FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircrafts. Aircraft (1) includes fuselage (2) with engine (8a). Maximum fuselage (2) width is defined in engine (8a) area. Front fuselage fairing and rear fuselage fairing are partially closing engine (8a) and are spaced apart in direction across engine (8a) lengthwise axis, by means of a predetermined fairing displacement, for dynamic air intake (9) determination, through which sucked air flow is supplied to said at least one engine (8a) using air as oxidant in operation.
EFFECT: invention improves aircraft engine protection.
15 cl, 16 dwg
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