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S5.3M
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Other Designations: S5.3M. Designer: Isayev. Developed in: 1959-60, 1958-60. Application: R-9 (SS-8) missile stage 1. Propellants: Nitric acid/Amine. Thrust(vac): 396.700 kN (89,182 lbf). Isp (sea level): 241 sec. Mass Engine: 433 kg (954 lb). Chambers: 4. Chamber Pressure: 66.00 bar. Area Ratio: 9.55. Oxidizer to Fuel Ratio: 3.60. Thrust to Weight Ratio: 93.42. Country: Russia. Status: Out of Production. Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level.
Bibliography and Further Reading - Sergienko, A; Chervakov, V, Fifth Symposium Propulsion, "Russian Rocket Engines Design", Paper 5.3, Paris, May 1996 via Dietrich Haeseler.
- Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
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