| 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.
ENGINE | 1 x Pratt & Whitney TF30 turbofan, 9000kg |
WEIGHTS |
Take-off weight | 18000 kg | 39683 lb |
Empty weight | 9500 kg | 20944 lb |
DIMENSIONS |
Wingspan | 10.5 m | 34 ft 5 in |
Length | 17.6 m | 58 ft 9 in |
Height | 5.8 m | 19 ft 0 in |
PERFORMANCE |
Max. speed | 2333 km/h | 1450 mph |
Ceiling | 20000 m | 65600 ft |
![Dassault Mirage F2](../../pictures/france/m/dassault_mirage_f-2-m.gif) | A three-view drawing (1663 x 1223) |
grahamclayton, e-mail, 07.05.2023 06:18 What is the bulge at the base of the vertical stabilizer? reply |
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