Kalinin K-2
| Kalinin K-2 | |
|---|---|
| Type: | Airliner |
| Design country: | |
| Manufacturer: |
Kharkov aircraft plant |
| First flight: |
1926 |
| Number of pieces: |
4th |
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The Kalinin K-2 ( Russian Калинин К-2 ) was a Soviet airliner that was designed and built by the designer Konstantin Kalinin . The aircraft was a variant of its predecessor K-1 with a more powerful engine and an all-metal construction. The total weight of the construction significantly exceeded that of the planning. The first flight took place in 1926. The assembly was more complex than with the K-1, nevertheless four copies were built and used for the transport of passengers.
history
After the approval of the K-1 model, Kalinin was assigned the shipyard of the airline “Ukrwosduchputj” in Kharkov as a construction site. The shipyard was then renamed GROS (Graschdanskoje Opytnoje Samoljostrojenie, experimental aircraft construction for civil aviation). Shortly thereafter, it was only referred to as a "serial work". Here, Kalinin gathered his best employees and planned the further development of the aircraft type. The planning group included I. G. Neman , S. I. Iskowitsch , A. J. Shcherbakow and W. J. Krilow. After the K-1 model was put into operation, the designers very quickly came to the decision to replace the 170 hp Salmson RB-9 engine with a more powerful and modern engine, as was also done with the K-1. Several engines were considered. But Kalinin and his group ultimately decided on a BMW IV engine with 240 hp.
construction
The fuselage consisted of a welded tubular steel frame and was clad with light metal sheets made of Kolchug aluminum . The construction was designed as a shoulder- wing aircraft, the wings of which were braced to the lower part of the fuselage. The wings had an elliptical shape and, like the tail unit, were made of tubular steel and also clad with light metal sheets. The tail unit had a normal shape (tail fins aimed at the fuselage). All control surfaces were covered with fabric. The chassis was solid and provided with a continuous axle. At the stern of the fuselage was a spring-loaded tail spur. The pilot sat in a closed cabin.
Technical specifications
| Parameter | Data |
|---|---|
| crew | 1 |
| Passengers | 4th |
| length | 11.17 m |
| span | 16.76 m |
| Wing area | 40.00 m² |
| Wing extension | 7th |
| Wing loading | 55.8 kg / m² |
| Power load | 9.3 kg / hp |
| Preparation mass | 1600 kg |
| Payload | 636 kg |
| Takeoff mass | 2236 kg |
| Engine | a liquid-cooled six - cylinder in - line BMW IV engine with a rigid two-bladed wooden propeller |
| power | 176 kW (approx. 240 PS) |
| Fuel volume | 200 kg |
| Top speed | 170 km / h |
| Cruising speed | 140 km / h (economical) |
| Landing speed | 75 km / h |
| Rate of climb | 1.4 m / s |
| Service ceiling | 3500 m |
| Max. Range | 650 km |
| Take-off run | 220 m |
| Landing runway | 200 m |
literature
- Heinz A. F. Schmidt: Historical Airplanes Part II . Motor book, Stuttgart 1970.
- Heinz A. F. Schmidt: Soviet planes . Transpress , Berlin, p. 35 .
- В. Б. Шавров: История конструкций самолетов в СССР до 1938 . S. 416 .
- Bill Gunston: The Osprey Encyclopedia of Russian Aircraft . Osprey, 2000, pp. 132 f .