A rocket of mass $1000 k g$ is exhaust gases at a rate of $4 k g / s$ with a velocity $3000 m / s$ . The thrust developed on the rocket is

12000 N

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120 N

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800 N

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200 N

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Solution

The correct option is A $12000 N$
$m = 1000 k g$

$\frac{Δ m}{Δ t} = 4 k g / s, v = 3000 m / s$

Thrust on the rocket

$F = - v \frac{Δ M}{Δ t}$

$= - 3000 \times 4$

$= - 12000 N$

(Negative sign indicates that thrust applied in a direction opposite to the direction of escaping gas)

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