May 292010

From 1962… 6,000,000 pounds thrust, LOX/RP-1 propellants, 2000 psia chamber pressure, expansion ratio 14:1, Isp 283 sec at sea level, 304 sec vacuum. Sized for eas of transportation and manufacturing… which means it’s the small engine in the design study. More to come.


Note: the drawing came to me in B&W, like this:


But that’s boring, so I blueprintified it. Now it’s better.

 Posted by at 1:55 pm
  • sferrin

    always wondered about that one when I’d see it mentioned in the Nova lineup.

  • Pat Flannery

    You can see a lot of F-1 design extrapolation in the overall engine layout.
    Considering all the trouble they had getting the F-1 and SSME to work properly, combining the two and scaling up the result to even larger size should have really kept them busy for a few years.

  • Jim

    should have really kept them busy for a few years.

    Shame it didn’t.


  • George Allegrezza

    L-9H maybe? Any numbers bigger than 9?

  • admin

    > Any numbers bigger than 9?

    Well, there’s the 30,000 K engine, with a diameter of 900 inches… but surely that must be *boring* so I won’t bother y’all with it…

  • George Allegrezza

    Somewhat pedestrian, but please expound . . . . 🙂

    Aerojet showed a 24M system at the 1964 Large Liquid Rocket Conference, but it had 12 or 24 thrust chambers in a common E-D nozzle so I don’t know if that counts as a single “engine”.

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