Rocket Propulsion Calculator

Calculate rocket delta-V, exhaust velocity, and burn time using the Tsiolkovsky rocket equation.

Specific Impulse (Isp)

Initial Mass (m₀)

Final Mass (mf)

Thrust Force

Tab to move between fields

Delta-V (ΔV)

3,542.08 m/s

Exhaust Velocity2,942 m/s

Mass Ratio (m₀/mf)3.33

Burn Time205.94 s

Mass Flow Rate33.99 kg/s

How to Use This Calculator

Enter propellant specific impulse (Isp in seconds) from the engine's performance specification.
Set initial (wet) mass (kg) and final (dry) mass (kg) after propellant burnout.
Enter thrust force (N) and propellant mass flow rate (kg/s) if known.
Review delta-V (m/s), exhaust velocity (m/s), mass ratio, burn time, and mass flow rate.
Use the Tsiolkovsky rocket equation output to verify the mission delta-V budget is achievable.

How the result changes with Specific Impulse (Isp)

Specific Impulse (Isp): Measure of engine efficiency in seconds. Higher values mean more efficient propulsion.
Initial Mass (m₀): Total mass of the vehicle including propellant before the burn.
Final Mass (mf): Mass of the vehicle after all propellant has been expended.
Thrust Force: Total thrust produced by the engine, used to calculate burn time.

Identify Input Parameters
4 parameters
Specific Impulse (Isp) = 300, Initial Mass (m₀) = 10000, Final Mass (mf) = 3000, Thrust Force = 100000 = 4 input(s) provided
Calculate Delta-V
Delta-V
3542.08 = 3542.08
Calculate Exhaust Velocity
Exhaust Velocity
2942 = 2942
Calculate Mass Ratio
Mass Ratio
3.333 = 3.333