

| Engine | turbojet | |
| Statistical traction | N | 9-220 |
| Engine speed | rev/min | 32000-112000 |
| Fuel consumption | ml/min | 129-730 |
| Speed of exhaust gas at nozzle section | km/h | 1840 |
| Parachute rescue system (designed for emergency landing) | ||
| Max.(barometric) height for activation of the parachute system | m | 3500 |
| Vertical speed of UAV descent above sea level with the following characteristics х in МСА circumstances | m/s | not more than 5 |
| Maximum speed for activation of the parachute | m/s | 60 |
| Minimum speed for activation of the parachute | m/s | 15 |
| Minimum height of parachute activation above the landing field level | m | 100 |
| Barometric height of location of the area above sea level | m | up to 2000 |
| Key geometric characteristics | ||
| Length | mm | 2384 |
| Span of wings | mm | 2800 |
| Weight data | ||
| Takeoff mass | kg | 33 |
| Standard fuel margin | ml | 7200 |
| Basic flight characteristics | ||
| Range of horizontal flight speed | km/h | 100-330 |
| Maximum speed with extended landing gear | km/h | 290 |
| Cruise speed | km/h | 150 |
| Required traction at cruise speed | N | 60 |
| Takeoff speed | km/h | 90 |
| Landing speed at glide path with extended flaps | km/h | 115 |
| Vertical speed during landing | m/s | 5-6 |
| Contact velocity | km/h | 85 |
| Flight attitude range | m | 50-3000 |
| Practical flight length | km | 90 |
| Flight duration | minutes | 20 |
| Control | ||
| Flight control | Automatic/dual | |
| Communication range (within line of sight) | km | up to 64 |
| Control system | Autonomous navigation, automatic performance of the flight task | |
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