Rocket Equation Calculator

Property to Calculate:

Change in velocity (Δ v):

Exhaust velocity (v_e):

Initial mass of the rocket (m₀):

Final mass of the rocket (m_f):

How This Is Calculated

$$ \Delta v = v_e \cdot ln\left( \frac{m_0}{m_f} \right) $$ where:

Δ v = Change in velocity (m/s)

v_e = Exhaust velocity (m/s)

m₀ = Initial mass of the rocket (kg)

m_f = Final mass of the rocket (kg)

Assumptions

The rocket is ideal.
The exhaust velocity remains constant.
The change in mass is only due to propellant being expelled.
There is only a single burn without staging or multile engine firings.

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