S2.721

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Engine Model: S2.721V. Other Designations: S2.721V. Designer: Isayev. Developed in: 1956-. Application: KSR. Propellants: Nitric acid/Amine. Thrust(vac): 11.800 kN (2,653 lbf). Thrust(sl): 6.860 kN (1,542 lbf). Chambers: 2. Country: Russia. Status: Developed 1956-. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.