Comparison of orbital rocket engines

This page exposes an incomplete list of orbital rocket engines.

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

Engine	Origin	Manufacturer	Vehicle	Stage	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
Vulcain[1][2] HM-60	Europe	Snecma	Ariane 5	1st	LH2/LOX	439[2]	326[1]	1,113,000[2]	773,200[1]	1,300[1]	84.318[1]	109[2]	Retired	Vulcain
Vulcain 2[3][4]	Europe	Snecma	Ariane 5	1st	LH2/LOX	429[4]	318[3]	1,359,000[4]	939,500[3]	1,800[3]	76.99?[note 1]	117.3[4]	Operational	Vulcain 2
P230[5]	Europe	SNPE (Societe Nationale des Poudres et Explosifs)	Ariane 5	Booster	HTPB(68/18)	286[5]	259[5]	6,472,300[5]	5,861,300[5]	269,000 with fuel[5]			Operational	P230
HM7B[6][7]	Europe	Snecma	Ariane 5 ECA	Upper	LH2/LOX	446[7]	310[6]	64,800[7]	43,600[6]	165[7]	40.05?[note 2]	37[7]	Operational	HM7B
Vinci[8][9]	Europe	Snecma	Ariane 6	Upper	LH2/LOX	465[8]		180,000[8]		280[9]	65.55[note 3]	60.8[8]	Development	Vinci
RD-180[10]	Russia	NPO Energomash	Atlas V Atlas III	1st	RP-1/LOX	338.4[10]	311.9[10]	4,152,136[10]	3,826,555[10]	5,480[10]	71.2[note 4]	261.7[10]	Operational	RD-180
RD-191[11]	Russia	NPO Energomash	Angara	1st	RP-1/LOX	337.5[11]	311.2[11]	2,084,894[11]	1,922,103[11]	2,200[11]	89.09[note 5]	262.6[11]	Operational	RD-191
RD-0124[12] 14Д23	Russia	TsSKB Progress	Soyuz-2.1b Soyuz-2-1v Angara	2nd,3rd	RP-1/LOX	359[12]		294,300[12]		520[12]	57.7[note 6]	160[12]	Operational	RD-0124
NK-33A (AJ26-58)[13] 11Д111	Soviet Union	Kuznetsov Design Bureau Aerojet	Antares Soyuz-2.1v	1st	RP-1/LOX	331[13]		1,638,000[13]		1,222[13]	136.8[13]	145[13]	Operational	NK-33-1 (AJ26-58)
Gamma 8[14]	UK	Bristol Siddeley	Black Arrow	1st	H2O2/Kerosene	265[14]		234,800[14]		342[14]	70.01[14]	47.40[14]	Retired	Gamma 8
Gamma 2[15]	UK	Bristol Siddeley	Black Arrow	2nd	H2O2/Kerosene	265[15]		68,200[15]		173[15]	40.22[15]		Retired	Gamma 2
Waxwing[16]	UK	Bristol Aerojet	Black Arrow	Upper	Solid	278[16]		29,400[16]		87[16]			Retired	Waxwing
Merlin 1C	United States	SpaceX	Falcon 9 Falcon 1	1st,2nd	RP-1/LOX	304[17]	266[18]	480,408[17]	422,581[17]	630	92[17]	67.7	Retired	Merlin 1C
Merlin Vacuum 1C	United States	SpaceX	Falcon 9 Falcon 1	2nd	RP-1/LOX	336[18]		413,644[18]			92		Retired	Merlin Vacuum 1C
Merlin 1D	United States	SpaceX	Falcon 9 v1.1	1st	RP-1/LOX	311 [19]	282 [19]	723,000[20]		470[20]	158[20]	97	Retired	Merlin 1D
Merlin 1D FT	United States	SpaceX	Falcon 9 v1.1 FT Falcon Heavy	1st	RP-1/LOX	311 [19]	282 [19]	825,000[21]	756,000[21]	470[20]	180[20]	97	Operational	Merlin 1D FT
Merlin Vacuum 1D	United States	SpaceX	Falcon 9 Falcon Heavy	2nd	RP-1/LOX	348[22]		934,000[22]					Operational	Merlin Vacuum 1D
Raptor[23]	United States	SpaceX		1st,2nd[24]	Methane/LOX[23]	363[23]		2,300,000[25]					Development	Raptor
RD-171M[26] Most powerful liquid-fuel rocket engine in the world	Russia	NPO Energomash	Zenit-2M Zenit-3SL Zenit-3SLB Zenit-3SLBF	1st	RP-1/LOX	337.2[26]	309.5[26]	7,904,160[26]	7,256,921[26]	9,300[26]	79.57[note 7]	250[26]	Operational	RD-171M
RD-107A[27] 14Д22	Russia	NPO Energomash	Soyuz-FG Soyuz-2	1st	RP-1/LOX	320.2[27]	263.3[27]	1,019,892[27]	839,449[27]	1,090[27]	78.53[note 8]	61.2[27]	Operational	RD-107A
RD-108A[27] 14Д21	Russia	NPO Energomash	Soyuz-FG Soyuz-2	2nd	RP-1/LOX	320.6[27]	257.7[27]	921,825[27]	792,377[27]	1,075[27]	75.16[note 9]	55.5[27]	Operational	RD-108A
RD-117[28] 11Д511	Soviet Union	NPO Energomash	Soyuz-U	1st	RP-1/LOX	316[28]	253[28]	978,000[29]	778,648[28]	1,100[28]	72.18[note 10]	54.2[28]	Operational	RD-117
RD-118[28] 11Д512	Soviet Union	NPO Energomash	Soyuz-U	2nd	RP-1/LOX	314[28]	257[28]	1,000,278[28]	818,855[28]	1,100[28]	75.91[note 11]	59.7[28]	Operational	RD-118
LE-5	Japan	Mitsubishi Heavy Industries NASDA	H-I	Upper	LH2/LOX	450[30]		103,000[30]		245[30]	42.87[note 12]	36.0[30]	Retired	LE-5
LE-5A	Japan	Mitsubishi Heavy Industries NASDA	H-II	Upper	LH2/LOX	452[31]		121,500[31]		242[31]	51.19[note 13]	40.0[31]	Retired	LE-5A
LE-5B	Japan	Mitsubishi Heavy Industries JAXA	H-IIA H-IIB	Upper	LH2/LOX	447[32]		137,000[32]		269[32]	51.93[note 14]	36.0[32]	Operational	LE-5B
LE-7	Japan	Mitsubishi Heavy Industries NASDA	H-II	1st	LH2/LOX	446[33]		1,078,000[33]	843,500[33]	1,714[33]	64.13[33]	127[33]	Retired	LE-7
LE-7A	Japan	Mitsubishi Heavy Industries JAXA	H-IIA H-IIB	1st	LH2/LOX	438[34]	338[34]	1,098,000[34]		1,800[34]	62.2[note 15]	121[34]	Operational	LE-7A
SRB-A	Japan	IHI Aerospace JAXA	H-IIA	Booster	HTPB	280[35]		2,250,000[35]		76,400 with fuel[35]		118[35]	Operational	SRB-A
SRB-A3	Japan	IHI Aerospace JAXA	H-IIB	Booster	BP-207J[36]	283.6[36]		2,305,000[36]	2,150,000[36]	76,600 with fuel[36]		111[36]	Operational	SRB-A3
RS-68A[37] Most powerful hydrogen-fueled engine in the world	United States	Pratt & Whitney Rocketdyne	Delta IV Delta IV Heavy	1st	LH2/LOX	414[37]		3,560,000[37]	3,137,000[37]	6,747[37]	53.80[note 16]	196[37]	Operational	RS-68A
Atlas V SRB	United States	Aerojet	Atlas V	Booster	Solid	275[38]		1,270,000[38]					Operational	Atlas V SRB
F-1 Most powerful single-chamber liquid-fueled rocket engine ever developed	United States	Rocketdyne	Saturn V	1st	RP-1/LOX	263		7,770,000	6,770,000	8,391	82.27?[note 17]	70	Retired	F-1
RS-25 - SSME	United States	Pratt & Whitney Rocketdyne	Space Shuttle	1st	LH2/LOX	452.3		2,279,000		3,526	53.79[note 18]	206.4	Inactive since STS-135	RS-25
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
UA1207[39]	United States	United Technologies	Titan IV	Booster	PBAN	272	245	7,116,000	6,410,400	319,330 with fuel			Retired	UA1207
J-2[40]	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[41][42]	United States	Pratt & Whitney Rocketdyne	Space Launch System	Upper	LH2/LOX	448		1,310,000		2,430[42]	54.97?[note 19]	30	Development	J-2X
RL-10B-2[43][44]	United States	Pratt & Whitney Rocketdyne	Delta III Delta IV	Upper	LH2/LOX	462		109,890		277	41	44	Operational	RL-10B-2
RL-10A-4-2[44][45]	United States	Pratt & Whitney Rocketdyne	Atlas V	Upper	LH2/LOX	451		99,100		167	59	39	Operational	RL-10A-4-2
NSTAR[46][47] 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
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
NEXT	United States	NASA		Ion thruster	Xenon	4,100 @6.9 kW		0.236 @6.9 kW					Development	NEXT
VASIMR	United States	Ad Astra Rocket Company		Electro-magnetic thruster	Argon	5,000 @200 kW		5.7 @200 kW					Development	VASIMR
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
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
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
RD-56(KVD-1)[48] 11Д56У	Russia	KBKhM	GSLV Mk I	Upper	LH2/LOX	462[48]		69,626[48]		282[48]	25.17	55.9	Retired	RD-56(KVD-1)
CE-7.5[49][50]	India	ISRO	GSLV Mk II	Upper	LH2/LOX	454[50]		73,550[49]		445[50]	16.85?[note 20]	58	Operational	CE-7.5
PSLV-1[51]	India	ISRO	PSLV	1st	HTPB	269[51]		486,000[51]		160,200[51]		58[51]	Operational	PSLV-1
SLV-1[52]	India	ISRO	PSLV	Booster	HTPB	253[52]		502,600[52]		10,800[52]		43[52]	Operational	SLV-1
S200[53]	India	ISRO	LVM3	Booster	HTPB	274.5[53]		5,150,000[54][55] [56]		207,000[53]			Operational	S200
RD-264[28] 11Д119	Soviet Union	NPO Energomash	Dnepr-1	1st	N2O4/UDMH	318.4[28]	293.3[28]	4,511,059[28]	4,158,020[28]	3,600[28]	117.77[note 21]	210[28]	Operational	RD-264
YF-100	China	CASC	Long March 5, Long March 6 and Long March 7[57] [58] [59]	Long March 5 K-3-1 and K-2-1 boosters, Long March 6 first stage and Long March 7 first stage and boosters.[60] [61] [62]	RP-1/LOX[63]	335[63]	300[63]	1,340,000[63]	1,200,000[63]				Development	YF-100
YF-21C	China	CASC	Long March 2,3	1st	N2O4/UDMH		260.7[64]		2,961,600[64]				Operational	YF-21C
YF-24E	China	CASC	Long March 2,3	2nd	N2O4/UDMH	298.0[64]		742,000[64]					Operational	YF-24E
YF-75	China	CALT	Long March 3	3rd	LH2/LOX	438.0[64]		167,170[64]					Operational	YF-75
RD-275M[65] 14Д14М	Russia	NPO Energomash	Proton-M	1st	N2O4/UDMH	315.8[65]	288[65]	1,831,882[65]	1,671,053[65]	1,070[65]	159.25[note 22]	165.2[65]	Operational	RD-275M
RD-0120[66] 11Д122	Soviet Union	KBKhA	Energia	1st	LH2/LOX	455[66]		1,962,000[66]		3,450[66]	57.80	219	Retired	RD-0120
RD-193[67][68]	Russia	NPO Energomash	Soyuz-2.1v	1st	RP-1/LOX	337.5[68]	311.2[68]	2,084,894[68]	1,922,103[68]	1,900[67][68]	103.15[note 23]		Development	RD-193
RD-181	Russia	NPO Energomash	Antares	1st	RP-1/LOX	337.5							Development	RD-181
Aestus[69]	Europe	Airbus Defence and Space	Ariane 5 ES	Upper	N2O4/MMH	324[69]		30,000[69]		111[69]	27.6?[note 24]	11[69]	Operational	Aestus
Aestus II[70]	Europe	Airbus Defence and Space	Ariane 5	Upper	N2O4/MMH	340[70]		55,400[70]		138[70]	40.9?[note 25]	60[70]	Development	Aestus II
BE-3	United States	Blue Origin	New Shepard	1st	LH2/LOX			490,000					Operational	BE-3
BE-4[71][72]	United States	Blue Origin	Atlas V Vulcan	1st	Methane/LOX			2,400,000[71][72]					Development	BE-4
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

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

References

1. "Vulcain". Encyclopedia Astronautica. Retrieved 27 December 2011.
2. EADS Astrium. "Vulcain Astrium". Airbus Defence and Space. Retrieved 27 December 2011.
3. "Vulcain 2". Encyclopedia Astronautica. Retrieved 27 December 2011.
4. EADS Astrium. "Vulcain 2 Astrium". Airbus Defence and Space. Retrieved 29 September 2015.
5. "P230". Encyclopedia Astronautica. Retrieved 27 December 2011.
6. "HM7-B". Encyclopedia Astronautica. Retrieved 27 April 2012.
7. EADS Astrium. "HM7-B Astrium". Airbus Defence and Space. Retrieved 1 November 2015.
8. EADS Astrium. "Vinci Astrium". Airbus Defence and Space. Retrieved 29 September 2015.
9. "Vinci". Encyclopedia Astronautica. Retrieved 1 November 2015.
10. "RD-180". NPO Energomash. Retrieved 30 June 2015.
11. "RD-191". NPO Energomash. Retrieved 30 June 2015.
12. "RD-0124 Engine". KBKha. Retrieved 7 January 2016.
13. "NK-33". Encyclopedia Astronautica. Archived from the original on 30 January 2014. Retrieved 30 January 2014.
14. "Gamma 8". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
15. "Gamma 2". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
16. "Black Arrow-3". Encyclopedia Astronautica. Archived from the original on 26 April 2013. Retrieved 26 April 2013.
17. "Updates: December 2007". SpaceX. Archived from the original on 2008-08-08.
18. "Falcon 9 Space Launch Report". SpaceLaunchReport. Retrieved 2015-11-01.
19. "Merlin section of Falcon 9 page". SpaceX. Archived from the original on 2013-07-15. Retrieved 2012-10-16.
20. "Is SpaceX's Merlin 1D's thrust-to-weight ratio of 150+ believable? - Quora". www.quora.com. Retrieved 2015-12-11.
21. "Merlin 1D". SpaceX. Retrieved 1 November 2015.
22. "SpaceX Falcon 9 Product Page". Retrieved 2015-11-01.
23. "Spacex Raptor". NASA SpaceFlight. 7 March 2014. Retrieved 2 July 2015.
24. http://www.defense.gov/News/Contracts/Contract-View/Article/642983. Missing or empty |title= (help)
25. Musk, Elon. "I am Elon Musk, CEO/CTO of a rocket company, AMA!". reddit.com. Retrieved 2015-06-01. Thrust to weight is optimizing for a surprisingly low thrust level, even when accounting for the added mass of plumbing and structure for many engines. Looks like a little over 230 metric tons (~500 klbf) of thrust per engine, but we will have a lot of them :)
26. "RD-171M". NPO Energomash. Retrieved 30 June 2015.
27. "RD-107A and RD-108A". NPO Energomash. Retrieved 30 June 2015.
28. "NPO Energomash Engines". NPO Energomash. Retrieved 30 June 2015.
29. "RD-117". lpre.de. Archived from the original on 27 November 2012. Retrieved 27 November 2012.
30. "LE-5". Encyclopedia Astronautica. Retrieved 13 January 2016.
31. "LE-5A". Encyclopedia Astronautica. Retrieved 13 January 2016.
32. "LE-5B". Encyclopedia Astronautica. Retrieved 13 January 2016.
33. "LE-7". Encyclopedia Astronautica. Retrieved 13 January 2016.
34. "LE-7A". Encyclopedia Astronautica. Retrieved 13 January 2016.
35. "SRB-A". Encyclopedia Astronautica. Retrieved 13 January 2016.
36. "SRB-A3". Spaceflight101. Retrieved 13 January 2016.
37. "RS-68A - Delta IV Heavy". Spaceflight101.com. Retrieved 2 November 2015.
38. "Atlas V Solid Rocket Motor". Aerojet Rocketdyne. Retrieved 2015-06-02.
39. "UA1207". Encyclopedia Astronautica. Archived from the original on 27 December 2015. Retrieved 27 December 2015.
40. "J-2". Encyclopedia Astronautica. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
41. "J-2X Engine". Pratt & Whitney Rocketdyne. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
42. "J-2X". Encyclopedia Astronautica. Archived from the original on 23 December 2011. Retrieved 23 December 2011.
43. "RL-10B-2". Encyclopedia Astronautica. 23 December 2011. Archived from the original on 23 December 2011.
44. "RL-10 - Specifications". Spaceandtech. 23 December 2011. Archived from the original on 23 December 2011.
45. "RL-10A-4-2". Encyclopedia Astronautica. 23 December 2011. Archived from the original on 23 December 2011.
46. Sovey, J. S., Rawlin, V. K., and Patterson, M. J. (May–June 2001). "Ion Propulsion Development Projects in U. S.: Space Electric Rocket Test 1 to Deep Space 1.". Journal of Propulsion and Power 17 (3): 517–526.
47. "Hughes' Ion Engine Serving as Primary Propulsion to NASA's Deep Space 1". www.boeing.com. 24 December 2011. Archived from the original on 24 December 2011.
48. "KVD1 Rocket Engine" Двигатель КВД1 (in Russian). КБХМ им. A.M. Исаева.
49. "Indigenous Cryogenic Engine and Stage". Retrieved 6 January 2014.
50. "GSLV Launch Vehicle Information". Retrieved 6 January 2014.
51. "PSLV-1". Retrieved 4 April 2014.
52. "SLV-1". Retrieved 4 April 2014.
53. "LVM3". Retrieved 21 December 2014.
54. ISRO Press Release: S200 First Static Test (S-200-ST-01)
55. "Isro successfully tests world's 3rd largest solid booster". dna. Retrieved 4 October 2014.
56. "India to test world's third largest solid rocket booster". Science and Technology Section. The Hindu News Paper. 2009-12-07. Retrieved 2009-12-07.
57. Gunter Dirk Krebs. "CZ-5 (Chang Zheng-5)". Gunter's Space Page. Retrieved 2015-07-02.
58. Gunter Dirk Krebs. "CZ-6 (Chang Zheng-5)". Gunter's Space Page. Retrieved 2015-07-02.
59. Gunter Dirk Krebs. "CZ-7 (Chang Zheng-5)". Gunter's Space Page. Retrieved 2015-07-02.
60. "Chang Zheng-5 (Long March-5)". SinoDefence. Retrieved 2015-07-02.
61. "Chang Zheng-6 (Long March-6)". SinoDefence. Retrieved 2015-07-02.
62. "Chang Zheng-7 (Long March-7)". SinoDefence. Retrieved 2015-07-02.
63. "Chinese YF-100 (Russian RD-120) to Power CZ-5". SPACEPAC, The Space Public Affairs Committee. Retrieved 2015-07-02.
64. "2.2 LM-3A Launch Vehicle". LM-3A Series Launch Vehicle User's Manual. Issue 2011 (pdf). CASC. 2011. p. 2–4. Retrieved 2016-01-16.
65. "RD-253 and RD-275M". NPO Energomash. Retrieved 30 June 2015.
66. "RD0120". KBKhA.
67. "Energomash Test Fires New RD-193 Engine". parabolicarc.com.
68. "Универсальный ракетный двигатель РД-193. Мнение инженера-разработчика". Журнал «Новости космонавтики».
69. "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on 29 January 2014. Retrieved 29 January 2014.
70. "Aestus Rocket Engine". Airbus Defence and Space. Archived from the original on 29 January 2014. Retrieved 29 January 2014.
71. Ferster, Warren (2014-09-17). "ULA To Invest in Blue Origin Engine as RD-180 Replacement". Space News. Retrieved 2014-09-19.
72. "BE-4". Blue Origin. Archived from the original on 17 September 2014. Retrieved 17 September 2014.

Notes

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