A rotorcraft compri sing: a fuselage ; a tailboom extending from the fuselage ; a tail rotor rotatably coupled to an aft portion of the tailboom and configured to provide yaw control for the rotorcraft ; a propulsion system coupled to the fuselage , the propulsion system including: a first fan assembly including a central fan and a mast , the central fan including a plurality of first fan blades ; a plurality of second fan assemblies including a plurality of second fan blades , the second fan assemblies are radially symmetric about the mast of the central fan assembly; and a drive system adapted to provide torque to the first and second fan blades ; wherein, the first fan blades have a larger rotational inertia than the second fan blades ; wherein, the central fan forms a rotor disk and the second fan assemblies are disposed outboard of the rotor disk of the central fan; wherein the second fan blades are formed from a different and lighter material than the first fan blades ; and wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft . a fuselage ; a tailboom extending from the fuselage ; a tail rotor rotatably coupled to an aft portion of the tailboom and configured to provide yaw control for the rotorcraft ; a propulsion system coupled to the fuselage , the propulsion system including: a first fan assembly including a central fan and a mast , the central fan including a plurality of first fan blades ; a plurality of second fan assemblies including a plurality of second fan blades , the second fan assemblies are radially symmetric about the mast of the central fan assembly; and a drive system adapted to provide torque to the first and second fan blades ; wherein, the first fan blades have a larger rotational inertia than the second fan blades ; wherein, the central fan forms a rotor disk and the second fan assemblies are disposed outboard of the rotor disk of the central fan; wherein the second fan blades are formed from a different and lighter material than the first fan blades ; and wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft . a first fan assembly including a central fan and a mast , the central fan including a plurality of first fan blades ; a plurality of second fan assemblies including a plurality of second fan blades , the second fan assemblies are radially symmetric about the mast of the central fan assembly; and a drive system adapted to provide torque to the first and second fan blades ; wherein, the first fan blades have a larger rotational inertia than the second fan blades ; wherein, the central fan forms a rotor disk and the second fan assemblies are disposed outboard of the rotor disk of the central fan; wherein the second fan blades are formed from a different and lighter material than the first fan blades ; and wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft . <EOS>