Putilov Stal-2

The Putilov Stal -2 (Russian Путилов Сталь -2, also: Steel -2) was a Soviet airliner for 5 passengers. Unlike other types was attempted in the Stal designs, to form the backbone of the machine made ​​of stainless steel instead of the then customary aluminum because aluminum in the 1920s was a scarce material in the nascent structure in the USSR.

Development

1929 was formed for this reason at the Scientific Institute of Civil Air Fleet ( GWF NII ) the Stal - development group with Putilov as chief designer. The development work on the Stal -2 began in 1930 and ended on 11 October 1931, the first flight of the prototype. The flight test was successful and in 1934 and 1935 left 111 series machines, the assembly halls. The application was carried out at the Aeroflot mainly on routes in Siberia and Central Asia, and later in the Second World War.

The stainless steel by using expected lower maintenance costs remained, since the welds and bolted joints also required a lot of maintenance. While it developed with the Stal - 3, a slightly larger successor, soon came but again to conventional building materials for the skeleton via. A building equipped with Frise ailerons pattern was built in only one copy, and received the name Stal - 2 bis.

Technical Description

The hull of the Stal - 2 consisted of welded steel tube with a rectangular cross section and received in the bow area a Sperrholzbeplankung, while the rest of the airframe and were covered with fabric. The mounted in high-wing design main wing had two main spars and was supported with two steel struts per side. The wing ribs were also made of steel. The normal tail was braced and made ​​of the same materials. The chassis consisted of two rigid main wheels and a tail skid and could optionally be equipped with floats or snow sled.

Specifications

  • Wingspan: 15.2 m
  • Length: 9.8 m
  • Height: 3.0 m
  • Wing area: 31.0 m²
  • Mass: 1150 kg
  • Take off weight: 1900 kg
  • Drive: an air-cooled 9-cylinder radial engine M-26 with 220 kW ( 300 hp) take-off power
  • Maximum speed: 210 km / h
  • Cruising speed: 170 km / h
  • Landing speed: 70 km / h
  • Rate of climb: 4.2 m / s
  • Ceiling: 5,150 m
  • Range: up to 750 km
  • Crew / passengers: 1/5
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