If you look at the derivation for thrust from a rocket, theend result is:

Ma=vdM/dt

Where M is the mass of the rocket, a is the acc of the rocket,and v is the speed of the exhaust gas relative to the rocket.

So, \(\displaystyle{v}={\frac{{{M}{a}}}{{{\frac{{{d}{M}}}{{{\left.{d}{t}\right.}}}}}}}\) this is a little weird, but you are given that at that instant, dM/dt is M/160 per second so \(\displaystyle{v}={M}\cdot{16}\) m/s

\(\displaystyle{\frac{{\frac{{M}}{{160}}}}{{{1}\ {\sec}}}}={2560}\ \frac{{m}}{{s}}\)

Ma=vdM/dt

Where M is the mass of the rocket, a is the acc of the rocket,and v is the speed of the exhaust gas relative to the rocket.

So, \(\displaystyle{v}={\frac{{{M}{a}}}{{{\frac{{{d}{M}}}{{{\left.{d}{t}\right.}}}}}}}\) this is a little weird, but you are given that at that instant, dM/dt is M/160 per second so \(\displaystyle{v}={M}\cdot{16}\) m/s

\(\displaystyle{\frac{{\frac{{M}}{{160}}}}{{{1}\ {\sec}}}}={2560}\ \frac{{m}}{{s}}\)