Discussion
A rocket exhausts \( 200 \ \mathrm{kg/s} \) at \( 3000 \ \mathrm{m/s} \). Ignoring pressure terms, its thrust is
Answer: D
Thrust is mass flow times exhaust velocity, \( 200 \times 3000 = 600\,000 \) newtons. There is no flight speed term because the rocket takes in nothing, which is precisely why its thrust is independent of speed and altitude alike.
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