Putilov Stal-2
| Putilov Stal-2 | |
|---|---|
|
|
| Type: | Airliner |
| Design country: | |
| Manufacturer: |
Plant (GAS) 81 |
| First flight: |
October 11, 1931 |
| Commissioning: |
1934 |
| Production time: |
1934-1935 |
| Number of pieces: |
111 |
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The Putilow Stal-2 ( Russian Путилов Сталь-2 , also: Stahl-2) was a Soviet airliner for up to five passengers. In contrast to other types, in the case of the Stal constructions, an attempt was made to form the basic structure of the machine from stainless steel instead of the aluminum common at the time, since aluminum was a scarce material in the emerging USSR in the 1920s.
development
For this reason, the Stal Development Group was formed at the Scientific Institute of the Civil Air Fleet ( NII GWF ) in 1929 with Putilov as chief designer. Development work on the Stal-2 began in 1930 and ended on October 11, 1931 with the first flight of the prototype. The flight tests were successful and 111 series machines left the assembly halls in 1934 and 1935. The Aeroflot was mainly used on routes in Siberia and Central Asia, later also during World War II .
The lower maintenance that was hoped for through the use of stainless steel was not achieved, as the weld points and screw connections also required a lot of care. With the Stal-3, a slightly larger successor model was developed, but soon afterwards they switched back to conventional building materials for the basic structure.
A model equipped with Frize ailerons was built in just one copy and was given the designation Stal-2bis .
technical description
The fuselage of the Stal-2 consisted of welded steel tube with a rectangular cross-section and was given plywood planking in the bow area, while the rest of the part and the airframe were covered with fabric. The main wing, mounted in the shoulder -wing construction method, had two main spars and was supported with two steel struts on each side. The wing ribs were also made of steel. The normal tail was braced and made of the same materials. The undercarriage consisted of two rigid main wheels and a tail spur and could optionally be equipped with floats or snow runners.
Technical specifications
| Parameter | Data |
|---|---|
| Crew / passengers | 1/5 (2/4) |
| length | 9.75 m |
| span | 15.20 m |
| height | 2.97 m |
| Wing area | 31.00 m² |
| Empty mass | 1150 kg |
| Payload | 750 kg |
| Takeoff mass | 1900 kg |
| Wing loading | 61.3 kg / m² |
| Power load | 6.3 kg / hp |
| drive | an air-cooled 9-cylinder radial engine M-26 |
| Starting power | 220 kW (299 hp) |
| Top speed | 210 km / h |
| Cruising speed | 170 km / h |
| Landing speed | 70 km / h |
| Climb performance | 4.2 m / s |
| Service ceiling | 5150 m |
| Range | Max. 750 km |
| Take-off / landing runway | 130 m / 140 m |
See also
literature
- Heinz AF Schmidt: Soviet planes . Transpress , Berlin 1971, p. 63 .
Web links
- History and Photos (Russian)