1% -------------------------------------------------------------------------
2% EXAMPLE: SHOCK_POLAR
3%
4% Compute shock polar plots at standard conditions, a set of 51 species
5% considered, and a set of initial shock front Mach numbers = [2, 3, 5, 14]
6%
7% Air_ions == {'eminus', 'Ar', 'Arplus', 'C', 'Cplus', 'Cminus', ...
8% 'CN', 'CNplus', 'CNminus', 'CNN', 'CO', 'COplus', ...
9% 'CO2', 'CO2plus', 'C2', 'C2plus', 'C2minus', 'CCN', ...
10% 'CNC', 'OCCN', 'C2N2', 'C2O', 'C3', 'C3O2', 'N', ...
11% 'Nplus', 'Nminus', 'NCO', 'NO', 'NOplus', 'NO2', ...
12% 'NO2minus', 'NO3', 'NO3minus', 'N2', 'N2plus', ...
13% 'N2minus', 'NCN', 'N2O', 'N2Oplus', 'N2O3', 'N2O4', ...
14% 'N2O5', 'N3', 'O', 'Oplus', 'Ominus', 'O2', 'O2plus', ...
15% 'O2minus', 'O3'}
16%
17% See wiki or list_species() for more predefined sets of species
18%
19% @author: Alberto Cuadra Lara
20% PhD Candidate - Group Fluid Mechanics
21% Universidad Carlos III de Madrid
22%
23% Last update Jan 10 2023
24% -------------------------------------------------------------------------
25
26%% INITIALIZE
27self = App('Air_ions');
28%% INITIAL CONDITIONS
29self = set_prop(self, 'TR', 300, 'pR', 1 * 1.01325);
30self.PD.S_Oxidizer = {'N2', 'O2', 'Ar', 'CO2'};
31self.PD.N_Oxidizer = [78.084, 20.9476, 0.9365, 0.0319] ./ 20.9476;
32%% ADDITIONAL INPUTS (DEPENDS OF THE PROBLEM SELECTED)
33self = set_prop(self, 'M1', [2, 3, 5, 14]);
34%% SOLVE PROBLEM
35self = solve_problem(self, 'SHOCK_POLAR');
36%% DISPLAY RESULTS (PLOTS)
37post_results(self);