|
Categories of the aircraft
|
ultralight
|
|
Type of the construction
|
all-metal
|
|
Type of the engine
|
ROTAX 912 UL
|
|
Configuration of the wing
and the fuselage
|
low-wing self-supporting
|
|
Max. take off weight
|
450 kg
|
|
Basic empty weight
|
285 kg
|
|
Max. fuel weight
|
max. 46
kg
|
|
Wing area
|
11,85 m2
|
|
Wing span
|
9,90 m
|
|
Wing slimness
|
7,78
|
|
Area
|
2,29 m2
|
|
Span
|
2,95 m
|
|
Area
|
1,18 m2
|
|
Height
|
1,35 m
|
|
Percentage depth aileron
|
0,30
|
|
Span
|
1,80 m
|
|
Area
|
0,60 m2
|
|
Deflection (Up) (Down)
|
(28_) (14_)
|
|
Percentage depth lift flap
|
0,29
|
|
Span
|
1,80 m
|
|
Area
|
0,70 m2
|
|
Take off deflection, Landing
deflection
|
(10_) (35_)
|
The Performance Data
|
Speed
|
CAS
|
(km/h)
|
|
Dive flight
|
VD
|
265
|
|
Max. level speed
|
VNE
|
240
|
|
Max. cruise speed
|
VC
|
200
|
|
Designed manoeuvring
velocity
|
VA
|
142
|
|
Max. velocity with flaps
fully extruded
|
VFE
|
100
|
|
Min. speed with lift flaps
|
VSO
|
48
|
|
Min. speed without lift
flaps
|
VS1
|
71
|
|
|
