Delta-V Calculator (Tsiolkovsky Rocket Equation)

Your details

Choose which variable to solve for. The remaining three fields are your inputs.
Select a propellant to auto-fill specific impulse, or choose Custom.
Isp in seconds. The exhaust velocity is Isp x 9.80665 m/s. Select a propellant preset above to auto-fill.
s
Total rocket mass including propellant at the start of the burn.
kg
Total rocket mass including propellant at the start of the burn.
kg
Rocket mass after propellant is exhausted (structure + payload).
kg
Rocket mass after propellant is exhausted (structure + payload).
kg
The velocity change required for your mission maneuver.
m/s
Choose display units for delta-V and exhaust velocity outputs.
Delta-VDeep-space capable
7,022.6m/s

Velocity change the rocket can achieve with this propellant load

Delta-V7.023km/s
Exhaust velocity3,049.9m/s
Specific impulse (Isp)311s
Initial (wet) mass100,000kg
Final (dry) mass10,000kg
Propellant mass90,000kg
Propellant fraction90%
Mass ratio (m0/mf)10
Propellant90,000
Dry mass10,000

This rocket can achieve 7.023 km/s of delta-V.

  • This delta-V (7.02 km/s) is in the range needed to reach Earth orbit (~9.4 km/s from the ground) or transfer to the Moon.
  • 90.0% of the initial mass is propellant, leaving 10.0% as dry mass (structure and payload).
  • A mass ratio of 10.00 means you need 10.00 kg of loaded rocket for every 1 kg of dry rocket.
  • With a Kerosene / LOX (RP-1) engine (Isp 311 s), the exhaust velocity is 3050 m/s.

Next stepTo extend your delta-V budget, increase Isp (better engine) or reduce dry mass (lighter structure and payload).

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