Sinus

Sinus UL Motorglider technical data

 

model SINUS 912
ENGINE ROTAX ROTAX 912 UL2
max power(with 2 carb.) 80 hp at 5800 rpm
PROPELLER Pipistrel VARIO
SIZES  
wing span 14,97 m
length 6,6 m
height 1,70 m
wing area 12,26 m2
rudder area 1,1 m2
tail area 1,63 m2
aspect ratio 18,3
positive flaps 9 deg, 18 deg
negative flaps 5 deg
center of gravity 20% - 39%
WEIGHTS  
empty weight 285 kg
empty weight light version 275 kg
max take off weight (MTOW) 450 kg  / 472.5 kg / 544kg
fuel tanks capacity 2 x 30 l / 2 x 50 l
useful fuel 2 x 27 l / 2 x 45 l
PERFORMANCES DATA PUBLISHED FOR TOM of 472.5 kg
stall with flaps 63 km/h
stall without flaps 66 km/h
cruising speed (75% power) 200 km/h   
max. horizontal speed   220 km/h
VNE 225 km/h
max speed with airbrakes out 160 km/h
max speed with flaps down 130 km/h
manoeuvring speed 141 km/h
best climb speed 120 km/h
max climb rate ( 450 kg) 6,5 m/sec 
climb rate at 140 km/h 6,3 m/sec  
min.sink speed 90 km/h
min.sink (prop. 90 deg.) 1,03 m/sec
max. sink with airbrakes 5,5 m/sec
best glide ratio speed 95 km/h
best glide (prop. 90 deg.) 1:27
glide at 150 km/h (prop 90 deg) 1:18
take off run ( 450 kg) 88 m
take off over 15 m obstacle (450 kg) 148 m
service ceiling ( 450 kg) 8800 m
45° - 45° roll time 4,2 sec
fuel consum. at cruis. speed 9,2 l/hour
endurance (std tanks)
5,8 hours
range distance 1200 km
max load factor permitted ( x 1,8) +4 g  - 2 g
max load factor tested + 7,2 g - 7,2 g

Pipistrel reserves the right to revise the above data whenever occasioned by product improvement, government/authority regulations or other good cause.
The design basis follow the strictest EASA CS-22, CS-VLA and CS-23 (sections), as well as rules applicable to ultralight/microlight aircraft (LTF-UL 2003, etc.)
and ASTM-LSA standards.
Ultralight/Microlight certification basis varies from country to country, therefore the actual certificated data may be different from stated above. Please check the certifications link.


 

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