A vertical takeoff and landing, VTOL, aircraft comprising: an elongate fuselage defining a longitudinal axis of the aircraft having a forward passenger compartment; fixed-position port and starboard wings (24a, 24b) extending laterally from the fuselage; an empennage provided with port and starboard elevators (18a, 18b) and rudders (20a, 20b) at an aft end of the fuselage; a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof; a series of port and starboard rotor units (30, 32) each of which includes a pair of opposed rotor blades (30a, 32a), and a motor (30b, 32b) to rotate the rotor blades (30a, 32a) and provide vertical thrust to the aircraft, and a logic control unit, wherein each motor (30b, 32b) includes a motor control unit operatively connected to the motor (30b, 32b); wherein each of the rotor units (30, 32) comprises a rotor position sensor which senses the angular position of the rotor blades relative to the longitudinal axis of the fuselage and issues the position signal to the logic control unit; wherein the logic control unit, in response to a position signal, controllably issues a control signal to the motor control unit which in turn issues a command signal to the individual motors (30b, 32b) and sets an angular position of the pair of opposed rotor blades (30a, 32a) along a position axis relative to the longitudinal axis of the aircraft in response to the logic control unit determining an optimal position of the rotor blades (30a, 32a) of minimum airflow disruption over the fixed-position wings (24a, 24b) during cruise flight operation; and wherein the logic control unit estimates the optimal rotor position in response to measurement of the local airflow, or in response to the aircraft's attitude. an elongate fuselage defining a longitudinal axis of the aircraft having a forward passenger compartment; fixed-position port and starboard wings (24a, 24b) extending laterally from the fuselage; an empennage provided with port and starboard elevators (18a, 18b) and rudders (20a, 20b) at an aft end of the fuselage; a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof; a series of port and starboard rotor units (30, 32) each of which includes a pair of opposed rotor blades (30a, 32a), and a motor (30b, 32b) to rotate the rotor blades (30a, 32a) and provide vertical thrust to the aircraft, and a logic control unit, wherein each motor (30b, 32b) includes a motor control unit operatively connected to the motor (30b, 32b); wherein each of the rotor units (30, 32) comprises a rotor position sensor which senses the angular position of the rotor blades relative to the longitudinal axis of the fuselage and issues the position signal to the logic control unit; wherein the logic control unit, in response to a position signal, controllably issues a control signal to the motor control unit which in turn issues a command signal to the individual motors (30b, 32b) and sets an angular position of the pair of opposed rotor blades (30a, 32a) along a position axis relative to the longitudinal axis of the aircraft in response to the logic control unit determining an optimal position of the rotor blades (30a, 32a) of minimum airflow disruption over the fixed-position wings (24a, 24b) during cruise flight operation; and wherein the logic control unit estimates the optimal rotor position in response to measurement of the local airflow, or in response to the aircraft's attitude.