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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