even with just the auxiliary chamber alone running at 660lb thrust that is around 655lbs of fuel per minute. IF these numbers are correct the auxiliary chamber alone used fuel at a faster rate than a B-29 climbing out with a heavy load.
They can't be correct, the specific impulse of this type of hypergolic bipropellant is around 180-240 seconds. So 660lbs fuel would provide 660 lbs thrust for 180-240 seconds. About 3.0 to 2.5lbs per second or 150lbs per minute. It's still poor, 660lbs is 300kg would be about 300L of fuel. Nevertheless the rocket compensates by being smaller lighter and not having an intake system adding both drag, weight and taking up space that could be used for propellant. A WW2 jet would be doing well to produce as much thrust at 10,000m.
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