The F-1 engine used on the first stage of the Saturn V rocket operated on RP1/LO

Question

The F-1 engine used on the first stage of the Saturn V rocket operated on RP1/LOX at a specific impulse of 260 sec and developed a thrust of 6.9 Times 10^6 N at liftoff. Assuming the stagnation temperature, ratio of specific heats and mean molecular weight given in "1" apply, plot the throat area that would have been required as a function of stagnation pressure for it to operate properly. If it operated at an initial supportance of 1.2 g's and there were 5 of these engines, what must the initial mass of the vehicle have been? If the vehicle mass dropped to 1/3 of its initial value before these engines were throttled, what maximum G-load would the crew have felt?

Explanation / Answer

Impulse = thrust /mass

Therefore

Mass= impulse *thrust

M= 260*6.9*10power of6

M=1790 * 10 power of6

G= 600/260

G=2.3*10 power of 6 m/sec

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