Minimal estimator of ideal (isentropic) rocket nozzle performance: exit state (Me, Pe, Te), CF, Isp, F/At, with Pc–area-ratio sweeps. Pure Python, small tests, CSV output for quick trade studies. Requires Python 3.10+.
python engineering gas-dynamics thrust nozzle rocketry demo-project compressible-flow isentropic aerothermodynamics rocket-propulsion specific-impulse
-
Updated
Nov 13, 2025 - Python