I-250 (MiG-13, N)
Fighter fitted out with combined powerplant

    Design all-metal. The sizes of an airplane small, wing area only 15,0 м², it of a thin section, with special aerodynamic layout.
    I-250 combined powerplant consisted of VK-107A engine rated at 1650 hp and VRDK booster developed in TSIAM under K.V.Kholshchevnikov.  Power produced by piston engine supplied propeller and VRDK compressor. During take-off and in flight with VRDK off, power was used mainly by propeller; VRDK compressor was rotating at the lowest gear ratio. In order to reduce take-off run and attain maximum speed, the second, highest gear ratio was selected and combustion chamber has been supplied by fuel. The combustion chamber - about family by injectors behind a cabin, output gas nozzle - with adjustable lateral doors. The common power of a piston engine and VDRK was 2800 h.p. at the altitude 7000 m at speed of 820 kms / ч. Three-blade AV-10P-60 propeller, 3.1 m in diameter, was used on the aircraft.
     Armament consisted of three B-20, 20 mm-cal. cannon (100 shells for each cannon). One cannon shot through a hollow gear shaft; two synchronous cannon were mounted at the fuselage sides.
    Unlike prototypes I-250, MiG-13's fuel reserve loaded to four wing tanks was increased by 190 kg. The range without actuation VDRK on speed of 600 kms /hч has increased up to 1818 km.

References and Credits:

• History and aircraft of Mikoyan design bureau / «Wings of Russia», 1999, CD-ROM /
• «History of designs of airplanes in USSR (1938-1950)» / V.B.Shavrov, 1988 /

Helped

• Andrei Chernoburov

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