| Type description |
ULF-2, single seat ultralight motor glider |
| Type responsibility |
Dieter Reich |
| Wing |
Cantilever wing, single built-up wooden spar,
plywood nose section, built-up wood ribs, fabric covered. Wing
section: WORTMANN FX 63-137,
18 % thick at root, 15 % thick at tip. Spoiler on upper wing
surface. |
| Fuselage |
Wood frame of multi-corner cross section;
oval plywood spine; covered with fabric |
| Tail |
Cantilever structure, fabric covered |
| Landing Gear |
Main gear: One piece GFC-spring; wheel brakes.
Tail gear: GFC-spring, wheel is pedal controlled |
| Propulsion |
24 kW, two Cylinder (horizontally opposed),
4-Stroke CITROËN-VISA car engine,
belt driven reduction gear, 2 to 3 blade propeller, 1.6 m diameter.
Aluminium fuel tank behind firewall, 33 litre capacity |
| Pilot Accommodation |
Single 33 deg. reclined GFC seat, open or closed
windshield, cockpit width: 54 cm (21,3 inch) |
| Rescue system |
Fuselage integrated, consisting of parachute,
electric ignition box, pull-out rocket |
| Instruments |
Air speed indicator, rate of climb indicator,
altimeter |
| Dimensions |
Wing span
Wing root chord length
Wing tip chord length
Wing aspect ratio
Overall length
Horiz. tail span
|
11 m
1.51 m
1.07 m
8.7
6.25 m
2.6 m
|
36.09 ft
4.95 ft
3.51 ft
20.51 ft
8.53 ft |
| Areas |
Wing
Vertical tail
Horizontal tail
|
13.9 m²
1.33 m²
2.02 m²
|
149.56 sq.ft
14.31 sq.ft
21.47 sq.ft |
| Masses |
Mass empty
(without rescue system)
Max. take-off mass
|
210 kg
323 kg
|
463 lbs
712 lbs |
Ultimate Structural
Load Factors
|
Positive
Negative
|
6 g
3 g
|
|
| Performance |
Max. speed (VNE) Cruising speed (VCR)
Economical cruising speed
Minimum speed
Minimum sink speed (power-off)
Maximum L/D
(power-off)
Take-off ground run distance
Maximum rate of climb
Fuel consumption at 100 km/h |
140 km/h
120 km/h
100 km/h
50 km/h
1.1 m/s
14
80 m
3.0 m/s
4.0 l/h
|
87 mph
75 mph
62 mph
31 mph
215 fpm
260 ft
600 fpm
1.06 U.S.gal |
| Noise |
ICAO Annex 16, Chapt. 10 |
55 dB(A) |
Technical
Data 
