Technical data
Type G-20
Function Trainer Aerobatic Trainer
Year 1935 1937
Crew 2
Engines 1*100hp M-11 1*150hp M-11E
Length 6.3m
Wingspan 9.7m
Wing area 13.2m2
Empty weight 607kg 620kg
Loaded weight 836kg 880kg
Wing Load (kg/m2) 66.4 66.6
Power load (kg/hp) 8.4 5.9
Speed at 0m 209km/h 235km/h
Landing Speed 66km/h 70km/h
Landing Roll 170m 17sec 190m 14sec
Takeoff Roll - 190m 14sec
Range 400km ?
Flight Endurance 2.5h ?
Climb
Rate at 0m 3.8m/sec -
1000m 4.6min -
2000m 11.1min -
3000m 22.2min -
Ceiling 3870m ?
Payload
Fuel+Oil 69kg 100kg in wing

G-20 by V.K.Gribovskij

41k b/w drawing from 'Krylia Rodiny' magazine, 1984 Vol.6

Trainer, two-seater with enclosed cockpit and low wing supported by V-struts. G-20 was ordered by Osoaviakhim for aerobatic training. Wing struts were attached to special pylon, integrated into the canopy and serving as a 'safety frame' in the case of noseover.

It passed State Acceptance Trials and participated in The First Large Circle flight of light aircraft. Engine power was insufficient for 'high aerobatics', and in 1937 G-20 was re-engined. In more powerful configuration it became very popular, and about 70 pilots were trained on single built G-20.

PredecessorsModifications
- -

ReferencesLinks
  • "Samoliot" magazine, 1935, Vol.9 pp9;
  • "Samoliot" magazine, 1937, Vol.7 pp25-29;
  • "Technica Vozdushnogo Flota" magazine, 1936, Vol.5 pp86-94;
  • "Technica Vozdushnogo Flota" magazine, 1937, Vol.4 pp892;
  • 'Krylia Rodiny' magazine, 1984 Vol.6
  • "History of aircraft construction in the USSR", Vol.1 p.535;
  • G-20

  • Created January 05, 1999 Back to
    Main Gate