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Mikoyan-Gurevich SN

mig-sn


Despite termination of trials in 1951 with the SU derivative of the MiG-15 featuring paired 23mm cannon on articulated mountings, the basic concept of gun armament capable of elevation and depression for air-air use was persisted with by the MiG OKB. In 1953, flight testing of a more sophisticated development of the concept began as Izdeliye SN. A variation of the MiG-17, the SN featured lateral air intakes, the 2900kg VK-1A turbojet being fed by circular orifices against concave fuselage sides forward of the wing roots. This arrangement permitted installation of the SV-25 armament system of three 23mm TKB-495 cannon mounted asymmetrically (one to port and two to starboard) on an articulated mounting in the nose section. Operated electrically, the cannon could be elevated to 27° 26' and depressed to 9° 48', the complete SV-25 system weighing 469kg. Trials with the SN were discontinued owing to aiming complexities combined with advances in air-to-air missiles.

Engine: 1 x 2900kg VK-1A turbojet
Take-off weight: 5620 kg / 12390 lb
Empty weight: 4152 kg / 9154 lb
Wingspan: 9.63 m / 31 ft 7 in
Length: 12.33 m / 40 ft 5 in
Height: 3.80 m / 12 ft 6 in
Wing area: 22.60 sq.m / 243.26 sq ft
Max. speed: 1058 km/h / 657 mph
Ceiling: 14500 m / 47550 ft

mig-sn-ld

Mikoyan/Gurevich SN

 

 


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