Rocket Nozzle Performance

Compute equilibrium combustion products, characteristic velocity and specific impulse for a propellant combination with Cantera. The quasi-1-D nozzle expansion runs with frozen, shifting-equilibrium or finite-rate chemistry, so the spread between them is visible across a map of area or pressure ratios.
Estimated minimum cost: $—

Examples

Thermochemistry

The gas-phase species and their thermodynamic data: a bundled Cantera data file, a Cantera YAML, or a single-file Chemkin mechanism with inline thermodynamic data. Reactions are only used by the finite-rate expansion. Up to 1000 species.

Extra species thermo (optional)

A Cantera YAML species list, for example NASA-7 fits for a custom propellant. Species are added to the gas phase; one with the same name replaces the mechanism's entry.

or drop a file here

Propellants

Fuel and oxidizer streams and their mixture ratio. Each stream's enthalpy comes from the mechanism at its temperature unless you assign one.

Fuel
Oxidizer

Chamber and expansion

Chamber conditions, back pressure, the expansion chemistry, and the exit points of the performance map (up to 200 area and pressure ratios in total).

Nozzle contour and efficiencies

The area law along the axis for the T, p and composition profiles and the finite-rate expansion: two straight cones, or your own stations. Efficiencies scale the delivered c* and Isp; the ideal values are reported alongside them.