| Virus SW |
SW 80 (472.5kg) | SW 100 (472.5kg) | SW 100 (600kg) |
| ENGINE ROTAX | ROTAX 912 UL | ROTAX 912 ULS | ROTAX 912 ULS |
| max power | 80 hp at 5800 RPM | 100 hp at 5800 RPM | 100 hp at 5800 RPM |
| PROPELLER | Pipistrel VARIO | Variable pitch | Variable pitch |
| SIZES | |||
| wing span | 10,71 m | 10,71 m | 10,71 m |
| length | 6,5 m | 6,5 m | 6,5 m |
| height | 1,85 | 1,85 | 1,85 |
| wing area | 9,51 m2 | 9,51 m2 | 9,51 m2 |
| rudder area | 1,1 m2 | 1,1 m2 | 1,1 m2 |
| tail area | 1,08 m2 | 1,08 m2 | 1,08 m2 |
| aspect ratio | 11,3 | 11,3 | 11,3 |
| positive flaps | 9 deg, 19 deg | 9 deg, 19 deg | 9 deg, 19 deg |
| negative flaps | 5 deg | 5 deg | 5 deg |
| center of gravity | 25% – 37% | 25% – 37% | 25% – 37% |
| WEIGHTS | |||
| empty weigh | 287 kg | 289 kg | 289 kg |
| max take off weight (MTOW) | 472.5 kg | 472.5 kg | 600 kg |
| fuel tanks capacity | 2 x 50 l | 2 x 50 l | 2 x 50 l |
| useful fuel | 2 x 47 l | 2 x 47 l | 2 x 47 l |
| PERFORMANCES | DATA for TOM 472.5 kg | DATA for TOM 600 kg | |
| stall with flaps | 64 km/h | 64 km/h | 74 km/h |
| stall without flaps | 79 km/h | 79 km/h | 84 km/h |
| cruising speed (75% power) | 246 km/h | 273 km/h | 264 km/h |
| max. horizontal speed | 264 km/h | 283 km/h | 275 km/h |
| VNE | 302 km/h | 302 km/h | 302 km/h |
| max speed with airbrakes | 205 km/h | 205 km/h | 205 km/h |
| max speed with flaps | 130 km/h | 130 km/h | 130 km/h |
| turbulence penetration speed Vb | 250 km/h | 250 km/h | 250 km/h |
| best climb speed | 140 km/h | 140 km/h | 148 km/h |
| max climb rate | 6.1 m/sec | 8.4 m/sec | 6.6 m/sec |
| best glide ratio speed | 118 km/h | 118 km/h | 123 km/h |
| best glide | 1:17 | 1:15 | 1:15 |
| take off run | 140 m | 95 m | 140 m |
| take off over 15 m obstacle | 225 m | 175 m | 230 m |
| service ceiling | 6200 m | 6800 m | 5800 m |
| 45° – 45° roll time | 1,6 sec | 1,6 sec | 1.6 s |
| fuel consum. at cruis. speed | 13.6 l/hour | 17.8 l/hour | 18.0 l/hour |
| endurance | 6,9 hours | 5,3 hours | 5.3 h |
| range distance | 1650 km | 1450 km | 1415 km |
| max load factor permitted ( x 1,8) | +4g -2g | +4g -2g | +4g -2g |
| design safety factors & tested | minumum 1.875 | minumum 1.875 | minumum 1.875 |
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.
