LRE Estimator

Preliminary design for a liquid rocket engine. Fill each step and see results update live. Calculations follow felipebogaertsm/lre-scripts, adapted from the Rocketlab/China Lake design paper.

Inputs are saved locally and restored on next visit.

00Propellant pair (optional)

Pick a common combo to lock in typical Isp, O/F, Tc, γ, propellant molar mass, fuel density, and oxidizer. Values from Sutton (Pc ≈ 6.9 MPa, optimum sea-level expansion). Choose Custom to enter your own.

Propellant combination

01Mass flow rates

Set engine thrust, specific impulse, and oxidizer-to-fuel ratio.

Awaiting input

Thrust (N)

Specific impulse (s)

O/F ratio