An Open-Source Framework for Electric Propulsion System Analysis and Optimization in UAV Design
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Updated
Jun 21, 2026 - Python
An Open-Source Framework for Electric Propulsion System Analysis and Optimization in UAV Design
Open source, 0-dimensional, object-oriented airbreathing engine modelling package for preliminary analysis and design of airbreathing engines, divulgation and educational purposes.
The ultimate electric propulsion modeling and optimization module.
A comprehensive solution for designing and optimizing student-built liquid rocket engines.
Hybrid Rocket Propulsion Model [Python]
An object-oriented Python 3 GUI and API for single- and multi-element parametric airfoil design, analysis, and optimization
A comprehensive repository for designing, simulating, and analyzing thermal protection systems and heat shielding for spacecraft and rockets.
CFD simulation of an aeroacoustic oscillating resonator using the Lattice Boltzmann Method (D2Q9). Visualise thrust generation via dynamic boundary layer and asymmetric fluid resistance accumulation.
Simulation of a rocket undergoing pogo oscillation effect
🚀 Professional rocket engine simulation & 6-DOF flight analysis platform. NASA CEA validated thermochemistry, real-time performance calculations, Monte Carlo dispersion analysis.
This is a full cycle code for the PT6A-114 engine. The code was developed for AERO 417 Aerospace Propulsion. In this repository, you will find the code for the engine, as well as the basic engine specs and code results
Gridded ion thruster global model
A python GUI app that helps a user to compare various ion engines by plotting a 'Total spacecraft mass by thrust' graph and generating a log that includes various calculated parameters.
Source code of a university project. It is a liquid rocket engine designer that calculates a multitude of geometrical and thermodynamical variables with given performance constraints.
Advanced rocket trajectory simulation and design optimization system with parallel optimization algorithms and supersonic flight regime detection. Optimizes diameter, nose cone length, and body length to achieve target apogee within tolerance.
Simple blade element propeller momentum theory analysis to analyse speeds of aircraft in forward flight.
Set of Python classes that allows computations for contours of supersonic nozzles
GitHub repository for the Unified Ducted fan Code (UDC) and Ducted Fan Optimisation Frameworks
Tools and theory for designing and understanding rocket motors, gas turbines and engines
Hybrid and liquid rocket engine solvers, design tools, and codes for analysis.
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