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Model: Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Country: USA. No Engines: 5. Motor: F-1. Cost $ : 391.500 million. First Flight: 1967. Last Flight: 1973. No Launched: 24.

Configuration as flown.

Model: Saturn S-IC-8. Gross Mass: 3,627,500 kg (7,997,200 lb). Empty Mass: 181,400 kg (399,900 lb). Thrust (vac): 61,925.000 kN (13,921,293 lbf). Isp: 304 sec. Burn time: 157 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 12.19 m (39.99 ft). Span: 22.87 m (75.03 ft). Length: 48.79 m (160.07 ft). Country: USA. No Engines: 8. Motor: F-1. Status: Study 1960.

Model: Saturn IC C-3B. Gross Mass: 1,160,787 kg (2,559,097 lb). Empty Mass: 72,549 kg (159,943 lb). Thrust (vac): 22,954.798 kN (5,160,444 lbf). Isp: 304 sec. Burn time: 140 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 34.41 m (112.89 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1961.

Final first stage design of Saturn C-3 (November 1961).

Model: Saturn IC C-4B. Gross Mass: 1,450,984 kg (3,198,872 lb). Empty Mass: 90,686 kg (199,928 lb). Thrust (vac): 30,606.397 kN (6,880,592 lbf). Isp: 304 sec. Burn time: 130 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 33.46 m (109.77 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1961.

Final first stage design of Saturn C-3 (November 1961). Unique S-IC design in that fuel and propellant tank shared common bulkhead; stage was actually shorter than C-3B S-IC.

Model: Saturn IC C-5A. Gross Mass: 2,217,285 kg (4,888,276 lb). Empty Mass: 131,495 kg (289,896 lb). Thrust (vac): 38,257.990 kN (8,600,738 lbf). Isp: 304 sec. Burn time: 160 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.87 m (140.64 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1961. First Flight: 1961. Last Flight: 1961. No Launched: 1.

Final first stage design of Saturn C-5 (November 1961) before selection as Apollo launch vehicle and development in Saturn V.

Model: Saturn IC-Flat Bulkhead. Gross Mass: 2,278,800 kg (5,023,800 lb). Empty Mass: 127,000 kg (279,000 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 161 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 36.55 m (119.91 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study MSFC 1965.

Standard S-IC but with reduced length and structural weight through use of 'flat' bulkheads consisting of multiple conical sections.

Model: Saturn MS-IC-1A. Gross Mass: 2,694,700 kg (5,940,700 lb). Empty Mass: 160,600 kg (354,000 lb). Thrust (vac): 46,443.300 kN (10,440,869 lbf). Isp: 304 sec. Burn time: 160 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 48.16 m (158.00 ft). Country: USA. No Engines: 6. Motor: F-1. Status: Study 1965.

Basic Saturn IC stretched 240 inches with 6 F-1 engines.

Model: Saturn MS-IC-4(S)B. Gross Mass: 2,875,500 kg (6,339,300 lb). Empty Mass: 154,000 kg (339,000 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 206 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 50.58 m (165.94 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1966.

S-IC with 336 inch stretch, 6,000,0000 lbs propellant, structural strength increased from 56% to 65% depending on station, resulting in 13.9% increase in empty weight.

Model: Saturn S-ID Sustainer-1. Gross Mass: 2,627,600 kg (5,792,800 lb). Empty Mass: 84,400 kg (186,000 lb). Thrust (vac): 7,740.300 kN (1,740,089 lbf). Isp: 304 sec. Burn time: 371 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 48.16 m (158.00 ft). Country: USA. No Engines: 1. Motor: F-1. Status: Study 1967.

Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas; 20 foot stretch of sustainer stage. Booster stage burn 154 seconds in this configuration.

Model: Saturn MS-IC-1. Gross Mass: 2,694,703 kg (5,940,803 lb). Empty Mass: 169,719 kg (374,166 lb). Thrust (vac): 45,948.754 kN (10,329,691 lbf). Isp: 310 sec. Burn time: 158 sec. Propellants: Lox/Kerosene. Isp(sl): 270 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Country: USA. No Engines: 5. Motor: F-1A. Status: Study 1967.

Basic Saturn IC stretched 240 inches with F-1A engines uprated 20% in thrust and 6 second improvement in specific impulse.

Model: Saturn MS-IC/260. Gross Mass: 2,721,600 kg (6,000,100 lb). Empty Mass: 181,400 kg (399,900 lb). Thrust (vac): 38,717.600 kN (8,704,063 lbf). Isp: 304 sec. Burn time: 192 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.05 m (137.95 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1967.

Standard length S-IC but with feed of propellant from fuel and propellant tanks housed above strap-on solid rocket motors

Model: Saturn MS-IC-3B. Gross Mass: 2,718,800 kg (5,993,900 lb). Empty Mass: 178,700 kg (393,900 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 162 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Country: USA. No Engines: 5. Motor: F-1A. Status: Study 1967.

S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission).

Model: Saturn MS-IC-23(L). Gross Mass: 2,694,000 kg (5,939,000 lb). Empty Mass: 169,000 kg (372,000 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 192 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 48.15 m (157.97 ft). Country: USA. No Engines: 5. Motor: F-1. Status: Study 1967.

Basic Saturn IC stretched 240 inches with standard F-1 engines.

Model: Saturn S-ID Sustainer. Gross Mass: 2,219,100 kg (4,892,200 lb). Empty Mass: 68,100 kg (150,100 lb). Thrust (vac): 7,740.300 kN (1,740,089 lbf). Isp: 304 sec. Burn time: 315 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Country: USA. No Engines: 1. Motor: F-1. Status: Study 1968. Used as: Saturn S-ID Booster.

Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage burns 124 seconds in this configuration.

Model: Saturn S-ID Booster. Gross Mass: 67,100 kg (147,900 lb). Empty Mass: 67,100 kg (147,900 lb). Thrust (vac): 30,962.500 kN (6,960,647 lbf). Isp: 304 sec. Burn time: 154 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.01 m (62.36 ft). Length: 42.07 m (138.02 ft). Country: USA. No Engines: 4. Motor: F-1. Status: Study 1968.

Boeing studies, 1967:'Stage and a half' S-1C with four outboard F-1's jettisoned and inboard F-1 functioning as sustainer as in Atlas. Booster half stage recoverable. Mass estimated based on double mass of four F-1's (based on Atlas example).

Model: Saturn MS-IC-25(S). Gross Mass: 3,223,800 kg (7,107,200 lb). Empty Mass: 211,900 kg (467,100 lb). Thrust (vac): 45,925.500 kN (10,324,463 lbf). Isp: 304 sec. Burn time: 192 sec. Propellants: Lox/Kerosene. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 54.70 m (179.40 ft). Country: USA. No Engines: 5. Motor: F-1A. Status: Study 1968.

S-IC with 41.5 foot stretch, 6,640,0000 lbs propellant, uprated F-1 engines.

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© Mark Wade, 1997 - 2008 except where otherwise noted.