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Dassault Mirage F2 & G

The Dassault Mirage F2 was a French prototype two-seat ground attack / fighter aircraft, which was designed to serve as a test bed for the SNECMA TF306 turbofan engine.

The F2 also influenced the subsequent Dassault Mirage G, a variable geometry design.

The Dassault Mirage G was a French two-seat twinjet variable-geometry prototype fighter, built in the late 1960s.

The type was further developed into the twin-engine Mirage G4 and G8 variants as a multi-role jet fighter capable of both interception and nuclear strike missions.

Although Dassault built and flew prototypes, the entire program was terminated in the 1970s without the aircraft entering production.


Mirage F2

The Mirage F2 is preserved at the DGA Techniques Aeronautiques in Toulouse Balma, France.

Mirage G

Single engined initial version, first flight 18 November 1967.

Crashed 13 January 1971.

Mirage G4

G8-01 is on public display at the Musée de l’Air et de l’Espace

The basic Mirage G was developed into a twin-engine, two-seat nuclear strike fighter, the Mirage G4 after a separate contract was issued in 1968 for two aircraft to be built.

These aircraft were intended to be powered by Snecma M53 turbofans in production.

While the aircraft were under construction the requirements changed and the French military requested that the design be converted into a dedicated interceptor, the Mirage G8.

Mirage G8

Mirage G4-01 was redesignated G8-01 and remained a two-seat aircraft with the second aircraft, G4-02 becoming a single-seat version, G8-02.

The G8 variants were equipped with Thomson-CSF radar and a low-altitude navigational-attack system based on that used in the SEPECAT Jaguar and Dassault Milan.

As no funding was included for the Mirage G8 in the 1971-1976 French defence budget the aircraft did not enter production.





18.8 m (61 ft 8 in)


15.4 m (50 ft 6 in)

Swept wingspan

8.7 m (28 ft 7 in) swept


5.35 m (17 ft 7 in)

Empty weight

14,740 kg (32,496 lb)

Max take-off weight

23,800 kg (52,470 lb)


2 × SNECMA Atar 9K50 afterburning turbojet engines,

49.03 kN (11,020 lbf) thrust each dry, 70.1 kN (15,800 lbf) with afterburner


Maximum speed

Mach 2.2


3,850 km (2,390 mi, 2,080 nmi)

Service ceiling

18,500 m (60,700 ft).

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