| Specifications
|
|---|
| Maximum takeoff weight |
36500 kg |
| Maximum payload |
10000 kg |
| Maximum speed |
700 km/h |
| Operating ceiling |
10100 m |
| Crew |
2 pilots |
|
| Wingspan |
31.890 ì |
| Length |
28.068 m |
| Height |
8.650 m |
| Wing area |
98.620 êâ. m |
| Fuselage diameter |
3.100 m |
| Wheel track |
4.094 m |
| Wheel base |
8.670 m |
| Takeoff power (H=0, M=0): |
| - Thrust, kgf (kN) | 6,500 (63,7) |
| - Specific fuel consumption, kg/kgf*h |
0,358 |
| - Maximum continuous power (H=0, M=0): |
| - Thrust, kgf (kN) | 5,000 (49) |
| - Maximum cruising power (H=8,000 m, M=0.75): |
| - Thrust, kgf (kN) |
1,600 (16,0) |
| - Specific fuel consumption, kg/kgf*h | 0,602 |
| Critical altitude |
11,000 m |
| Engine starting critical altitude:: |
| on the ground |
up to 3,600 m |
| in the flight |
up to 8,000 m |
| An-74TK-100 is equipped with two turbojet bypass engines D-36 of 3A series produced by Motor Sich (Zaporozhye), which correspond to ICAO requirements to low noise and emission. D-36 engines and their modifications are highly reliable and economic. Among their main advantages are low specific fuel consumption, ability to take off in the extreme weather conditions, "hot and high" characteristics. These engines are simple to service and repair because of their modular construction. |
| The exhaust section of the bypass duct is arranged to make it possible to equip the engine with a thrust reverser. |
