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Partial reheat providing a 20% thrust increase [3] was installed to give the take-off thrust required for Concorde to operate from existing runways, and for transonic acceleration from Mach 0.95 up to Mach 1.7; the aircraft flew supersonically without reheat above that speed. At cruise the engine's direct contribution (transferred by its mounts ...
Ultra Electronics also developed Concorde's thrust-by-wire engine control system. [101] Engine failure causes problems on conventional subsonic aircraft; not only does the aircraft lose thrust on that side but the engine creates drag, causing the aircraft to yaw and bank in the direction of the failed engine. If this had happened to Concorde at ...
For example, Concorde cruised at 1354 mph, or 7.15 million feet per hour, with its engines giving an SFC of 1.195 lb/(lbf·h) (see below); this means the engines transferred 5.98 million foot pounds per pound of fuel (17.9 MJ/kg), equivalent to an SFC of 0.50 lb/(lbf·h) for a subsonic aircraft flying at 570 mph, which would be better than even ...
The BOl.1 first ran on 16 May 1950 and was designed to produce 9,140 lbf (40.7 kN) thrust and to be free from destructive rotating stall on start up to idle speed and to be free from surging on fast accelerations to maximum thrust. The engine started without a problem and Hooker, supervising the first test run and displaying the confidence he ...
Jet-engine thrust is an application of Newton's reaction principle, in which the engine generates thrust because it increases the momentum of the air passing through it. [5] Thrust depends on two things: the velocity of the exhaust gas and the mass of the gas exiting the nozzle.
It’s now almost 55 years since the 002 prototype for Concorde first flew at Mach 1 on March 25, 1970, and more than 21 years since commercial supersonic travel ended with the Anglo-French ...
The supersonic aircraft suffered a catastrophic crash in Paris on 25 July 2000
The thrust-to-weight ratio is usually calculated from initial gross weight at sea level on earth [6] and is sometimes called thrust-to-Earth-weight ratio. [7] The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5]