Example_ROCKET_FAC.m#

 1% -------------------------------------------------------------------------
 2% EXAMPLE: ROCKET Propellants considering an Finite-Area-Chamber (FAC)
 3%
 4% Compute rocket propellant performance considering an Finite-Area-Chamber
 5% with an area ratio of the combustion chamber A_chamber/A_throat = 2
 6% for lean to rich LH2-LOX mixtures at 101.325 bar, a set of 24 species
 7% considered, a set of equivalence ratios phi contained in (2, 5) [-], and
 8% an exit area ratio A_exit/A_throat = 3 
 9%   
10% HYDROGEN_L == {'H','H2O','OH','H2','O','O3','O2','HO2','H2O2',...
11%                'H2bLb','O2bLb'}
12%   
13% See wiki or list_species() for more predefined sets of species
14%
15% @author: Alberto Cuadra Lara
16%          PhD Candidate - Group Fluid Mechanics
17%          Universidad Carlos III de Madrid
18%                 
19% Last update Jul 30 2022
20% -------------------------------------------------------------------------
21
22%% INITIALIZE
23self = App('HYDROGEN_L');
24%% INITIAL CONDITIONS
25self = set_prop(self, 'TR', 90, 'pR', 100 * 1.01325, 'phi', 1:0.05:5);
26self.PD.S_Fuel     = {'H2bLb'};
27self.PD.S_Oxidizer = {'O2bLb'};
28self.PD.FLAG_IAC = false;
29%% ADDITIONAL INPUTS (DEPENDS OF THE PROBLEM SELECTED)
30self = set_prop(self, 'Aratio_c', 2, 'Aratio', 3);
31%% SOLVE PROBLEM
32self = solve_problem(self, 'ROCKET');
33%% DISPLAY RESULTS (PLOTS)
34post_results(self);