Driven aircraft, in particular an aircraft designed as a flying wing and/or having a low radar signature

1. An aircraft, comprising:

a fuselage;

wing body;

a jet engine; and

at least one drive flow passage, which runs from an air inlet, which is directed forward on a body surface of the wing body, via the jet engine through the wing body to a jet nozzle that opens towards the rear on the body surface,

wherein at least a part of the jet engine is arranged upstream of the air inlet seen in a flight direction of the aircraft and the at least one drive flow passage has curvature sections configured to couple the air inlet to the jet engine,

wherein the entire jet engine, seen in the flight direction, is arranged upstream of the center of gravity of the aircraft or upstream of a geometric centroid of a contour of the body seen from above.

2. The aircraft according to claim 1 , wherein the entire jet engine is arranged upstream of the air inlet seen in the flight direction of the aircraft.

3. The aircraft according to claim 1 , wherein the air inlet, seen in the flight direction, is arranged downstream of a center of gravity of the aircraft or downstream of a geometric centroid of a contour of the wing body seen from above.

4. The aircraft according to claim 1 , wherein an opening of the air inlet is delimited on its outside by a region of the wing body tapering forwards to a point.

5. The aircraft according to claim 1 , wherein the at least one drive flow passage is arranged as two drive flow passages arranged symmetrically to a vertical longitudinal center plane of the wing body.

6. The aircraft according to claim 1 , wherein the at least one drive flow passage comprises:

a first curvature section, adjoining the air inlet, the first curvature section configured for flow deflection,

a first longitudinal section, adjoining the first curvature section and extending in the flight direction, the first longitudinal section configured for flow guidance,

a second curvature section, adjoining the first longitudinal section, the second curvature section configured for flow deflection, and

a second longitudinal section, adjoining the second curvature section and extending against the flight direction, the second longitudinal section configured for flow guidance.

7. The aircraft according to claim 6 , wherein the first longitudinal section contains the jet engine.

8. The aircraft according to claim 6 , wherein at least one of the curvature sections has a first course region configured for flow deflection about a first angle and a second course region directly adjoining it with opposite curvature direction configured for flow deflection about a second angle, which is smaller than the first angle.