The exit velocity of a rocket nozzle can be calculated using the ideal rocket equation, which describes the relationship between the velocity of a rocket, the effective exhaust velocity, and the natural logarithm of the ratio of the initial mass of the rocket to its final mass. The formula is as follows:
Where:
- is the effective exhaust velocity (m/s)
- is the specific impulse of the rocket engine (seconds)
- is the standard gravity (9.81 m/s²)
- is the initial mass of the rocket (kg)
- is the final mass of the rocket (kg)