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The Mirage 4000 was noticeably larger and heavier than the single-engined Mirage 2000, the 4000 having two SNECMA M53-2 turbofans. [1] It also featured small canards above the engine air intakes and a true bubble canopy, compared to the Mirage 2000 and previous Mirages.
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 ]
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Mirage F2: Strike fighter, a larger and more powerful version of the conventionally tailed F1. [4] Mirage G, G4 and G8: Variable-geometry (swing-wing) fighters. The G was effectively a swing-wing F2, while the G4 and G8 were twin-engined developments. [4] Mirage 4000 or Super Mirage 4000: Prototype larger version of the Mirage 2000 design.
The Dassault Mirage IIIV, also spelled Mirage III V, was a French vertical take-off and landing prototype fighter aircraft of the mid-1960s developed and produced by Dassault Aviation. The Mirage IIIV was a VTOL derivative of an existing conventional fighter, the Dassault Mirage III ; the principal difference between the two types was the ...
Distributed propulsion on an aircraft is typically characterised not only by the distributed nature of the propulsive thrust but also by utilisation of the effect this has on the aircraft aerodynamics. [2] The propulsive air flows are distributed over the aerodynamic surfaces of the craft, typically spanwise over a fixed wing.
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 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]