M-20
Single Seater, Enclosed
|
|
Prototypes
flying. Future production
is not planned.
|
TECHNICAL SPECIFICATIONS
| WEIGHT |
|
| Empty weight |
205 Kg (452
lb.) |
| Maximum take-off
gross weight |
350 Kg (771
lb.) |
| Useful Load |
145 Kg (319
lb.) |
| |
|
| PERFORMANCE |
|
| Maximum speed |
110 mph |
| Cruising speed |
90 mph |
| Absolute ceiling |
4000 m (13,000
ft) |
| Service ceiling |
3500 m (11,400
ft) |
| Take-off roll |
45 m (150 ft) |
| Landing roll |
from 0 to 30
m (0 to 100 ft) |
| Rate of climb |
5m/s (950) |
| Fuel tank capacity |
45 lt (11.8
gal) |
| Endurance |
2 h |
| Range (no reserve) |
180 miles |
| |
|
| DIMENSIONS |
|
| Rotor diameter |
7062 mm (23
ft) |
| Propeller diameter |
1620 mm (64
inch) |
| Overall width |
1730 mm (69
inch) |
| Overall length |
3920 mm (155
inch) |
| Overall height |
2370 mm (94
inch) |
| |
|
| DESCRIPTION |
|
| |
|
| AIRFRAME: |
Chrome-alloy
aeronautical 4130 steel, tig welded. |
| SEAT: |
With integral
fuel-tank manufactured from epoxy resin reinforced with fiberglass. |
| ENGINE: |
Rotax 912,
with mechanical prerotator. |
| PROPELLER: |
Three-blade,
made from carbon fiber with ground adjustable pitch. |
| ROTOR: |
Two-blade,
in composite materials. |
| CONTROLS: |
Single |
|
