Comparison of orbital rocket engines

This page is an incomplete list of orbital rocket engine data.

Engine data

Legend for below table:   [under development] — [retired,canceled] — [operational,inactive]

Engine	Origin	Manufacturer	Vehicle	Use	Propellant	Specific Impulse, Vac (s)	Specific Impulse, SL (s)	Thrust, Vac (N)	Thrust, SL (N)	Mass (kg)	Thrust-to-weight ratio	Combustion chamber pressure (bar)	Status	Engine
Aestus II[1]	Europe	Airbus Defence and Space	Ariane 5	Upper	N2O4/MMH	340[1]		55,400[1]		138[1]	40.9?[note 1]	60[1]	Development	Aestus II
Aestus[2]	Europe	Airbus Defence and Space	Ariane 5 ES	Upper	N2O4/MMH	324[2]		30,000[2]		111[2]	27.6?[note 2]	11[2]	Operational	Aestus
AR1	United States	Aerojet Rocketdyne	Vulcan	1st	RP-1/LOX				2,200,000[3]				Development	AR1
Atlas V SRB	United States	Aerojet	Atlas V	Booster	Solid	275[4]		1,270,000[4]					Operational	Atlas V SRB
BE-3	United States	Blue Origin	New Shepard	1st	LH2/LOX			490,000					Operational	BE-3
BE-4[5][6]	United States	Blue Origin	New Glenn Vulcan	1st	Methane/LOX			2,400,000[5][6]				134[7]	Development	BE-4
Boeing 601HP First ever ion engine used as a main engine on an operational commercial satellite (PAS-5)	United States	Boeing	Boeing 601HP satellites	Ion thruster	Xenon	2,568 @0.5 kW		0.018 @0.5 kW					Operational	Boeing 601HP
Boeing 702	United States	Boeing	Boeing 702 satellites	Ion thruster	Xenon	3,800 @4.5 kW		0.165 @4.5 kW					Operational	Boeing 702
CE-20	India	ISRO	LVM3	Upper	LH2/LOX	443		45,000		588		60.00	Development	CE-20
CE-7.5[8][9]	India	ISRO	GSLV Mk II	Upper	LH2/LOX	454[9]		73,550[8]		445[9]	16.85?[note 3]	58	Operational	CE-7.5
F-1 Most powerful single-chamber liquid-fueled rocket engine ever developed	United States	Rocketdyne	Saturn V	1st	RP-1/LOX	304	263	7,770,000	6,770,000	8,391	82.27?[note 4]	70	Retired	F-1
Gamma 2[10]	UK	Bristol Siddeley	Black Arrow	2nd	H2O2/Kerosene	265[10]		68,200[10]		173[10]	40.22[10]		Retired	Gamma 2
Gamma 8[11]	UK	Bristol Siddeley	Black Arrow	1st	H2O2/Kerosene	265[11]		234,800[11]		342[11]	70.01[11]	47.40[11]	Retired	Gamma 8
HiPEP Most efficient inert gas ion thruster ever built	United States	NASA	Jupiter Icy Moons Orbiter	Ion thruster	Xenon	9,620 @39.3 kW		0.670 @39.3 kW					Canceled	HiPEP
HM7B[12][13]	Europe	Snecma	Ariane 5 ECA	Upper	LH2/LOX	446[13]	310[12]	64,800[13]	43,600[12]	165[13]	40.05?[note 5]	37[13]	Operational	HM7B
J-2[14]	United States	Rocketdyne	Saturn V Saturn IB	2nd, 3rd	LH2/LOX	421		1,033,100		1,438	73.18	30	Retired	J-2
J-2X[15][16]	United States	Pratt & Whitney Rocketdyne	Space Launch System	Upper	LH2/LOX	448		1,310,000		2,430[16]	54.97?[note 6]	30	Development	J-2X
LE-5	Japan	Mitsubishi Heavy Industries NASDA	H-I	Upper	LH2/LOX	450[17]		103,000[17]		245[17]	42.87[note 7]	36.0[17]	Retired	LE-5
LE-5A	Japan	Mitsubishi Heavy Industries NASDA	H-II	Upper	LH2/LOX	452[18]		121,500[18]		242[18]	51.19[note 8]	40.0[18]	Retired	LE-5A
LE-5B	Japan	Mitsubishi Heavy Industries JAXA	H-IIA H-IIB	Upper	LH2/LOX	447[19]		137,000[19]		269[19]	51.93[note 9]	36.0[19]	Operational	LE-5B
LE-7	Japan	Mitsubishi Heavy Industries NASDA	H-II	1st	LH2/LOX	446[20]		1,078,000[20]	843,500[20]	1,714[20]	64.13[20]	127[20]	Retired	LE-7
LE-7A	Japan	Mitsubishi Heavy Industries JAXA	H-IIA H-IIB	1st	LH2/LOX	438[21]	338[21]	1,098,000[21]		1,800[21]	62.2[note 10]	121[21]	Operational	LE-7A
Merlin 1C	United States	SpaceX	Falcon 9 Falcon 1	1st,2nd	RP-1/LOX	304[22]	266[23]	480,408[22]	422,581[22]	630	92[22]	67.7	Retired	Merlin 1C
Merlin 1D	United States	SpaceX	Falcon 9 v1.1	1st	RP-1/LOX	311 [24]	282 [24]	723,000[25]		470[25]	158[25]	97	Retired	Merlin 1D
Merlin 1D FT	United States	SpaceX	Falcon 9 v1.1 FT Falcon Heavy	1st	RP-1/LOX	311 [24]	282 [24]	914,000[26]	845,000[26]	470[25]	199.5[26]	97	Operational	Merlin 1D FT
Merlin Vacuum 1C	United States	SpaceX	Falcon 9 Falcon 1	2nd	RP-1/LOX	336[23]		413,644[23]			92		Retired	Merlin Vacuum 1C
Merlin Vacuum 1D	United States	SpaceX	Falcon 9 Falcon Heavy	2nd	RP-1/LOX	348[27]		934,000[27]					Operational	Merlin Vacuum 1D
NewtonFour	United States	Virgin Galactic	LauncherOne	2nd	RP-1/LOX			22,241[28]					Development	NewtonFour
NewtonThree	United States	Virgin Galactic	LauncherOne	Booster	RP-1/LOX			266,893[29]					Development	NewtonThree
NEXT	United States	NASA		Ion thruster	Xenon	4,100 @6.9 kW		0.236 @6.9 kW					Development	NEXT
NK-33A (AJ26-58)[30] 11Д111	Soviet Union	Kuznetsov Design Bureau Aerojet	Antares Soyuz-2.1v	1st	RP-1/LOX	331[30]		1,638,000[30]		1,222[30]	136.8[30]	145[30]	Operational	NK-33-1 (AJ26-58)
NSTAR[31][32] First ever ion engine used as a main engine on an operational science spacecraft	United States	Hughes Electron Dynamics Boeing	Deep Space 1 Dawn	Ion thruster	Xenon	3,100 @2.3 kW		0.0920 @2.3 kW		8.2			Operational	NSTAR
P230[33]	Europe	SNPE (Societe Nationale des Poudres et Explosifs)	Ariane 5	Booster	HTPB(68/18)	286[33]	259[33]	6,472,300[33]	5,861,300[33]	269,000 with fuel[33]			Operational	P230
PPS-1350	Russia  Europe	OKB Fakel Snecma	SMART-1	Hall thruster	Xenon	1,650 @1.5 kW		0.088 @1.5 kW		5.3			Operational	PPS-1350
PSLV-1[34]	India	ISRO	PSLV	1st	HTPB	269[34]		486,000[34]		160,200[34]		58[34]	Operational	PSLV-1
Raptor Vacuum[35]	United States	SpaceX	Interplanetary Transport System	2nd[36]	Methane/LOX[35]	382[37]		3,500,000[37]				300[37]	Development	Raptor Vacuum
Raptor[35]	United States	SpaceX	Interplanetary Transport System	1st,2nd (incl. 2nd-stage use as Earth & planetary lander)[38][37]	Methane/LOX[35]	361[37]	334[37]	~3,285,000[37]	3,050,000[37]			300[37]	Development	Raptor
RD-0120[39] 11Д122	Soviet Union	KBKhA	Energia	1st	LH2/LOX	455[39]		1,962,000[39]		3,450[39]	57.80	219	Retired	RD-0120
RD-0124[40] 14Д23	Russia	TsSKB Progress	Soyuz-2.1b Soyuz-2-1v Angara	2nd,3rd	RP-1/LOX	359[40]		294,300[40]		520[40]	57.7[note 11]	160[40]	Operational	RD-0124
RD-107A[41] 14Д22	Russia	NPO Energomash	Soyuz-FG Soyuz-2	1st	RP-1/LOX	320.2[41]	263.3[41]	1,019,892[41]	839,449[41]	1,090[41]	78.53[note 12]	61.2[41]	Operational	RD-107A
RD-108A[41] 14Д21	Russia	NPO Energomash	Soyuz-FG Soyuz-2	2nd	RP-1/LOX	320.6[41]	257.7[41]	921,825[41]	792,377[41]	1,075[41]	75.16[note 13]	55.5[41]	Operational	RD-108A
RD-117[42] 11Д511	Soviet Union	NPO Energomash	Soyuz-U	1st	RP-1/LOX	316[42]	253[42]	978,000[43]	778,648[42]	1,100[42]	72.18[note 14]	54.2[42]	Operational	RD-117
RD-118[42] 11Д512	Soviet Union	NPO Energomash	Soyuz-U	2nd	RP-1/LOX	314[42]	257[42]	1,000,278[42]	818,855[42]	1,100[42]	75.91[note 15]	59.7[42]	Operational	RD-118
RD-171M[44] Most powerful multi-chamber rocket engine in the world	Russia	NPO Energomash	Zenit-2M Zenit-3SL Zenit-3SLB Zenit-3SLBF	1st	RP-1/LOX	337.2[44]	309.5[44]	7,904,160[44]	7,256,921[44]	9,300[44]	79.57[note 16]	250[44]	Operational	RD-171M
RD-180[45]	Russia	NPO Energomash	Atlas V Atlas III	1st	RP-1/LOX	338.4[45]	311.9[45]	4,152,136[45]	3,826,555[45]	5,480[45]	71.2[note 17]	261.7[45]	Operational	RD-180
RD-181	Russia	NPO Energomash	Antares	1st	RP-1/LOX	337.5							Development	RD-181
RD-191[46]	Russia	NPO Energomash	Angara	1st	RP-1/LOX	337.5[46]	311.2[46]	2,084,894[46]	1,922,103[46]	2,200[46]	89.09[note 18]	262.6[46]	Operational	RD-191
RD-193[47][48]	Russia	NPO Energomash	Soyuz-2.1v	1st	RP-1/LOX	337.5[48]	311.2[48]	2,084,894[48]	1,922,103[48]	1,900[47][48]	103.15[note 19]		Development	RD-193
RD-264[42] 11Д119	Soviet Union	NPO Energomash	Dnepr	1st	N2O4/UDMH	318.4[42]	293.3[42]	4,511,059[42]	4,158,020[42]	3,600[42]	117.77[note 20]	210[42]	Operational	RD-264
RD-275M[49] 14Д14М	Russia	NPO Energomash	Proton-M	1st	N2O4/UDMH	315.8[49]	288[49]	1,831,882[49]	1,671,053[49]	1,070[49]	159.25[note 21]	165.2[49]	Operational	RD-275M
RD-56(KVD-1)[50] 11Д56У	Russia	KBKhM	GSLV Mk I	Upper	LH2/LOX	462[50]		69,626[50]		282[50]	25.17	55.9	Retired	RD-56(KVD-1)
RL-10A-4-2[51][52]	United States	Pratt & Whitney Rocketdyne	Atlas V	Upper	LH2/LOX	451		99,100		167	59	39	Operational	RL-10A-4-2
RL-10B-2[53][51]	United States	Pratt & Whitney Rocketdyne	Delta III Delta IV	Upper	LH2/LOX	462		109,890		277	41	44	Operational	RL-10B-2
RS-25 - SSME	United States	Pratt & Whitney Rocketdyne	Space Shuttle	1st	LH2/LOX	452.3		2,279,000		3,526	53.79[note 22]	206.4	Inactive since STS-135	RS-25
RS-68A[54] Most powerful hydrogen-fueled engine in the world	United States	Pratt & Whitney Rocketdyne	Delta IV Delta IV Heavy	1st	LH2/LOX	414[54]		3,560,000[54]	3,137,000[54]	6,747[54]	53.80[note 23]	196[54]	Operational	RS-68A
Rutherford	New Zealand	Rocket Lab	Electron	1st, 2nd	LOX/RP-1	327		22,000	16,890				Certified for flight	Rutherford
S200[55]	India	ISRO	LVM3	Booster	HTPB	274.5[55]		5,150,000[56][57] [58]		207,000[55]			Operational	S200
SCE-200	India	ISRO	LVM3/Unified Launch Vehicle	Upper/Main	RP-1/LOX	335	299	460,000	410,000	2700		18	Development	SCE-200
SLS Solid Rocket Booster Largest, most powerful solid-fuel rocket motor ever built	United States	Orbital ATK	SLS	Booster	PBAN	267		16,000,000		730,000 with fuel			Development	SLS Solid Rocket Booster
SLV-1[59]	India	ISRO	PSLV	Booster	HTPB	253[59]		502,600[59]		10,800[59]		43[59]	Operational	SLV-1
Space Shuttle Solid Rocket Booster Largest solid-fuel rocket motor ever flown, and the first to be used for primary propulsion on human spaceflight missions	United States	Thiokol	Space Shuttle Ares I	Booster	APCP	268		14,000,000	12,500,000	590,000 with fuel			Inactive since STS-135	Space Shuttle Solid Rocket Booster
SPT-100	Russia	OKB Fakel	LS-1300 satellites	Hall thruster	Xenon	1,500 @1.35 kW		0.083 @1.35 kW		3.5			Operational	SPT-100
SRB-A	Japan	IHI Aerospace JAXA	H-IIA	Booster	HTPB	280[60]		2,250,000[60]		76,400 with fuel[60]		118[60]	Operational	SRB-A
SRB-A3	Japan	IHI Aerospace JAXA	H-IIB	Booster	BP-207J[61]	283.6[61]		2,305,000[61]	2,150,000[61]	76,600 with fuel[61]		111[61]	Operational	SRB-A3
UA1207[62]	United States	United Technologies	Titan IV	Booster	PBAN	272	245	7,116,000	6,410,400	319,330 with fuel			Retired	UA1207
VASIMR	United States	Ad Astra Rocket Company		Electro-magnetic thruster	Argon	5,000 @200 kW		5.7 @200 kW					Development	VASIMR
Vikas (rocket engine)	India	ISRO	PSLV/GSLV/LVM3	Second/Main/Booster	N2O4/UDMH	262		680,500-804,500	600,500-756,500			5.30-5.85	Operational	Vikas (rocket engine)
Vinci[63][64]	Europe	Snecma	Ariane 6	Upper	LH2/LOX	465[63]		180,000[63]		280[64]	65.55[note 24]	60.8[63]	Development	Vinci
Vulcain 2[65][66]	Europe	Snecma	Ariane 5	1st	LH2/LOX	429[66]	318[65]	1,359,000[66]	939,500[65]	1,800[65]	76.99?[note 25]	117.3[66]	Operational	Vulcain 2
Vulcain[67][68] HM-60	Europe	Snecma	Ariane 5	1st	LH2/LOX	439[68]	326[67]	1,113,000[68]	773,200[67]	1,300[67]	84.318[67]	109[68]	Retired	Vulcain
Waxwing[69]	UK	Bristol Aerojet	Black Arrow	Upper	Solid	278[69]		29,400[69]		87[69]			Retired	Waxwing
YF-100	China	CASC	Long March 5, Long March 6 and Long March 7[70] [71] [72]	Long March 5 K-3-1 and K-2-1 boosters, Long March 6 first stage and Long March 7 first stage and boosters.[73] [74] [75]	RP-1/LOX[76]	335[76]	300[76]	1,340,000[76]	1,200,000[76]				Operational	YF-100
YF-21C	China	CASC	Long March 2,3	1st	N2O4/UDMH		260.7[77]		2,961,600[77]				Operational	YF-21C
YF-24E	China	CASC	Long March 2,3	2nd	N2O4/UDMH	298.0[77]		742,000[77]					Operational	YF-24E
YF-75	China	CALT	Long March 3	3rd	LH2/LOX	438.0[77]		167,170[77]					Operational	YF-75

See also

• Comparison of orbital launch systems
• Comparison of orbital launchers families
• Comparison of orbital spacecraft
• Comparison of space station cargo vehicles
• Comparison of solid-fuelled orbital launch systems
• List of space launch system designs
• List of orbital launch systems

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Notes

1. ${\frac {55,400\ {\mathrm {N}}}{(138\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=40.9$
2. ${\frac {30,000\ {\mathrm {N}}}{(111\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=27.6$
3. ${\frac {73,550\ {\mathrm {N}}}{(445\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=16.85$
4. ${\frac {6,770,000\ {\mathrm {N}}}{(8,391\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=82.27$
5. ${\frac {64,800\ {\mathrm {N}}}{(165\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=40.05$
6. ${\frac {1,310,000\ {\mathrm {N}}}{(2,430\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=54.97$
7. ${\displaystyle {\frac {103,000\ \mathrm {N} }{(245\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=42.87}$
8. ${\displaystyle {\frac {121,500\ \mathrm {N} }{(242\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=51.19}$
9. ${\displaystyle {\frac {137,000\ \mathrm {N} }{(269\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=51.93}$
10. ${\displaystyle {\frac {1,098,000\ \mathrm {N} }{(1,800\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=62.2}$
11. ${\displaystyle {\frac {294,300\ \mathrm {N} }{(480\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=57.7}$
12. ${\frac {839,449\ {\mathrm {N}}}{(1,090\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=78.53$
13. ${\frac {792,377\ {\mathrm {N}}}{(1,075\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=75.16$
14. ${\frac {778,648\ {\mathrm {N}}}{(1,100\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=72.18$
15. ${\frac {818,855\ {\mathrm {N}}}{(1,100\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=75.91$
16. ${\frac {7,256,921\ {\mathrm {N}}}{(9,300\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=79.57$
17. ${\displaystyle {\frac {3,826,555\ \mathrm {N} }{(5,480\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=71.2}$
18. ${\frac {1,922,103\ {\mathrm {N}}}{(2,200\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=89.09$
19. ${\displaystyle {\frac {1,922,103\ \mathrm {N} }{(1,900\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=103.15}$
20. ${\frac {4,158,020\ {\mathrm {N}}}{(3,600\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=117.77$
21. ${\frac {1,671,053\ {\mathrm {N}}}{(1,070\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=159.25$
22. ${\frac {1,860,000\ {\mathrm {N}}}{(3,526\ {\mathrm {kg}})(9.807\ {\mathrm {m/s^{2}}})}}=53.79$
23. ${\displaystyle {\frac {3,560,000\ \mathrm {N} }{(6,747\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=53.80}$
24. ${\displaystyle {\frac {180,000\ \mathrm {N} }{(280\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=65.55}$
25. ${\displaystyle {\frac {1,359,000\ \mathrm {N} }{(1,800\ \mathrm {kg} )(9.807\ \mathrm {m/s^{2}} )}}=76.99}$