Aircraft comprising at least one fuselage , which has a front fuselage section and a rear fuselage section , at least one wing provided in the region of the front fuselage section , at least one first drive device provided in the region of the front fuselage section and/or on the wing and configured to generate propulsion and/or lift, at least one tailplane which is configured to rotate and/or stabilize the aircraft about a transverse axis of the aircraft during flight, wherein the tailplane - is attached to the fuselage , and the rear fuselage section can be pivoted relative to the front fuselage section about a pivot axis (S2) which is substantially parallel to the transverse axis of the aircraft, and/or - is attached to at least one support element which is mounted on the fuselage and/or on the wing and which can be pivoted relative to the fuselage and/or to the wing about a pivot axis (S1) which is substantially parallel to the transverse axis of the aircraft, at least one second drive device provided on the tailplane and/or on the rear fuselage section and/or on the at least one support element and configured to generate lift, and a control device configured to control the aircraft in a first hovering mode, in which the aircraft can take off and/or land, such that - the longitudinal axis of the aircraft (L) is substantially vertical, - the rear fuselage section or the at least one support element is pivoted into a second orientation which is substantially perpendicular to the longitudinal axis (L) of the aircraft, and - the lift of the aircraft is generated by the first and second drive device , characterized in that the control device is further configured to control the aircraft in a second hovering mode, in which the aircraft can take off and/or land, such that - the longitudinal axis (L) of the aircraft is substantially vertical, - the rear fuselage section or the at least one support element is pivoted into a first orientation which is substantially parallel to the longitudinal axis (L) of the aircraft, and - the lift of the aircraft is generated, in particular only, by the first drive device . - is attached to the fuselage , and the rear fuselage section can be pivoted relative to the front fuselage section about a pivot axis (S2) which is substantially parallel to the transverse axis of the aircraft, and/or - is attached to at least one support element which is mounted on the fuselage and/or on the wing and which can be pivoted relative to the fuselage and/or to the wing about a pivot axis (S1) which is substantially parallel to the transverse axis of the aircraft, at least one second drive device provided on the tailplane and/or on the rear fuselage section and/or on the at least one support element and configured to generate lift, and a control device configured to control the aircraft in a first hovering mode, in which the aircraft can take off and/or land, such that - the longitudinal axis of the aircraft (L) is substantially vertical, - the rear fuselage section or the at least one support element is pivoted into a second orientation which is substantially perpendicular to the longitudinal axis (L) of the aircraft, and - the lift of the aircraft is generated by the first and second drive device , characterized in that the control device is further configured to control the aircraft in a second hovering mode, in which the aircraft can take off and/or land, such that - the longitudinal axis (L) of the aircraft is substantially vertical, - the rear fuselage section or the at least one support element is pivoted into a first orientation which is substantially parallel to the longitudinal axis (L) of the aircraft, and - the lift of the aircraft is generated, in particular only, by the first drive device . <EOS>