1% -------------------------------------------------------------------------
2% EXAMPLE: ROCKET Propellants considering an Infinite-Area-Chamber (IAC)
3%
4% Compute rocket propellant performance considering an Infinite-Area-Chamber
5% for lean to rich LH2-LOX mixtures at 101.325 bar, a set of 11 species
6% considered, a set of equivalence ratios phi contained in (2, 5) [-], and
7% an exit area ratio A_exit/A_throat = 3
8%
9% HYDROGEN_L == {'H','H2O','OH','H2','O','O3','O2','HO2','H2O2',...
10% 'H2bLb','O2bLb'}
11%
12% See wiki or list_species() 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 Jul 30 2022
19% -------------------------------------------------------------------------
20
21%% INITIALIZE
22self = App('HYDROGEN_L');
23%% INITIAL CONDITIONS
24self = set_prop(self, 'TR', 90, 'pR', 100 * 1.01325, 'phi', 1:0.05:5);
25self.PD.S_Fuel = {'H2bLb'};
26self.PD.S_Oxidizer = {'O2bLb'};
27self.PD.FLAG_IAC = true;
28%% ADDITIONAL INPUTS (DEPENDS OF THE PROBLEM SELECTED)
29self = set_prop(self, 'Aratio', 3);
30%% SOLVE PROBLEM
31self = solve_problem(self, 'ROCKET');
32%% DISPLAY RESULTS (PLOTS)
33post_results(self);