| 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 |
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.
| Predecessors | Modifications |
|---|
|
-
|
-
|
| References | Links |
|---|
|
"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
|
