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astronautix.com S2.253 derivative


Other Designations: S2.253 derivative. Designer: Isayev. Application: EKR (experimental winged missile). Used on stages: EKR Stage 1. Used on launch vehicles: EKR. Propellants: Lox/Kerosene Thrust(vac): 10,945 kgf. Thrust(vac): 93.20 kN. Isp: 250 sec. Isp (sea level): 217 sec. Burn time: 127 sec. Chambers: 1. Country: Russia. Status: Design concept 1990's. References: 21 . Comments: Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile).
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Last update 12 March 2001.
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