SymPy-based lab for quasi-1D nozzle gasdynamics: symbolic isentropic relations, numerical profiles, and engineering plots.
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+.
Conceptual design and analysis of a liquid-propellant rocket engine for orbital launch vehicles. Presents key specs (chamber pressure, nozzle expansion, thrust-to-weight), propellant/material selection (LOX/RP-1 & LOX/LH₂), cycle considerations, and computational workflows for engine sizing, sweeps and trade-off studies.
Transient startup of a liquid-fueled rocket nozzle using a 2D axisymmetric compressible-flow. 1.1 MN of thrust
Physics-informed propellant combustion and nozzle performance simulator with an optional TensorFlow surrogate for specific impulse. Computes exhaust velocity, thrust, Isp, temp/pressure profiles, wall heating, and stability spectrum for multiple propellants. CLI, plots, and cached models in models
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