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The first derivative of the A320 was the Airbus A321, also known as the Stretched A320, A320-500 and A325. [9] [25] Its launch came on 24 November 1988 after commitments for 183 aircraft from 10 customers were secured. [9] [26] The aircraft was to be a minimally changed derivative, apart from minor wing modifications and the fuselage stretch ...
Maximum flap extended speed. [7] [8] [9] V FTO: Final takeoff speed. [7] V H: Maximum speed in level flight at maximum continuous power. [7] [8] [9] V LE: Maximum landing gear extended speed. This is the maximum speed at which a retractable gear aircraft should be flown with the landing gear extended. [7] [8] [9] [20] V LO: Maximum landing gear ...
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
II-5-1-3 Pilots may not use a lower category than the one certified, but may choose to use a higher category for higher speed approaches. [2] The maximum permitted speed for visual manoeuvring is significantly higher than the threshold speed. Additional speed ranges are specified for other segments of the approach. [1]: Table II-5-1-2
The Airbus A320neo family is an incremental development of the A320 family of narrow-body airliners produced by Airbus.The A320neo family (neo being Greek for "new", as well as an acronym for "new engine option") is based on the enhanced variant of the previous generation A319, A320, and A321, which was then retrospectively renamed the A320ceo family (ceo being an acronym for "current engine ...
The right side of the graph represents the maximum speed of the aircraft. This is typically sloped in the same manner as the stall line due to air resistance getting lower at higher altitudes, up to the point where an increase in altitude no longer increases the maximum speed due to lack of oxygen to feed the engines.
The performance data for landing an aircraft can be obtained from the aircraft's flight manual or pilot's operating handbook. It will state the distance required to bring the aircraft to a stop under ideal conditions, assuming the aircraft crosses the runway threshold at a height of 50 ft, at the correct speed.
As stalling is due to wing loading and maximum lift coefficient at a given altitude and speed, this limits the turning radius due to maximum load factor. At Mach 0.85 and 0.7 lift coefficient, a wing loading of 50 lb/sq ft (240 kg/m 2 ) can reach a structural limit of 7.33 g up to 15,000 feet (4,600 m) and then decreases to 2.3 g at 40,000 feet ...