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Mikoyan-Gurevich I-270(ZH)

mig-i-270


Created to meet a 1945 requirement for a rocket-propelled target defence fighter, the I-270(Zh) was based broadly on the Junkers Ju 248, but was of more conventional configuration. The I-270 featured a straight, near-laminar flow wing, a conventional horizontal tail, and an ejection seat (the first in a Soviet fighter).

The first of two prototypes was initially flown in December 1946 without the rocket motor installed, being towed into the air by a Tu-2.

Only the second prototype was to be fitted with the rocket motor. This, the RD-2M-3V developed by L Dushkin and V Glushko, was a bi-propellant dual-chamber unit with a total thrust of 3,196 lb / 1450kg of which the cruise chamber contributed 400kg. The cabin was pressurised and proposed armament comprised two 23mm cannon and eight RS-82 rockets. Calculated endurance was 4 min at maximum thrust and 85 min on the power of the cruise chamber alone.

The first powered flight was carried out with the second prototype early in 1947, and speeds of the order of 620 mph (1000 km/h) were allegedly attained in level flight. The second prototype was written off as a result of a landing crash while being flown by an NII VVS pilot.

Shortly afterwards, the first prototype was damaged in a belly landing and was not repaired, further development was discontinued.

Max take-off weight: 4120 kg / 9083 lb
Empty weight: 1546 kg / 3408 lb
Wingspan: 7.75 m / 25 ft 5 in
Length: 8.91 m / 29 ft 3 in
Height: 3.08 m / 10 ft 1 in
Wing area: 12.00 sq.m / 129.17 sq ft
Max. speed: 1000 km/h / 621 mph
Time to 32,810 ft (10 000 m): 2.37 min
Time to to 49,210 ft (15 000 m): 3.03 min

mig-i-270ld

Mikoyan/Gurevich I-270

 

 

 


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