Engine Model: R-101B.36000-0. 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.