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Looking at the Wikipedia page for the J-2 (one engine was used on the Saturn V third stage, and 5 engines on the second stage) it gets about 232Klbs thrust in vacuum, but at sea level, only 109KLbs thrust.

That is a pretty wild performance swing.

Why such a difference? If you compare the Vacuum Merlin's vs the sea level Merlin's performance you get a much smaller swing in performance.

I am guessing it is because there never was a sea level optimized J-2 engine (it was meant as an upper stage engine) so the sea level number may be spurious or only from test stands.

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This, in a nutshell, is the problem that linear aerospike engines are supposed to solve. –  Travis Bear Feb 14 at 5:34

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Designed for high altitude low ambient pressure, I assume. The primary optimization is in the nozzle:

For optimal performance the pressure of the gas at the end of the nozzle should just equal the ambient pressure: if the exhaust's pressure is lower than the ambient pressure, then the vehicle will be slowed by the difference in pressure between the top of the engine and the exit; on the other hand, if the exhaust's pressure is higher, then exhaust pressure that could have been converted into thrust is not converted, and energy is wasted.

To maintain this ideal of equality between the exhaust's exit pressure and the ambient pressure, the diameter of the nozzle would need to increase with altitude, giving the pressure a longer nozzle to act on (and reducing the exit pressure and temperature). This increase is difficult to arrange in a lightweight fashion, although is routinely done with other forms of jet engines. In rocketry a lightweight compromise nozzle is generally used and some reduction in atmospheric performance occurs when used at other than the 'design altitude' or when throttled.

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So you expect a reduction in behavior for a vacuum optimized engine/nozzle, but this is a 50% cut in performance. More than usual. –  geoffc Feb 13 at 19:03

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