Taurus Electro is made in highest technology composites (epoxy resin, glass fibre, carbon fibre, kevlar fibre and honeycomb structures). The airfoil used on wings is ORL 170, (F. Orlando).
| model TAURUS ELECTRO G2 | |
| Motor | High performance synchronus 3-phase electric outrunner with permanent magnets |
| power | 40 kW for takeoff, 30 kW contionus |
| PROPELLER | 2 blade Pipistrel 1650 mm diam special for Taurus Electro G2 |
| PROPORTIONS | |
| wing span | 14.97 m |
| length | 7.27 m |
| height | 1.41 m |
| wing area | 12.33 m2 |
| rudder area | 0.9 m2 |
| horizontal tail area | 1.36 m2 |
| aspect ratio | 18.6 |
| positive flaps | 5 deg, 9 deg, 18 deg |
| negative flaps | -5 deg |
| center of gravity | 23% – 41% |
| WEIGHTS | |
| empty weight (includes standard battery!) | 306 kg |
| minimum pilot weight | 60 kg |
| maximum total pilots weight | 220 kg |
| max take off weight (MTOW) | 450 kg / 472.5 kg / 550 kg |
| weight of std battery system | 42 kg |
| weight of optional battery system | 59 kg |
| PERFORMANCES | |
| stall with flaps | 63 km/h |
| stall without flaps | 71 km/h |
| manoeuvring speed | 163 km/h |
| max. speed with flaps extended | 130 km/h |
| max. speed with airbrakes extended | 225 km/h (extend at or below 160 km/h) |
| max. speed with powerplant extended | 160 km/h |
| VNE | 225 km/h |
| min.sink | 0.70 m/sec |
| min.sink speed | 94 km/h |
| max. sink with airbrakes | 6.0 m/sec @ 100 km/h |
| best glide | 1: 41 |
| best glide ratio speed | 107 km/h |
| best glide at 150 km/h | 1: 33 |
| best glide at 180 km/h | 1: 23 |
| max towing speed | 150 km/h |
| 45°-45° roll time | 3.9 sec |
| take off run MTOW | 160 m |
| take off over 15 m MTOW | 245 m |
| best climb speed | 100 km/h |
| max climb rate (MTOW) | 3.1 m/sec |
| relative climb (elevation independent!) | 1100 m (4000 ft) / 2000 m (6000 ft) |
| max load factor permitted (x1,8) | +5.3g -2.65g |
| max load factor tested | + 7.2g – 7.2g |
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.
