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 (24a, 24b, 24c, 24d) including a plurality of second fan blades (34a, 34b, 34c, 34d), the second fan assemblies (24a, 24b, 24c, 24d) 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 (30, 34a, 34b, 34c, 34d); wherein, the first fan blades have a larger rotational inertia than the second fan blades (34a, 34b, 34c, 34d); wherein, the central fan forms a rotor disk and the second fan assemblies (24a, 24b, 24c, 24d) are disposed outboard of the rotor disk of the central fan; wherein the second fan blades (34a, 34b, 34c, 34d) are formed from a different and lighter material than the first fan blades; and wherein, the second fan blades (34a, 34b, 34c, 34d) 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 (24a, 24b, 24c, 24d) including a plurality of second fan blades (34a, 34b, 34c, 34d), the second fan assemblies (24a, 24b, 24c, 24d) 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 (30, 34a, 34b, 34c, 34d); wherein, the first fan blades have a larger rotational inertia than the second fan blades (34a, 34b, 34c, 34d); wherein, the central fan forms a rotor disk and the second fan assemblies (24a, 24b, 24c, 24d) are disposed outboard of the rotor disk of the central fan; wherein the second fan blades (34a, 34b, 34c, 34d) are formed from a different and lighter material than the first fan blades; and wherein, the second fan blades (34a, 34b, 34c, 34d) 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 (24a, 24b, 24c, 24d) including a plurality of second fan blades (34a, 34b, 34c, 34d), the second fan assemblies (24a, 24b, 24c, 24d) 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 (30, 34a, 34b, 34c, 34d); wherein, the first fan blades have a larger rotational inertia than the second fan blades (34a, 34b, 34c, 34d); wherein, the central fan forms a rotor disk and the second fan assemblies (24a, 24b, 24c, 24d) are disposed outboard of the rotor disk of the central fan; wherein the second fan blades (34a, 34b, 34c, 34d) are formed from a different and lighter material than the first fan blades; and wherein, the second fan blades (34a, 34b, 34c, 34d) 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.