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  • finde more documentations of the aviation history here: http://www.pegasus-ent.com/index.php The A?rospatiale-BAC Concorde is a turbojet-powered supersonic passenger airliner, a supersonic transport (SST). It was a product of an Anglo-French government treaty, combining the manufacturing efforts of A?rospatiale and the British Aircraft Corporation. First flown in 1969, Concorde entered service in 1976 and continued commercial flights for 27 years. Among other destinations, Concorde flew regular transatlantic flights from London Heathrow (British Airways) and Paris-Charles de Gaulle Airport (Air France) to New York JFK, profitably flying these routes at record speeds, in less than half the time of other airliners. With only 20 aircraft built, their development represented a substantial economic loss, in addition to which Air France and British Airways were subsidised by their governments to buy them. As a result of the types only crash on 25 July 2000 and other factors, its retirement flight was on 26 November 2003. Concordes name reflects the development agreement between the United Kingdom and France. In the UK, any or all of the type—unusual for an aircraft—are known simply as Concorde. The aircraft is regarded by many as an aviation icon. Diskussion in pprune about the CG handling of the BOAC Concorde and many more... http://www.pprune.org/tech-log/423988-concorde-question-4.html http://i303.photobucket.com/albums/nn142/Bellerophon_photos/P8160022-1.jpg General characteristics Crew: 3 (2 Pilots and a flight engineer) Capacity: 92–120 passengers (128 in high-density layout)[N 9] Length: 202 ft 4 in (61.66 m) Wingspan: 84 ft 0 in (25.6 m) Height: 40 ft 0 in (12.2 m) Fuselage internal length: 129 ft 0 in (39.32 m) Fuselage width: maximum of 9 ft 5 in (2.87 m) external 8 ft 7 in (2.62 m) internal Fuselage height: maximum of 10 ft 10 in (3.30 m) external 6 ft 5 in (1.96 m) internal) Wing area: 3,856 ft2 (358.25 m2) Empty weight: 173,500 lb (78,700 kg) Useful load: 245,000 lb (111,130 kg) Powerplant: 4 ? Rolls-Royce/SNECMA Olympus 593 Mk 610 afterburning turbojets Dry thrust: 32,000 lbf (140 kN) each Thrust with afterburner: 38,050 lbf (169 kN) each Maximum fuel load: 210,940 lb (95,680 kg) Maximum taxiing weight: 412,000 lb (187,000 kg) Performance Maximum speed: Mach 2.04 (?1,354 mph, 2,179 km/h, 1,176 knots) at cruise altitude Cruise speed: Mach 2.02 (?1,340 mph, 2,158 km/h, 1,164 knots) at cruise altitude Range: 3,900 nmi (4,488.04 mi, 7,222.8 km) Service ceiling: 60,000 ft (18,300 m) Rate of climb: 5,000 ft/min (25.41 m/s) lift-to-drag: Low speed– 3.94, Approach– 4.35, 250 kn, 10,000 ft– 9.27, Mach 0.94– 11.47, Mach 2.04– 7.14 Fuel consumption: 46.85 lb/mi (13.2 kg/km) operating for maximum range Thrust/weight: 0.373 Maximum nose tip temperature: 260 °F (127 °C) Runway requirement (with maximum load): 3,600 m (11,800 ft)
  • Published: 16.05.2016 16:53 on the channel Milan Jankovi

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