the aircraft is effectively reduced; the engine and the hanger can perform small-angle pitching deflection around the rotating shaft in the hanger, so that the mounting angle of the engine is adjusted, and the
propulsive efficiency of the engine under the non-design-point working condition is improved; the horizontal tail tip can be folded upwards to provide additional vertical tail capacity during supersonic cruising, loss of vertical tail efficiency during supersonic cruising is made up, and expansion
waves generated by an engine exhaust
nozzle and a horizontal tail are prevented from spreading to the ground. And the wingtip is put down during low-speed take-off and landing, so that a larger horizontal tail area is ensured, and the trimming requirement of a take-off and landing structure is met.