Status: Design concept 1996-. Date: 1996-. Thrust: 820.00 kN (184,340 lbf). Unfuelled mass: 770 kg (1,690 lb). Specific impulse: 344 s.
Engine: 770 kg (1,690 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 108.59. Oxidizer to Fuel Ratio: 2.6.