A rotary wing aircraft that extends along a roll axis between a nose region and an aft region, comprising: at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition of the rotary wing aircraft; and a flight control system that is configured to control, in a transition phase from the hover condition to the forward flight condition: the at least one propulsion device for generating forward thrust, and the at least one first electric machine and the at least one second electric machine to operate in a closed loop configuration with the at least one first single-blade rotor and the at least one second single-blade rotor for braking the at least one first single-blade rotor and the at least one second single-blade rotor down to a rotation speed close to zero, wherein the flight control system is configured to control, in the transition phase, the at least one first electric machine for operation in the motor mode and the at least one second electric machine for operation in generator mode. at least one first single-blade rotor and at least one second single-blade rotor which are spaced apart from each other along the roll axis; at least one first electric machine and at least one second electric machine which are at least configured to drive in motor mode the at least one first single-blade rotor and the at least one second single-blade rotor for generating lift in hover condition of the rotary wing aircraft; at least one propulsion device that is at least configured to generate forward thrust in forward flight condition of the rotary wing aircraft; a fixed-wing arrangement that is at least configured to provide lift in the forward flight condition of the rotary wing aircraft; and a flight control system that is configured to control, in a transition phase from the hover condition to the forward flight condition: the at least one propulsion device for generating forward thrust, and the at least one first electric machine and the at least one second electric machine to operate in a closed loop configuration with the at least one first single-blade rotor and the at least one second single-blade rotor for braking the at least one first single-blade rotor and the at least one second single-blade rotor down to a rotation speed close to zero, the at least one propulsion device for generating forward thrust, and the at least one first electric machine and the at least one second electric machine to operate in a closed loop configuration with the at least one first single-blade rotor and the at least one second single-blade rotor for braking the at least one first single-blade rotor and the at least one second single-blade rotor down to a rotation speed close to zero, wherein the flight control system is configured to control, in the transition phase, the at least one first electric machine for operation in the motor mode and the at least one second electric machine for operation in generator mode.