Bartini Stal-7

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Stal-7
Role Transport
National origin USSR
Manufacturer ZOK NII GVF
Designer Roberto L. Bartini
First flight Spring 1937
Number built 1
Variants Yermolaev DB-240
Yermolayev Yer-2
Yermolayev Yer-4

The Stal-7 was a twin-engined transport aircraft designed and produced in the USSR from 1934.

Development[edit]

Aeroflot issued a requirement for two transport aircraft types. Bartini began design work in October 1934 on an aircraft to meet the larger 10/12 passenger specification. Initially Bartini intended the Stal-7 to use a steel tube truss airframe, with fabric covering, but problems with complexity and the flexibility of the truss structure led Bartini to re-design the aircraft with a light-alloy monocoque structure. The hydraulically retractable main undercarriage legs retracted rearwards into the engine nacelles, which were positioned at the junction of the inverted gull wings. The trailing edges had hydraulically operated flaps inbord and ailerons outboard. Both the wings and tail surfaces were sharply tapered and the inboard wing sections sloped sharply upwards to pass through the fuselage cabin.

Flight testing began in the Spring of 1937 piloted by N. P. Shebanov, revealing high efficiency in speed, range and load. The Stal-7 crashed on take-off during full load testing, prompting the arrest of Bartini who was sent to a gulag in Siberia.[citation needed]

Repair of the Stal-7 was carried out under Vladimir Yermolaev's direction in 1939 and the aircraft continued to demonstrate excellent cruise performance during a 5,068 kilometres (3,149 mi), MoscowSverdlovskSevastopol – Moscow, non-stop flight averaging 405 kilometres per hour (252 mph).

The impressive performance of the Stal-7 prompted the appointment of Yermolaev as the head of OKB-240, to develop the Stal-7 into an effective long-range bomber, resulting in the DB-240 (Dal'niy Bombardirovschik – long-range bomber), Yer-2 and Yer-4 aircraft.


Specifications (Stal-7)[edit]

Data from Encyclopedia of Russian Aircraft 1875–1995 [1]

General characteristics

  • Crew: 2
  • Capacity: 10/12
  • Length: 16 m (52 ft 6 in)
  • Wingspan: 23 m (75 ft 5½ in)
  • Wing area: 72 m2 (775 ft2)
  • Empty weight: 4,800 kg (10,580 lb)
  • Gross weight: 11,000 kg (24,250 lb)
  • Powerplant: 2 × M-103, 641.3 kW (860 hp) each

Performance

  • Maximum speed: 450 km/h (280 mph)
  • Cruising speed: 360/380 km/h (224/236 mph)
  • Range: 5,000 km (3,107 miles)
  • Service ceiling: 10,000 m (32,800 ft)

See also[edit]

Aircraft of comparable role, configuration and era
Related lists

References[edit]

  1. ^ Gunston 1995, p. 42.
  • Gunston, Bill. The Osprey Encyclopedia of Russian Aircraft 1875–1995. London, Osprey. 1995. ISBN 1-85532-405-9

External links[edit]