Engine Model: RD-169. Manufacturer Name: RD-169. Designer: Glushko. Application: Riksha-0 stage 1. Propellants: Lox/LCH4. Thrust(vac): 167.000 kN (37,543 lbf). Isp: 351 sec. Isp (sea level): 309 sec. Mass Engine: 215 kg (473 lb). Diameter: 0.50 m (1.64 ft). Length: 1.70 m (5.50 ft). Chambers: 1. Chamber Pressure: 147.00 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 79.06. Country: Russia. Status: Design concept 1990's. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. Status 1996 was project, development estimated for four years. Nozzle expansion ratio is 150/0.51=294.
Bibliography:- Klepikov, Katorgin, Chvanov, IAF-Congress Turin, 1997, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-97-S.1.03 via Dietrich Haeseler.