03 Aug 2016 First shipment of Pipistrel Aircraft for the Indian Ministry of Defense successfully delivered Pipistrel, who was awarded the contract by Indian MoD to supply 194 aircraft to the Indian Air Force (IAF), Indian Navy (IN) and National Cadet Corps (NCC), delivered the first batch of their aircraft to India and kick-started the process of training Indian Engineers and Pilots. Read more...
19 Jul 2016 Enjoy AirVenture Oshkosh with the Pipistrel team! We are proud that this year, Pipistrel was able to get a better location for our booth: right at the main entrance to AirVenture, through the front gates and immediately on the right. See you there! Read more...
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Sinus UL Motorglider technical data


model SINUS 912
max power(with 2 carb.) 80 hp at 5800 rpm
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%
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
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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