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| GENERAL CARACTERISTICS | ||
| Wing span | 6,63 m | |
| Wing area | 5.20 m² | |
| Aspect ratio | 8,45 | |
| Cabin Width | 1,12 | |
| Fuel capacity standard | 80 l | |
| Extended range fuel tanks | 2 x 50 l | |
| Empty weight (Basic version) | 220 kg | |
| Equipped empty weight | 260 kg | |
| Max. Takeoff weight | 490 kg | |
| Wing loading | 86 kg/m² | |
| ENGINE OPTIONS | ||
| Propeller | Two, or three blades fix pitch or constant speed |
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| Rotax 912 Engine | 80 hp | |
| Rotax 912S Engine | 100 hp | |
| Rotax 914 turbo charged Engine | 100 hp | |
| Jabiru 2200 Engine (still in development) |
80 hp | |
| V Speed | ||
| VSO (stall speed landing configuration) | 87 km/h | |
| Va (Maneuvering speed) | 225 km/h | |
| Vne ( Never exceeding speed) | 320 km/h | |
| Design maneuvering speed | 355 km/h | |
| Vno (Normal Operation Speed) | 260 km/h | |
| G loading | +4 /-2 g | |
| Vfe (Flaps extended speed) | 170 km/h | |
| PERFORMANCES | ||
| ENGINE | R 912 | R 912S |
| Power plant hp | 80 | 100 |
| Cruising 75%, FL 0 (km/h) | 272 | 295 |
| Cruising 75%, FL 80 (km/h) | 292 | 318 |
| Fuel consumption 75% (liters/h) | 17.1 | 21.3 |
| Range ,std Tanks 75% (km) | 1 366 | 1 194 |
| Cruising 65% FL110 (km/h) | 286 | 312 |
| Fuel consumption 65% (liters/h) | 14.8 | 18.5 |
| Range ,std Tanks 65% (km) | 1 545 | 1 375 |
| Takeoff roll; CS. Prop (m) | 190 | 152 |
| Climb rate FL 0, CS. Prop (ft/min) | 1550 | 1750 |
| For further information please visit Dyn'Aéro | ||