Mikoyan-Gurevich MiG-13
| Mikoyan-Gurevich MiG-13 (N) | |
|---|---|
|
|
| Type: | Fighter plane |
| Design country: | |
| Manufacturer: |
OKB Mikoyan-Gurevich |
| First flight: |
March 3, 1945 |
| Commissioning: |
1945 |
| Production time: |
1945-1946 |
| Number of pieces: |
≈50 |
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The Mikoyan-Gurewitsch MiG-13 ( Russian Микоян-Гуревич МиГ-13 , also known as I-250 , Project N or MiG-7 ) was a Soviet fighter aircraft . It was designed by the Mikoyan-Gurevich design office and had a mixed drive consisting of a piston engine and a so-called Kholschevnikov accelerator .
development
In addition to the conventional piston engine, a Cholschtschewnikow accelerator developed at ZIAM served as an additional drive in the fuselage rear from 1943. In order to achieve a low air resistance, the wings were designed very thin. The MiG-13 was developed as a parallel development to the Suchoi Su-5 , which also had a mixed drive.
The first project studies began in the summer of 1944, the first prototype was piloted by A. P. Dejew and flew for the first time on March 3, 1945. A second was built, which had a slightly modified landing gear and tail unit.
It was decided to put the MiG-13 into series production instead of the Su-5, but only in small numbers, as the advantages of pure jet propulsion had been recognized. From 1945 to 1946 around 50 series machines were produced, which differed from the prototypes mainly in that the keel fin under the stern was omitted. Until 1950 they flew with the Soviet Navy as coast surveillance aircraft in the Baltic States and the North Sea .
The abbreviation MiG-13 was only used by official Soviet agencies from 1981; Before that, all series machines were designated as MiG-7, the prototypes as I-250 or N, where the N stands for Nowij (new).
technical description
The MiG-13 was an all-metal low-wing aircraft with an oval fuselage cross-section. The auxiliary engine is located in the stern and is supplied with air together with the piston engine via a common inlet in the nose cone. The trapezoidal wings have a slightly positive V-shape, the tail unit has a normal construction. The undercarriage is completely retractable, with the main wheels retracting inwards.
Technical specifications
| Parameter | Data |
|---|---|
| crew | 1 |
| length | 8.75 m |
| span | 11.05 m |
| height | 4.25 m |
| Wing area | 15.00 m² |
| Wing extension | 8.1 |
| Empty mass | 2950 kg |
| Takeoff mass | normal 3680 kg |
| Top speed | 600 km / h without WRDK 825 km / h at 7800 m altitude with WRDK |
| Rate of climb | 4.6 min at 5000 m altitude |
| Climb performance | 20 m / s |
| Service ceiling | 11,900 m |
| Range | 1818 km |
| Engines | a water-cooled V-engine Klimow WK-107A (1070 kW / 1455 PS) a air jet engine Cholschtschewnikow WRDK (993 kW / 1350 PS) total power of both drives (2063 kW / 2805 PS) |
| Armament | three, later four 20 mm MK G-20s, one in the propeller hub, the others in the wings |
See also
literature
- Rudolf Höfling: Typenkompass MiG. Aircraft since 1939 . Motorbuch, Stuttgart 2011, ISBN 978-3-613-03335-1 .
- Wilfried Bergholz: Russia's great aircraft manufacturer. Jakowlew, Mikojan / Gurewitsch, Suchoj. The complete type book . Aviatic, Oberhaching 2002, ISBN 3-925505-73-3 .
- Wilfried Copenhagen : Soviet fighters . Transpress, Berlin 1985, DNB 850798752 (VLN: 162-925 / 145/85).
