It's hard to say because the data on the
Eurojet (not RR) EJ230 is very limited. It was offered to the Indians for a development of the HAL Tejas but not taken up. The public data I have seen is that it is basically an uprated EJ200 with thrust vectoring ability. I have seen it mentioned to have maximum wet thrust of approximately 102 kN and Dry thrust is around 72 kN. Comparing to the F414, we get 97.9 kN and 57.8 kN respectively. Thus on just thrust it is roughly comparable. To have a full comparison though, one needs to also know the dimensions, weight and SFC. Using that known for the EJ200 and F414 we get:
| EJ200 | F414 |
- Length: 398.78 cm (157.00 in)
- Diameter: 73.66 cm (29.00 in)
- Dry weight: 988.83 kg (2,180.0 lb)
- Air mass flow: 75–77 kg/s (165–170 lb/s)
- Specific fuel consumption: 21–23 g/(kN⋅s) (0.74–0.81 lb/(lbf⋅h)) and 47–49 g/(kN⋅s) (1.66–1.73 lb/(lbf⋅h)) (with reheat)
- Thrust-to-weight ratio: 6.11:1 and 9.17:1 (with reheat)
|
- Length: 154 in (391 cm)
- Diameter: 35 in (89 cm) overall, 31 in (79 cm) inlet
- Dry weight: 2,445 lb (1,110 kg) max weight
- Air mass flow: 170 lb/s (77.1 kg/s)
- Specific fuel consumption: 23.9 g/kN⋅s (0.840 lb/HR/lb) (w/o afterburner); 49.3 g/kN⋅s (1.850 lb/HR/lb) (with afterburner)
- Thrust-to-weight ratio: 5.3 and 9 (with reheat)
|
Now if the EJ230 has added thrust vectoring one might reasonably assume that that comes with some additional weight. Similarly, extra thrust usually comes with extra fuel burn. Thus overall, I would say the engines are roughly comparable. That said, it is all theoretical until someone actually does it...and pays for it.