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J-2
J-2 -

Credit: © Mark Wade. 29,661 bytes. 304 x 445 pixels.

Manufacturer Name: J-2. Designer: Rocketdyne. Developed in: 1960. Application: . Used on stages: Jarvis-2, Nova 4 J-2, Nova 60-8-3, Nova 9L-3, Nova 9L-4, Nova A-2, Nova B-2, Nova GD-B-2, Nova NASA-3, Saturn II, Saturn II C-5A, Saturn IVB, Saturn IVB (S-IB), Saturn IVB (S-V), Saturn IVB C-3B, Saturn IVB C-5A, Saturn IVB-A, Saturn MS-II-1, Saturn MS-II. Used on launch vehicles: Jarvis, Nova 4S, Nova 5S, Nova 7S, Nova 8L, Nova 8L Mod, Nova 9L, Nova A, Nova B, Nova C, Nova D, Nova GD-B, Nova NASA, Saturn C-2, Saturn C-3, Saturn C-3B, Saturn C-3BN, Saturn C-4, Saturn C-4B, Saturn C-5, Saturn C-5N, Saturn C-8, Saturn IB, Saturn IB-A. Propellants: Lox/LH2 Thrust(vac): 105,352 kgf. Thrust(vac): 1,033.10 kN. Isp: 421 sec. Isp (sea level): 200 sec. Burn time: 475 sec. Mass Engine: 1,438 kg. Diameter: 2.0 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 28.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 73.18. Country: USA. Status: Out of Production. First Flight: 1966. Last Flight: 1975. Flown: 87. References: 225 .

Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Specific impulse and thrust is for final flight version; J-2 had a specific impulse of 418 sec/thrust of 90,700 kgf/mix ratio of 5.00 on LV's SA-201 through 203, and 419 sec/thrust of 102,040 kgf on SA-204 through 207 and SA-501 to 503. Sea level versions with reduced expansion ratio proposed for Saturn II first stage use. Upgraded toroidal aerospike versions (J-2T-200K and J-2T-250K) studies for upgrades to Saturn upper stages. Modestly improved J-2S was tested and provides basis for X-33 linear aerospike engine thirty years later. Proposed for use in Nova A-2; Saturn IVB; Nova NASA-3; Nova B-2; Saturn II; Jarvis-2; Saturn MS-II-1; Saturn S-II-8; Saturn S-IVC; Nova 60-8-3; Saturn S-II-C3; Saturn S-II-4; Saturn S-II. Saturn V S-ll & S-IVB Stage Engines, Saturn IB S-IVB. Upper Stage Engine. Gas generator, pump-fed.

J-2J-2

Credit: Boeing / Rocketdyne. 8,624 bytes. 163 x 239 pixels.

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Last update 12 March 2001.
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