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The flight controls on the Airbus A330, for example, are all electronically controlled and hydraulically activated. Some surfaces, such as the rudder, can also be mechanically controlled. In normal flight, the computers act to prevent excessive forces in pitch and roll. [7] Airbus A321 cockpit Illustration of the air-data reference system on ...
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 operating speed. This is the maximum speed at which the landing gear on a retractable gear aircraft should be extended or retracted. [7] [9] [20] V LOF ...
Additional speed ranges are specified for other segments of the approach. [1]: Table II-5-1-2 Table II-5-1-2 Approach plates generally include visibility requirements up to category D. [ 1 ] : II-5-1-3 While ICAO specify a top speed of 391 km/h for Category E, there exist no aircraft with an approach speed above this.
Cruise altitude is usually where the higher ground speed is balanced against the decrease in engine thrust and efficiency at higher altitudes. Common narrowbodies like the Airbus A320 and Boeing 737NG cruise at Mach 0.78 (450 kn; 830 km/h), [2] [3] while modern widebodies like the Airbus A350 and Boeing 787 cruise at Mach 0.85 (490 kn; 900 km/h).
Lift and drag are the two components of the total aerodynamic force acting on an aerofoil or aircraft.. In aerodynamics, the lift-to-drag ratio (or L/D ratio) is the lift generated by an aerodynamic body such as an aerofoil or aircraft, divided by the aerodynamic drag caused by moving through air.
Many variables affect the landing distance of an aircraft, such as approach speed, weight and the presence of either a tailwind or a headwind. For an Airbus A320, a landing speed of 20 knots (37 km/h; 23 mph) higher than normal can result in as much as a 25% increase in the runway length needed to stop an aircraft.
An increase in weight increases the stall speed of the aircraft. Therefore, the landing approach speed increases as the aircraft's weight increases. The kinetic energy ( 1 / 2 mV 2) that has to be dissipated to stop an aircraft is a function of the mass of the aircraft and the square of its speed at touchdown. The kinetic energy ...
Designing an aircraft that operates across a wide range of speeds, like a modern airliner, requires these competing needs to be carefully balanced for every aircraft design. Swept wings are a practical outcome of the desire to have a low thickness-to-chord ratio at high speeds and a lower one at lower speeds during takeoff and landing .