Engine Model: Otrag. Designer: Otrag. Developed in: 1975-1987. Application: First and Upper Stages. Propellants: N2O4/Kerosene. Thrust(vac): 27.500 kN (6,182 lbf). Thrust(sl): 25.000 kN (5,620 lbf). Throttled thrust(vac): 11.000 kN (2,472 lbf). Isp: 297 sec. Isp (sea level): 270 sec. Burn time: 150 sec. Diameter: 0.27 m (0.88 ft). Chambers: 1. Country: Germany. Status: Out of production. First Flight: 1977. Last Flight: 1983. Flown: 1,152. Pressure-fed, using cheapest possible propellants. Injection pressure: 40 - 15 bar; Thrust control: 100% - 40 %; Pressurization: Compressed air 66% tank filling in blow-down mode; Injector: Radial like on like; Chamber cooling: Ablative phenolic; Material of injector, valves, bulkheads: AlMg5.
Otrag used on Rocket Stages
Bibliography:- Kayser, Lutz, Personal communication, 2005.,
