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R-101B.36000-0
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Designer: Isayev. Developed in: July 1950. Application: R-101B/R-108 SAM. Propellants: Nitric acid/Amine. Thrust(sl): 83.300 kN (18,727 lbf). Chambers: 1. Country: Russia. Status: Developed 1950-51. Single chamber engine designed for use in the R-101B and R-108 (derivative of German Wasserfall). Never flown in this application but developed for use in the V-300 SAM and R-11 SSM.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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