Multi-engine aircraft having a hybrid propulsion system, comprising • at least a first and a second hybrid-electric propulsion unit (31, 32), each comprising an internal combustion engine (41, 42), a motor-generator unit (71, 72) for transmitting propulsive power to a propulsor (61, 62), • wherein the propulsor (61, 62) is connectable to the internal combustion engine (41, 42) and/or the motor-generator unit (71, 72) for the transmission of drive power, • the first and second motor-generator units (71, 72) are connected to a transmission device for distributing electrical power, • a fuel cell for supplying the first and/or second motor-generator unit (71, 72) with electrical energy, • a controller which is connected to the internal combustion engines (41, 42) and/or the transmission device and/or motor-generator units (71, 72) and/or the fuel cell to control the thermally and electrically generated drive power, • separate fuel tanks (43, 44) for supplying the internal combustion engines (41, 42) with fuel and the fuel cell with cryogenic hydrogen, • an airfoil accommodating the drive units (31, 32) and a fuel tank (43, 44), a fuselage, • wherein the drive unit (31, 32) is formed by a turboprop engine having one respective gas turbine (41, 42) that can be coupled to a speed-reducing gearbox (51, 52) to drive a propeller (61, 62), and • the motor-generator unit (71, 72) can be coupled to the gearbox (51, 52) under the control of the controller depending on the operating mode, characterized in that at least the predominant volume of the fuel tanks (43, 44) for supplying the internal combustion engines (41, 42) is integrated in the airfoil and at least the predominant volume of the fuel tanks for supplying the fuel cell is integrated in a tail region of the fuselage. • at least a first and a second hybrid-electric propulsion unit (31, 32), each comprising an internal combustion engine (41, 42), a motor-generator unit (71, 72) for transmitting propulsive power to a propulsor (61, 62), • wherein the propulsor (61, 62) is connectable to the internal combustion engine (41, 42) and/or the motor-generator unit (71, 72) for the transmission of drive power, • the first and second motor-generator units (71, 72) are connected to a transmission device for distributing electrical power, • a fuel cell for supplying the first and/or second motor-generator unit (71, 72) with electrical energy, • a controller which is connected to the internal combustion engines (41, 42) and/or the transmission device and/or motor-generator units (71, 72) and/or the fuel cell to control the thermally and electrically generated drive power, • separate fuel tanks (43, 44) for supplying the internal combustion engines (41, 42) with fuel and the fuel cell with cryogenic hydrogen, • an airfoil accommodating the drive units (31, 32) and a fuel tank (43, 44), a fuselage, • wherein the drive unit (31, 32) is formed by a turboprop engine having one respective gas turbine (41, 42) that can be coupled to a speed-reducing gearbox (51, 52) to drive a propeller (61, 62), and • the motor-generator unit (71, 72) can be coupled to the gearbox (51, 52) under the control of the controller depending on the operating mode,