Example_ROCKET.m#

 1% -------------------------------------------------------------------------
 2% EXAMPLE: ROCKET Propellants
 3%
 4% Compute adiabatic temperature and equilibrium composition at constant
 5% pressure (e.g., 1.01325 bar) for lean to rich LH2-LOX mixtures at
 6% standard conditions, a set of 24 species considered and a set of
 7% equivalence ratios phi contained in (2, 8) [-]
 8%   
 9% HYDROGEN_L == {'H','H2O','OH','H2','O','O3','O2','HO2','H2O2',...
10%                'H2bLb','O2bLb'}
11%   
12% See wiki or ListSpecies() for more predefined sets of species
13%
14% @author: Alberto Cuadra Lara
15%          PhD Candidate - Group Fluid Mechanics
16%          Universidad Carlos III de Madrid
17%                 
18% Last update March 24 2022
19% -------------------------------------------------------------------------
20
21%% INITIALIZE
22self = App('HYDROGEN_L');
23%% INITIAL CONDITIONS
24self = set_prop(self, 'TR', 90, 'pR', 1 * 1.01325, 'phi', 2:0.05:8);
25self.PD.S_Fuel     = {'H2bLb'};
26self.PD.S_Oxidizer = {'O2bLb'};
27%% SOLVE PROBLEM
28self = SolveProblem(self, 'ROCKET');
29%% DISPLAY RESULTS (PLOTS)
30postResults(self);