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Gross weight: 16,100 kg (35,494 lb) combat weight Fuel capacity: approx 11,000 L (2,900 US gal; 2,400 imp gal) internal fuel Powerplant: 2 × SNECMA M53 afterburning turbofan engines, 64.3 kN (14,500 lbf) thrust each dry, 95.1 kN (21,400 lbf) with afterburner
Flight testing started in July 1973 using a Caravelle flying test-bed and the engine first went supersonic in a Mirage F.1 test bed at the end of 1974. [ 3 ] The engine was designed to have better performance than the latest Atar engines but simpler and less costly than the SNECMA TF 306 turbofan. [ 1 ]
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]
The Mirage F1 emerged from a series of design studies performed by French aircraft manufacturer Dassault Aviation. [2] Having originally sought to develop a larger swept wing derivative of the Mirage III, which became the Mirage F2, to serve as a vertical take-off and landing propulsion testbed akin to the Dassault Mirage IIIV, however, it was soon recognized that the emerging design could ...
The Mirage III family has its origins within a series of studies conducted by the French Defence Ministry which had commenced in 1952. At the time, several nations had taken an interest in the prospects of a light fighter, which had been motivated by combat experiences acquired during the Korean War, specifically the Soviet-built Mikoyan-Gurevich MiG-15 jet-propelled fighter aircraft which had ...
The Dassault Mirage 2000 is a French multirole, single-engine, delta wing, fourth-generation jet fighter manufactured by Dassault Aviation.It was designed in the late 1970s as a lightweight fighter to replace the Mirage III for the French Air Force (Armée de l'air).
Dassault's resulting prototype, dubbed Mirage IV 01, looked a lot like the Mirage IIIA, even though it had double the wing surface, two engines instead of one, and twice the unladen weight. [3] The Mirage IV also carried three times more internal fuel than the Mirage III.
The Atar 101E added a "zeroth" compressor stage, raising the overall pressure ratio to 4.8:1 and the thrust to 36,300 N (8,200 lb f), surpassing the projected thrust of 34.3 kN (7,700 lbf) of the German BMW 018 turbojet still being developed in 1945. Various Atar 101 models were tested on a wide variety of aircraft.