Combustion Toolbox: A MATLAB-GUI based open-source tool for solving gaseous combustion problems

## Features - The code stems from the minimization of the free energy of the system by using Lagrange multipliers combined with a Newton-Raphson method, upon condition that initial gas properties are defined by two functions of states (e.g., temperature and pressure) - When temperature is not externally imposed, the code retrieves a routine based on the Steffensen-Aitken root-finding algorithm to find the equilibrium temperature - Solve processes that involve strong changes in the dynamic pressure, such as detonations and shock waves in the steady state - Find the equilibrium conditions of the different phenomena undergoing behind the shock: molecular vibrational excitation up to dissociation, and electronic excitation up to ionization, thereby providing the `properties of the gas in plasma state` within the temperature range given by the NASA's 9-coefficient polynomial fits. - The corresponding thermodynamic properties of the species are modelled with `NASA's 9-coefficient polynomial fits`, which ranges `up to 20000 K`, and the ideal gas equation of state - Results are in `excellent agreement with NASA's Chemical Equilibrium with Applications (CEA) program`, CANTERA and Caltech's Shock and Detonation Toolbox - All the routines and computations are encapsulated in a more comprehensive and user-friendly GUI - The code is in it's transition to Python - Display predefined plots (e.g., molar fraction vs equilence ratio) - Export results in a spreadsheet (requires Excel) - Export results as a .mat format * `Chemical equilibrium problems` - TP: Equilibrium composition at defined temperature and pressure - HP: Adiabatic temperature and composition at constant pressure - SP: Isentropic compression/expansion to a specified pressure - TV: Equilibrium composition at defined temperature and constant volume - EV: Adiabatic temperature and composition at constant volume - SV: Isentropic compression/expansion to a specified volume * `Shock calculations:` - Pre-shock and post shock states - Equilibrium or frozen composition - Incident or reflected shocks - Chapman-Jouguet detonations and overdriven detonations - Hugoniot curves Ideal jump conditions for a given adiabatic index and pre-shock Mach number * `Rocket propellant performance assuming:` - Infinite-Area-Chamber model (IAC) - Finite-Area-Chamber model (FAC) - under development - * All the routines and computations are encapsulated in a more comprehensive and `user-friendly GUI`. * The code `is in it's transition to Python`. * Export results in a spreadsheet * Export results as a .mat format * `Display predefined plots` (e.g., molar fraction vs equilence ratio) This project is also part of the PhD of [Alberto Cuadra-Lara](https://www.acuadralara.com/).