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Societe Nationale de Constructions Aeronautiques Du Sud Est SE 212 Durandal

sud-est212


From the end of 1951, the bureau d'etudes headed by Pierre Satre at the SNCA du Sud-Est undertook a series of studies of potential lightweight mixed-power interceptor fighters under what was effectively the generic designation SE 212. These studies crystallized in the shape of a small, 60-degree delta powered by a SNECMA Atar 101F with an afterburning thrust of 3800kg and a 750kg SEPR 75 rocket motor. The primary armament was intended to consist of a single AA 20 or R 052 missile carried externally on the fuselage centreline, alternative armament being two 30mm DEFA cannon or 24 SNEB rockets of 68mm calibre. An official contract was placed for two prototypes, the first of which was flown on 20 April 1956 without the rocket motor fitted. The Atar 101F turbojet was subsequently replaced by an Atar 101G with an afterburning thrust of 4400kg, and the first flight during which the rocket motor was lit took place on 19 December 1956. The second prototype SE 212 was flown on 30 March 1957. During flight testing a speed of 1444km/h, or Mach=1.36, was attained at 12,300m without the rocket motor and 1667km/h, or Mach=1.57, was reached at 11,800m with the rocket motor lit. These speeds were achieved without armament fitted, and the test programme terminated in 1958.

Loaded weight: 6700 kg / 14771 lb
Empty weight: 4575 kg / 10086 lb
Wingspan: 7.44 m / 24 ft 5 in
Length: 12.07 m / 40 ft 7 in
Wing area: 29.60 sq.m / 318.61 sq ft
Max. speed: 1667 km/h / 1036 mph

sud-est212-ld
Sud-Est SE 212 Durandal


 

 


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