An electric vertical takeoff and landing (eVTOL) aircraft (100; 400; 800) comprising: a fuselage (102; 402; 802); a wing (104; 404; 804) connected to the fuselage (102; 402; 802); first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) connected to the wing (104; 404; 804) on opposite sides of the fuselage (102; 402; 802), wherein at least a portion of each of the first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) and a first portion of the wing (114a, 114b; 404a, 404b, 414a, 414b) are tiltable between a first position in which the aircraft (100; 400; 800) is in a hover mode and a second position in which the aircraft (100; 400; 800) is in a cruise mode, and wherein a second portion of the wing is not tiltable; at least one additional electric motor disposed in the fuselage (102; 402; 802) for generating rotational power; and a driveshaft connected to the at least one additional electric motor for transferring the rotational power from the at least one additional electric motor to the first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b); wherein each of the propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) includes: a pylon (130a, 130b); a rotor assembly (132a, 132b) comprising a plurality of rotor blades (134a, 134b); and at least one electric motor, wherein each of the at least one electric motor is disposed in the pylon (130a, 130b) of the propulsion system; and wherein the first portion of the wing (114a, 114b; 404a, 404b, 414a, 414b) comprises wing extensions (114a, 114b; 414a, 414b) disposed outboard of the pylons (130a, 130b). a fuselage (102; 402; 802); a wing (104; 404; 804) connected to the fuselage (102; 402; 802); first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) connected to the wing (104; 404; 804) on opposite sides of the fuselage (102; 402; 802), wherein at least a portion of each of the first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) and a first portion of the wing (114a, 114b; 404a, 404b, 414a, 414b) are tiltable between a first position in which the aircraft (100; 400; 800) is in a hover mode and a second position in which the aircraft (100; 400; 800) is in a cruise mode, and wherein a second portion of the wing is not tiltable; at least one additional electric motor disposed in the fuselage (102; 402; 802) for generating rotational power; and a driveshaft connected to the at least one additional electric motor for transferring the rotational power from the at least one additional electric motor to the first and second propulsion systems (112a, 112b; 412a, 412b; 812a; 812b); wherein each of the propulsion systems (112a, 112b; 412a, 412b; 812a; 812b) includes: a pylon (130a, 130b); a rotor assembly (132a, 132b) comprising a plurality of rotor blades (134a, 134b); and at least one electric motor, wherein each of the at least one electric motor is disposed in the pylon (130a, 130b) of the propulsion system; and a pylon (130a, 130b); a rotor assembly (132a, 132b) comprising a plurality of rotor blades (134a, 134b); and at least one electric motor, wherein each of the at least one electric motor is disposed in the pylon (130a, 130b) of the propulsion system; and wherein the first portion of the wing (114a, 114b; 404a, 404b, 414a, 414b) comprises wing extensions (114a, 114b; 414a, 414b) disposed outboard of the pylons (130a, 130b).