Dassault Mirage F2


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Dassault Mirage F2

Early in 1964, Dassault was awarded a contract to develop a successor to the Mirage III with emphasis on the low-altitude penetration role, and an order followed for a single prototype of a tandem two-seat aircraft which it was intended to power with the SNECMA (Pratt & Whitney) TF-306 turbofan. Despite minimal resemblance and relationship to the delta-winged series of aircraft, the new fighter, which featured a high-mounted swept wing with horizontal tail surfaces, was assigned the designation Mirage F2 and was flown on 12 June 1966. Initial flight trials were conducted with a Pratt & Whitney TF30 turbofan rated at 8400kg with afterburning. After being re-engined with a TF-306 of 9000kg, it attained M=2.0 on its second flight, on 29 December 1966. Work had begun on a single-seat version, the Mirage F3 with a 10350kg TF-306E engine, but changes in Armee de l'Air requirements saw interest transferred to a scaled-down and simpler version of the basic design, the Mirage F1, development of which had been pursued in parallel by Dassault, and further development of the Mirage F2 was discontinued.

Dassault Mirage F2

 ENGINE1 x Pratt & Whitney TF30 turbofan, 9000kg
  Take-off weight18000 kg39683 lb
  Empty weight9500 kg20944 lb
  Wingspan10.5 m34 ft 5 in
  Length17.6 m58 ft 9 in
  Height5.8 m19 ft 0 in
  Max. speed2333 km/h1450 mph
  Ceiling20000 m65600 ft

Dassault Mirage F2A three-view drawing (1663 x 1223)

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