Citat:
Ursprungligen postat av
Mrsharpangel
F110 väger ochså dubbelt så mycket
Från
Wiki
Data from GE Aviation
F110-GE-129/F110-GE-132
General characteristics
Type: Afterburning turbofan
Length: 182.3–232.3 in (463–590 cm)
Diameter: 46.5 in (118 cm)
Dry weight: 3,920–4,400 lb (1,780–2,000 kg)
Components
Compressor: 2 spool, 3 fan and 9 HP
compressor stages
Combustors: Annular
Turbine: 2 LP and 1 HP stages
Performance
Maximum thrust:
Dry thrust: 16,610 lbf (73.9 kN)
F110-GE-129: 29,500 lbf (131 kN)
F110-GE-132: 32,000 lbf (140 kN)
Overall pressure ratio: 29.9:1 - 30.4:1
Turbine inlet temperature: 2,750 °F (1,510 °C)[7]
Thrust-to-weight ratio:
F110-GE-129: 7.29
F110-GE-132: 7.90
enl
F414
Data from
GE Aviation,[27] Deagal.com,[28] and
MTU Aero Engines[29]
General characteristics
Type: Afterburning turbofan
Length: 154 in (391 cm)
Diameter: 35 in (89 cm)
Dry weight: 2,445 lb (1,110 kg) max weight
Components
Compressor: axial compressor with 3 fan and 7 compressor stages
Combustors: annular
Turbine: 1 low-pressure and 1 high-pressure stage
Performance
Maximum thrust:
13,000 lbf (57.8 kN) military thrust
22,000 lbf (97.9 kN) with afterburner
Overall pressure ratio: 30:1
Bypass ratio: 0.25:1
Air mass flow: 170 lb/s (77.1 kg/s)
Thrust-to-weight ratio: 9
Dvs det är bättre kraft/vikt-förhållande med F414-serien. Inte riktigt dubbel vikt.
https://en.wikipedia.org/wiki/Pratt_%26_Whitney_F135 säger
Dry weight: 3,750 lb (1,701 kg) och
28,000 lbf (128 kN) military thrust,
43,000 lbf (191 kN) with afterburner
vilket ger Thrust-to-weight ratio: 7.47:1 military thrust, 11.47:1 augmented
som jmf med den motor flyget i ämnet har och behöver pga sämre aerodynamik.