Data for some military turbofan engines

Model no.	Thrust (lb)*	TSFC (lb/hr) /lbf	Airflow (lb/sec)	OPR	D (in)	L (in)	Weight (lb)	TIT (F)	FPR	BR	Remarks
Fl00-PW-229	29,000 17,800	2.05 0.74	248	23.0	47	191	3,036	2,700	3.8	0.4	F-15, F16
Fl01-GE-102	30,780 17,390	2.460 0.562	356	26.8	55.2	180.7	4,448	2,550	2.31	1.91	B-lB
F103-GE-101	51,711	0.399	1,476	30.2	86.4	173	8,768	2,490	—	4.31	KC-10A
F107-WR-10l	635	0.685	13.6	13.8	12	48.5	141	—	2.1	1.0	Air Launch Cruise Missile
F108-CF-100	21,634	0.363	785	23.7	72	115.4	4,610	2,228	1.5	6.0	KC-135R
Fl I 0-GE-l00	28,620 18,330	2.08 1.47	254	30.4	46.5	182	3,895	—	2.98	0.80	F-16
F117-PW-100	41,700	0.33	—	31.8	84.5	146.8	7,100	—	—	5.8	(PW2040) C-17A
F118-GE-100	19,000	0.67	—	35.1	46.5	100.5	3,200	—	—	—	B-2
F119-PW-100	35,000	—	—	—	—	—	—	—	—	—	F-22 Raptor
F135-PW-400	40,000	—	—	—	—	—	—	—	—	—	F-35 JSF
F404-GE-F1D2	10,540	0.79	—	24	35	83	1,730	—	—	—	F-117A
F404-GE-400	16,000	1.85	—	26	35	154	2,195	—	—	0.34	F/A-18A/B, F-5G
F414-GE-400	22,000	—	—	30	35	154	—	—	—	—	F/A-18E/F
JT3D-3B	18,000	0.535	458	13.6	53	136.4	4,300	1,600	1.74	1.37	(TF33-102) EC/RC-l35
JT8D-7B	14,500	0.585	318	16.9	45	123.7	3.252	1,076	—	1.03	C-22, C-9, T-43A
TF30-P-111	25,100 14,560	2.450 0.686	260	21.8	49	241.7	3,999	2,055	2.43	0.73	F-111F
TF33-P-3	17,000	0.52	450	13.0	53	136	3,900	1,600	1.7	1.55	B-52H
TF33-P-7	21,000	0.56	498	16.0	54	142	4,650	1,750	1.9	1.21	C-141
TF34-GE-100	9,065	0.37	333	20.0	50	100	1,421	2,234	1.5	6.42	A-10
TF39-GE-1	40,805	0.315	1,549	26.0	100	203	7,186	2,350	1.56	8.0	C-5A
TF41-A-1B	14,500	0.647	260	20.0	40	114.5	3,511	2,165	2.45	0.76	A-7D, K
TFE731-2	3,500	0.504	113	17.7	40	50	625	—	1.54	2.67	C-21A

OPR = overall pressure ratio, FPR = fan pressure ratio, TSFC = thrust specific fuel consumption, TIT = turbine inlet temperature, BR = bypass ratio

*Maximum/Military Power @ SLS

Sources: The Engine Handbook, Directorate of Propulsion, Headquarters Air Force Logistics Command, Wright-Patterson AFB, Ohio, 1991 and manufacturers’ literature