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

Open-source Python toolkit for thermodynamic modelling and performance analysis of Rotating Detonation Rocket Engines (RDREs)

Rocket staging optimizer CLI — find optimal engine configurations and propellant splits for multi-stage rockets using Tsiolkovsky's equation

A CLI tool to calculate rocket propellant chemical energy, TNT equivalent mass, and blast yield using conversion efficiencies. Inspired by the New Glenn incident (May 2026).

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.

SymPy-based lab for quasi-1D nozzle gasdynamics: symbolic isentropic relations, numerical profiles, and engineering plots.

Collection of my academic and technical projects in Aerospace Engineering, as well as Digital Twin modeling and other useful certificates.

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+.

CFD, thermal, and structural investigation of a high-enthalpy hydrogen propulsion system using ANSYS Fluent, ANSYS Mechanical, and MATLAB.

🚀 Estimate ideal rocket nozzle performance with this minimal Python tool, calculating key metrics like thrust coefficient and specific impulse effortlessly.