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Merge pull request #463 from AlbertoCuadra/develop
Add: include Finite-Area-Chamber model (rockets)
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| Original file line number | Diff line number | Diff line change |
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| @@ -0,0 +1,33 @@ | ||
| % ------------------------------------------------------------------------- | ||
| % EXAMPLE: ROCKET Propellants considering an Infinite-Area-Chamber (IAC) | ||
| % | ||
| % Compute adiabatic temperature and equilibrium composition at constant | ||
| % pressure (e.g., 1.01325 bar) for lean to rich LH2-LOX mixtures at | ||
| % standard conditions, a set of 24 species considered and a set of | ||
| % equivalence ratios phi contained in (2, 5) [-] | ||
| % | ||
| % HYDROGEN_L == {'H','H2O','OH','H2','O','O3','O2','HO2','H2O2',... | ||
| % 'H2bLb','O2bLb'} | ||
| % | ||
| % See wiki or ListSpecies() for more predefined sets of species | ||
| % | ||
| % @author: Alberto Cuadra Lara | ||
| % PhD Candidate - Group Fluid Mechanics | ||
| % Universidad Carlos III de Madrid | ||
| % | ||
| % Last update April 12 2022 | ||
| % ------------------------------------------------------------------------- | ||
|
|
||
| %% INITIALIZE | ||
| self = App('HYDROGEN_L'); | ||
| %% INITIAL CONDITIONS | ||
| self = set_prop(self, 'TR', 90, 'pR', 100 * 1.01325, 'phi', 2); | ||
| self.PD.S_Fuel = {'H2bLb'}; | ||
| self.PD.S_Oxidizer = {'O2bLb'}; | ||
| self.PD.FLAG_IAC = false; | ||
| %% ADDITIONAL INPUTS (DEPENDS OF THE PROBLEM SELECTED) | ||
| self = set_prop(self, 'Aratio_c', 2); | ||
| %% SOLVE PROBLEM | ||
| self = SolveProblem(self, 'ROCKET'); | ||
| %% DISPLAY RESULTS (PLOTS) | ||
| postResults(self); |
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| Original file line number | Diff line number | Diff line change |
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| @@ -0,0 +1,80 @@ | ||
| function [mix2_inj, mix2_c, mix3] = compute_chamber_FAC(self, mix1, varargin) | ||
| % Compute chemical equilibria at the injector, outlet of the chamber, | ||
| % using the Finite-Area-Chamber (FAC) model | ||
| % | ||
| % This method is based on Gordon, S., & McBride, B. J. (1994). NASA reference publication, 1311. | ||
| % | ||
| % Args: | ||
| % self (struct): Data of the mixture, conditions, and databases | ||
| % mix1 (struct): Properties of the initial mixture | ||
| % mix2_inj (struct): Properties of the mixture at the injector of the chamber (previous calculation) | ||
| % mix2_c (struct): Properties of the mixture at the outlet of the chamber (previous calculation) | ||
| % | ||
| % Returns: | ||
| % mix2_inj (struct): Properties of the mixture at the injector of the chamber | ||
| % mix2_c (struct): Properties of the mixture at the outlet of the chamber | ||
| % mix3 (struct): Properties of the mixture at the throat | ||
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| % Abbreviations | ||
| TN = self.TN; | ||
| % Unpack | ||
| if nargin > 3, mix2_inj = get_struct(varargin{1}); else, mix2_inj = []; end | ||
| if nargin > 4, mix2_c = get_struct(varargin{2}); else, mix2_c = []; end | ||
| if nargin > 5, mix3 = get_struct(varargin{3}); else, mix3 = []; end | ||
| % Definitions | ||
| Aratio_chamber = self.PD.Aratio_c.value; | ||
| % Obtain mixture compostion and properties at the injector of the chamber (equivalent to the outlet of the chamber using IAC model) | ||
| mix2_inj = compute_chamber_IAC(self, mix1, mix2_inj); | ||
| % Get results | ||
| pressure_inj = pressure(mix2_inj); % [bar] | ||
| % Compute guess pressure_inf | ||
| pressure_inf = compute_initial_guess_pressure(pressure_inj, Aratio_chamber); % [bar] | ||
| % Initialization | ||
| STOP = 1; it = 0; | ||
| mix2_inf = []; | ||
| pressure_inj = pressure_inj * 1e5; % [Pa] | ||
| % Loop | ||
| while STOP > TN.tol_rocket && it < TN.it_rocket | ||
| it = it + 1; | ||
| % Get guess | ||
| mix1.p = pressure_inf; % [bar] | ||
| % Obtain mixture compostions | ||
| [mix2_inf, mix3, mix2_c] = compute_IAC_model(self, mix1, mix2_inf, mix3, mix2_c, Aratio_chamber); | ||
| % Get results | ||
| pressure_c = pressure(mix2_c) * 1e5; % [Pa] | ||
| density_c = density(mix2_c); % [kg/m3] | ||
| velocity_c = velocity_relative(mix2_c); % [m/s] | ||
| % Compute pressuse_inj_a | ||
| pressure_inj_a = (pressure_c + density_c * velocity_c^2); % [Pa] | ||
| % Check convergence | ||
| STOP = abs(pressure_inj - pressure_inj_a) / pressure_inj; | ||
| % Update guess | ||
| pressure_inf = pressure_inf * pressure_inj / pressure_inj_a; % [bar] | ||
| mix2_inf.p = pressure_inf; | ||
| end | ||
| % Assign values | ||
| mix2_c.Aratio = Aratio_chamber; % [-] | ||
| end | ||
|
|
||
| % SUB-PASS FUNCTIONS | ||
| function str = get_struct(var) | ||
| try | ||
| str = var{1,1}; | ||
| catch | ||
| str = var; | ||
| end | ||
| end | ||
|
|
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| function pressure_inf = compute_initial_guess_pressure(pressure_inj, Aratio_chamber) | ||
| % Compute initial guess of the pressure assuming an Infinite-Area-Chamber | ||
| % (IAC) for the Finite-Area-Chamber model (FAC) | ||
| pressure_inf = pressure_inj * (1.0257 - 1.2318 * Aratio_chamber) / (1 - 1.26505 * Aratio_chamber); | ||
| end | ||
|
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| function [mix2_inf, mix3, mix2_c] = compute_IAC_model(self, mix1, mix2_inf, mix3, mix2_c, Aratio) | ||
| % Solve IAC model | ||
| self.PD.FLAG_IAC = true; | ||
| self.PD.FLAG_SUBSONIC = true; | ||
| mix2_inj = []; | ||
| [~, mix2_inf, mix3, mix2_c] = solve_model_rocket(self, mix1, mix2_inj, mix2_inf, mix3, mix2_c, Aratio); | ||
| end |
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