| Aircraft Engine Manufacturer |
General Electric Company |
Rolls-Royce |
| Aircraft Engine Type |
Turbojet |
Turbofan |
| Dry Weight (kg) |
314.7931 |
446.7885 |
| Diameter (mm) |
619.76 |
822.96 |
| Length (mm) |
2781.3 |
1544.32 |
| Wikipedia Article (URL) |
en.wikipedia.org/wiki/General_Electric_J97 |
en.wikipedia.org/wiki/Rolls-Royce_RB401 |
| Fuel |
|
Hydromechanical with provision for electronic monitoring |
| Geared Fan |
No |
No |
| Combustion Chamber |
annular |
Annular |
| Afterburner |
Yes |
No |
| Streams |
1 |
2 |
| Bypass Ratio |
|
4.2 |
| Maximum Takeoff Thrust (kN) |
23.4 |
24.7 |
| Thrust To Weight |
11.5 |
5.6 |
| Afterburner Thrust (kN) |
35 |
|
| Compressor Description |
14-stage |
Fan:Single-stage axial, HP:8-stage axial, variable inlet guide vanes |
| Turbine Description |
two-stage |
Two-stage LP, single-stage HP with air-cooled blades |