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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
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.
Has a power-off stall speed which does not exceed 24 knots (44 km/h; 28 mph) calibrated airspeed [1] Certification.
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
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.
Obstacles – An airplane must be able to take off and gain enough height to clear all obstacles and terrain beyond the end of the runway. The maximum weight at which a takeoff may be attempted, taking into account the above factors, is called the maximum permissible takeoff weight, maximum allowed takeoff weight or regulated takeoff weight.