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H-1 engine

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z H-1 engine Part of LR79 H-1 Credit: Boeing / Rocketdyne Rocketdyne LOx/Kerosene rocket engine. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. First flight 1961. Surplus Saturn motors adapted for use in Delta launch vehicle. AKA: H-1. Date: 1958. Number: 80 . Thrust: 947.70 kN (213,051 lbf). Unfuelled mass: 635 kg (1,399 lb). Specific impulse: 289 s. Specific impulse sea level: 255 s. Burn time: 150 s. Height: 2.13 m (6.98 ft). Diameter: 0.82 m (2.67 ft). Thrust (sl): 836.200 kN (187,985 lbf). Thrust (sl): 85,275 kgf. Engine: 635 kg (1,399 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 152.196850393701. Oxidizer to Fuel Ratio: 2.23. Coefficient of Thrust vacuum: 1.74073055260789. Coefficient of Thrust sea level: 1.54073055260789. Country: USA. Launch Vehicles: Juno V-A, Juno V-B, Saturn A-1, Saturn C-2, Saturn I. Propellants: Lox/Kerosene. Stages: S-I stage. Agency: Rocketdyne. Bibliography: 225. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

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