Question

A rocket burns fuel at a rate of 249 kg/s and exhats the gas at a relative speed of 2 km/s. Find the thrt of the rocket.

Answer 1

The thrust of the rocket, calculated using the mass flow rate of 249 kg/s and exhaust velocity of 2 km/s, is 498,000 newtons.

Step-by-step explanation:

The subject of this question is physics, particularly dealing with rocket propulsion and the concept of thrust.

Thrust is a force that propels a rocket forward and is calculated by multiplying the rate at which fuel is burned (mass flow rate) by the exhaust velocity relative to the rocket. Thus, the thrust (F) of the rocket can be calculated using the equation F = Δm/Δt ⋅ ve, where Δm/Δt is the rate at which the rocket burns its fuel and ve is the exhaust velocity.

Given that the rocket burns fuel at a rate of 249 kg/s and exhausts the gas at a relative speed of 2 km/s (2000 m/s), the thrust of the rocket can be calculated as:

F = 249 kg/s ⋅ 2000 m/s

F = 498,000 N (newtons)

Answer 2

The thrust of the rocket is calculated by multiplying the mass flow rate of the exhaust by the exhaust velocity, resulting in a thrust of 498000 N.

Step-by-step explanation:

The thrust of the rocket can be calculated using the relationship between the mass flow rate of the exhaust gases and the exhaust velocity. This is described by the formula thrust = mass rate × exhaust velocity. Given that the rocket burns fuel at a rate of 249 kg/s and expels the gas at a relative speed of 2 km/s (which is equivalent to 2000 m/s), the thrust can be found by multiplying these two values together.

To find the rocket's thrust:
Thrust = mass rate × exhaust velocity = 249 kg/s × 2000 m/s = 498000 N (Newtons).