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.