Interactive simulation
Escape velocity, delta-v, fuel burn, and combustion.
Run browser-side educational calculators for orbital energy, Tsiolkovsky delta-v, approximate propellant burn, and propellant chemistry.
Engine visual
Rocket engine test image
This page includes the generated engine-test image for propulsion, combustion, and simulation context.
Rocket Equation
Fuel Burn
Chemical Combustion
Methalox: CH4 + 2 O2 -> CO2 + 2 H2O. Hydrolox: 2 H2 + O2 -> 2 H2O. Kerolox approximation: C12H26 + 18.5 O2 -> 12 CO2 + 13 H2O. Real engines also track mixture ratio, dissociation, chamber pressure, cooling, and nozzle expansion.
Rocket Flight Lab
Launch from pad, follow trajectory, view MECO, separation, SECO, orbit, altitude, and booster landing.
LOX Engine Lab
Interactive cutaway engine simulation with combustion animation, cooling flow, readouts, and engineer controls.
Propulsion 3D Lab
Three-dimensional engine learning model covering thrust, nozzles, injector/chamber behavior, cooling, cycles, solids, controls, plumes, and testing.
Solid Fuels
HTPB/AP/metalized propellants offer simple storage and high thrust, but once ignited they are difficult to throttle or stop.
Storable Liquids
UDMH/N2O4 and MMH/MON are useful for long-duration storage and restart but require strict toxic handling controls.
Cryogenic Liquids
LOX/LH2 gives high specific impulse; LOX/methane and LOX/kerosene offer booster-friendly density and thrust tradeoffs.