Final answer:
The thrust of the rocket burning fuel at a rate of 150 kg/s and exhausting gas at a relative speed of 5 km/s is 0.75 MN.
Step-by-step explanation:
The thrust F of a rocket can be calculated using the formula F = Δm/Δt × v, where Δm/Δt is the rate of change of mass (mass flow rate) of the fuel, and v is the exhaust velocity relative to the rocket. In the given problem, the fuel is being exhausted at a mass flow rate of 150 kg/s with an exhaust velocity of 5 km/s (which is equivalent to 5000 m/s).
Thus, the thrust F can be calculated as follows:
F = (150 kg/s) × (5000 m/s) = 750,000 N.
Since 1 meganewton (MN) is equal to 1,000,000 newtons (N), the thrust in units of MN is:
F = 750,000 N / 1,000,000 (N/MN) = 0.75 MN.