Project 01 — Interactive Tool

Rocket Equation
Calculator

Compute delta-v from wet mass, dry mass, and specific impulse. Visualize how mass fractions drive propellant requirements — the same constraint every propulsion engineer works against.

Δv = ve × ln( m0 / mf )
Δvdelta-v (m/s)
veexhaust velocity
m0wet mass
mfdry mass
// inputs
kg
kg
s
// vehicle presets
// output
— m/s
 
mass ratio
—
propellant frac.
—
exhaust vel.
—
propellant mass
—
mass breakdown —
propellant
dry mass
Δv vs. mission requirements
LEO
9,400 m/s
GTO
12,000 m/s
Trans-lunar
13,500 m/s
Mars transit
16,000 m/s
Multi-stage estimate

For a 2-stage vehicle with equal mass ratios, total Δv ≈ 2× single stage.

— m/s (2-stage est.)