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Huntair Pathfinder Mark 1 ultralight. Ultralight aviation (called microlight aviation in some countries) is the flying of lightweight, 1- or 2-seat fixed-wing aircraft. Some countries differentiate between weight-shift control and conventional three-axis control aircraft with ailerons, elevator and rudder, calling the former "microlight" and the latter "ultralight".
A typical light aircraft: the Cessna 172 With a maximum gross takeoff weight of 12,500 lbs, the DHC-6 Twin Otter is an example of the upper limit of the light aircraft category.
Type MTOW [kg] MLW [tonnes] TOR [m] LR [m] ICAO category FAA category; Antonov An-225: 640,000: 591.7: 3,500: Super: Super Scaled Composites Model 351 Stratolaunch
Has a power-off stall speed which does not exceed 24 knots (44 km/h; 28 mph) calibrated airspeed [1] Certification.
A maximum take-off weight of 600 or 650 kg (1,323 or 1,433 lb) for an aircraft intended and configured for operation on water or 560 kg (1,235 lb) for a lighter-than-air aircraft. A maximum stalling speed in the landing configuration (Vso) of 45 kn (83 km/h) CAS. Maximum of two occupants, including the pilot. A fixed landing gear.
Take-off to 50 ft (15 m) Landing from 50 ft (15 m) Notes AAC Angel: US 1984 Utility Production 1,404 ft (428 m) 1,046 ft (319 m) [1] Aircraft Industries L 410 NG: Czech Republic 2015 Utility Production 1,936 ft (590 m) 1,969 ft (600 m) [2] Antonov An-14: Soviet Union 1958 Transport Production 656 ft (200 m) 985 ft (300 m) [3] Antonov An-72
Most modern and lightweight airplane seats are somewhere between seven and 10 kilograms (15-22 pounds) per passenger today. Any weight that can be saved means reducing the fuel needed to carry it.
This is a list of fixed-wing aircraft capable of vertical take-off and landing arranged under manufacturer. The list excludes helicopters, including compound helicopters and gyrocopters, because they are assumed to have this capability. For more detail on subtypes of VTOL, see List of tiltrotor aircraft