Rocket Equation Calculator (Tsiolkovsky Delta-V)

Your details

Choose which quantity to calculate. The remaining inputs become your knowns.
Select a common propellant combination to auto-fill Isp, or choose Custom to enter your own.
Total mass at ignition: payload + structure + full propellant load.
kg
Mass after all propellant is expended: payload + structural mass only.
kg
Delta-vTypical high-performance rocket
10,161.3

Total velocity change the rocket can deliver

Delta-v (km/s)10.161
Effective exhaust velocity (ve)4,413
Mass ratio (R = m0 / mf)10
Propellant mass consumed90,000
Propellant mass fraction90%
90% fraction
Low fraction<60%Moderate60%-80%High (feasible)80%-93%Impractical (>93%)93%+

This rocket can achieve 10161 m/s of delta-v.

  • Your mass ratio is 10.00, meaning the vehicle starts 10.00x heavier than it ends up after burnout.
  • A propellant fraction of 90.0% is within the range of real-world rocket designs.
  • This delta-v budget is sufficient for: Low Earth orbit (LEO).
  • To reach Geostationary transfer orbit (GTO) you would need approximately 839 m/s more delta-v.

Next stepRemember this is the ideal rocket equation: gravity losses (~1,500 m/s for ascent) and atmospheric drag add to the delta-v you actually need for launch. For a two-stage rocket, apply the equation to each stage separately and sum the results.

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