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Engine Model: Scramjet. Propellants: Air/Slush LH2. Thrust(vac): 1,372.900 kN (308,640 lbf). Thrust(sl): 1,372.900 kN (308,640 lbf). Isp: 1,550 sec. Burn time: 886 sec. Diameter: 16.00 m (52.00 ft). Chambers: 1. Country: USA. Status: Development ended 1992.

Thrust is maximum sea level thrust; specific impulse is average during ascent.

Scramjet used on Rocket Stages
  • Used on stage: X-30. on launch vehicle: X-30.
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© Mark Wade, 1997 - 2008 except where otherwise noted.