The invention relates to an aircraft comprising a fuselage and at least two substantially hollow cylindrical lifting bodies which are applied to the fuselage and comprise a plurality of rotor blades which extend over the periphery of the lifting bodies, the periphery of the lifting bodies being partially covered by at least one tail surface. The aim of the invention is to provide an aircraft with an extremely high degree of maneuverability, compact dimensions and economy of fuel. To this end, the lifting bodies are driven by at least one drive unit and respectively comprise a cylindrical axis which is substantially parallel to a longitudinal axis (1a) of the aircraft.