Status: Design concept 1990's. Thrust: 1,576.00 kN (354,298 lbf). Unfuelled mass: 2,370 kg (5,220 lb). Specific impulse: 363 s.
Engine: 2,370 kg (5,220 lb). Chamber Pressure: 172.50 bar. Thrust to Weight Ratio: 67.8. Oxidizer to Fuel Ratio: 3.4.