S2.253 derivative

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S2.253 derivative

Part of S2.253

Isayev LOx/Kerosene rocket engine. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile).

Status: Study 1953. Thrust: 93.20 kN (20,952 lbf). Specific impulse: 250 s. Specific impulse sea level: 217 s. Burn time: 127 s.

Country: Russia. Launch Vehicles: EKR. Propellants: Lox/Kerosene. Stages: EKR Stage 1. Agency: Isayev bureau.

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