Rocket Equation Calculator

Δv = v_e · ln(m₀ / m_f)

Presets

Exhaust Velocity (m/s) or use Isp below Specific Impulse (s) v_e = Isp × g₀ Wet Mass m₀ (kg) total mass with propellant Dry Mass m_f (kg) mass after burnout

Delta-v (m/s)

About the Tsiolkovsky Rocket Equation

Published by Konstantin Tsiolkovsky in 1903, this fundamental equation of astronautics relates the delta-v (total change in velocity) a rocket can achieve to its exhaust velocity and mass ratio. It shows that increasing propellant fraction or exhaust velocity yields higher delta-v, and explains why multi-stage rockets are necessary for orbital flight.