RS-27C RS-27A Credit - Boeing / Rocketdyne Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 1,054.200 kN (236,994 lbf). Thrust(sl): 890.100 kN (200,102 lbf). Isp: 302 sec. Isp (sea level): 255 sec. Burn time: 265 sec. Mass Engine: 1,091 kg (2,405 lb). Diameter: 2.44 m (8.00 ft). Length: 3.78 m (12.40 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 12.00. Oxidizer to Fuel Ratio: 2.25. Thrust to Weight Ratio: 98.53. Country: USA. First Flight: 1990. Last Flight: 2006. Flown: 107. RS-27C used on Rocket Stages Used on stage: Delta Thor XLT-C. on launch vehicle: Barbarian MDD. Used on stage: Delta Thor XLT-C. on launch vehicle: Barbarian MDD. Used on stage: Delta Thor XLT-C. on launch vehicle: Delta 7000. Used on stage: Delta Thor XLT-C. on launch vehicle: Delta 7000H.                   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 - 2007 except where otherwise noted.

Encyclopedia Astronautica topic index 0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z Enter your search terms   Web www.astronautix.com Submit search form