Question

A rocket burns fuel at a rate of 294 KG/S and exhaust gas at a relative speed of 6KM/S find the thrust of the rocket answer in units of MN

Answer 1

The thrust of the rocket can be found from the formula:

$$T=v\dfrac{dm}{dt},$$

here, $T$ is the thrust of the rocket, $v=6\ \dfrac{km}{s}$ is the relative speed of the exhaust gas, $\dfrac{dm}{dt}=294\ \dfrac{kg}{s}$ is the mass flow rate (or the rate of the burn fuel).

Then, we get:

$$T=6\ \dfrac{km}{s}\cdot \dfrac{1000\ m}{1\ km}\cdot294\ \dfrac{kg}{s}=1.764\cdot10^6\ N=1.764\ MN.$$

Answer:

$T=1.764\cdot10^6\ N=1.764\ MN.$