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.

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