Vertical take-off and landing aircraft

An aircraft, comprising:

• a fuselage;
• a single pair of wings connected to the fuselage or a single wing extending across the fuselage;
• a plurality of rotors connected to the single wing or single pair of wings for providing lift for vertical take-off and landing of the aircraft, wherein the plurality of rotors is four rotors, wherein the plurality of rotors comprises a first outermost rotor on a first side of the fuselage, a second outermost rotor on a second side of the fuselage, a first innermost rotor on the first side of the fuselage, and a second innermost rotor on the second side of the fuselage, wherein each rotor of the plurality of rotors is fixed in position;
• and
• a plurality of proprotors connected to the single wing or single pair of wings and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, wherein the plurality of proprotors is four proprotors;
• wherein each rotor comprises more than two blades,
• each rotor of the plurality of rotors has a rotational axis that is tilted rearward relative to a vertical axis of the aircraft;
• the rotational axis of the first outermost rotor is tilted rearward at a first fixed tilt angle relative to the vertical axis of the aircraft,
• the rotational axis of the second outermost rotor is tilted rearward at a second fixed tilt angle relative to the vertical axis of the aircraft,
• the first and second fixed tilt angles are greater than 0 degrees and less than or equal to 15 degrees,
• wherein the aircraft is a piloted vertical take-off and landing electric aircraft, and
• wherein each of a first innermost proprotor, a first outermost proprotor, a second innermost proprotor, and a second outermost proprotor of the plurality of proprotors is canted away from the fuselage.