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Visualization improvements #33

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f68d4b6
SUSAN Visualization Model
NawaKhai Jul 11, 2024
bd4a30b
BWB Geometry
NawaKhai Jul 12, 2024
5a9fb48
Propulsion Architecture bug fixing
NawaKhai Jul 12, 2024
17a1a65
Added TestGeometry.m to FAST repo
NawaKhai Jul 12, 2024
df13aae
Added PropArchTest.m
NawaKhai Jul 12, 2024
b3f9b02
Updated PropulsionArchitecture
prmoko Dec 2, 2024
ca186d5
Updated PropulsionArchitecture
prmoko Dec 2, 2024
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102 changes: 102 additions & 0 deletions +VisualizationPkg/+GeometrySpecsPkg/BWB.m
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function [Aircraft] = BWB(Aircraft)

%
% BWB.m
% written by Nawa Khailany, nawakhai@umich.edu
% last updated: 19 may 2024
%
% geometric parameters for a Blended Wing Body aircraft.
%
% inputs : Aircraft - aircraft structure with no geometry components
% outputs: Aircraft - aircraft structure with the geometry components
%

% ----------------------------------------------------------
%% DEFINE THE WING %%
%%%%%%%%%%%%%%%%%%%%%

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% list geometric parameters %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

Wing.AR = 11 ;
Wing.area = 3000 ;
Wing.taper = 0.3;
Wing.sweep = 18 ; %was 1 degree
Wing.dihedral = 0 ;
Wing.xShiftWing = 84 ;
Wing.yShiftWing = 0 ;
Wing.zShiftWing = 10 ;
Wing.symWing = 1 ;

% parameters with characters
Wing.orientation = 'xz' ;
Wing.wingAfoil.airfoilName = '0012' ;
Wing.type = 'liftingSurface';

%% DEFINE THE RIGHT WingTip %%

% parameters with numerical values
WingTipR.AR = 2;
WingTipR.area = 60;
WingTipR.taper = 0.25 ;
WingTipR.sweep = 40 ;
WingTipR.dihedral = 8;
WingTipR.xShiftWing = 118 ;
WingTipR.yShiftWing = 90.5 ;
WingTipR.zShiftWing = 10 ;
WingTipR.symWing = 0 ;

% parameters with characters
WingTipR.orientation = 'xy' ;
WingTipR.wingAfoil.airfoilName = '0004' ;
WingTipR.type = 'liftingSurface';

%% DEFINE THE LEFT WingTip %%

% parameters with numerical values
WingTipL.AR = 2;
WingTipL.area = 60;
WingTipL.taper = 0.25 ;
WingTipL.sweep = 40 ;
WingTipL.dihedral = -8;
WingTipL.xShiftWing = 118 ;
WingTipL.yShiftWing = -90.5 ;
WingTipL.zShiftWing = 10 ;
WingTipL.symWing = 0 ;

% parameters with characters
WingTipL.orientation = 'xy' ;
WingTipL.wingAfoil.airfoilName = '0004' ;
WingTipL.type = 'liftingSurface';

%% DEFINE THE FUSELAGE %%
%%%%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Fuselage.Length = 130;

% parameters with characters
Fuselage.type = 'bluntBody';
Fuselage.Style = fullfile("+VisualizationPkg","+GeometrySpecsPkg","BWBFuselage.dat");

%% REMEMBER THE GEOMETRY PARAMETERS %%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% save as one structure %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

Aircraft.Geometry.Wing = Wing;

Aircraft.Geometry.WingTipR = WingTipR;

Aircraft.Geometry.WingTipL = WingTipL;

Aircraft.Geometry.Fuselage = Fuselage;

end
50 changes: 50 additions & 0 deletions +VisualizationPkg/+GeometrySpecsPkg/BWBFuselage.dat
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x1=14.0
x2=135
TLength=130
SuperEllipseNum=9

supell_1
0.0 0.0 0.0 0.0
2 2 2 2
0.0 0.0 -2
NOTFVIEW
supell_2
2.5 2.5 2.5 2.5
2 2 2 2
2.5 0.0 -2
FVIEW
supell_3
7.5 7.5 7.5 7.5
3 3 2 2
14.0 0.0 0.0
NOTFVIEW
supell_4
10.0 13.0 10.0 13.0
3.7 3.7 2 2
28.0 0.0 0.0
FVIEW
supell_5
10.0 20.0 10.0 20.0
4 4 2 2
44 0.0 0.0
NOTFVIEW
supell_6
10.0 35.0 10.0 35.0
4.2 4.2 2 2
80 0.0 0.0
FVIEW
supell_7
7 35.0 7 35.0
4.2 4.2 2 2
105 0.0 2
NOTFVIEW
supell_8
5.0 23.0 5.0 23.0
4 4 1.9 1.9
120 0.0 3
NOTFVIEW
supell_9
1.5 0.5 1.5 0.5
2 2 2 2
135 0.0 5
NOTFVIEW
158 changes: 158 additions & 0 deletions +VisualizationPkg/+GeometrySpecsPkg/SUSAN.m
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function [Aircraft] = SUSAN(Aircraft)
%
% SUSAN.m
% written by Nawa Khailany, nawakhai@umich.edu
% last updated: 13 may 2024
%
% geometric parameters for a transport-like aircraft.
%
% inputs : Aircraft - aircraft structure with no geometry components
% outputs: Aircraft - aircraft structure with the geometry components
%

% ----------------------------------------------------------

%% DEFINE THE WING %%
%%%%%%%%%%%%%%%%%%%%%

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% list geometric parameters %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Wing.AR = 9.44 ;
Wing.area = 1470 ;
Wing.taper = 0.28;
Wing.sweep = 21 ;
Wing.dihedral = 2 ;
Wing.xShiftWing = 100 ;
Wing.yShiftWing = 0 ;
Wing.zShiftWing = -10 ;
Wing.symWing = 1 ;

% parameters with characters
Wing.orientation = 'xz' ;
Wing.wingAfoil.airfoilName = '2412' ;
Wing.type = 'liftingSurface';


%% DEFINE THE HTAIL %%
%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Htail.AR = 3;
Htail.area = 409;
Htail.taper = 0.25;
Htail.sweep = 28;
Htail.dihedral = 0 ;
Htail.xShiftWing = 161 ;
Htail.yShiftWing = 0 ;
Htail.zShiftWing = 32 ;
Htail.symWing = 1 ;

% parameters with characters
Htail.orientation = 'xz' ;
Htail.wingAfoil.airfoilName = '0008' ;
Htail.type = 'liftingSurface';


%% DEFINE THE VTAIL %%
%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Vtail.AR = 1.80;
Vtail.area = 280;
Vtail.taper = 0.8;
Vtail.sweep = 36;
Vtail.dihedral = 0 ;
Vtail.xShiftWing = 150 ;
Vtail.yShiftWing = 0 ;
Vtail.zShiftWing = 9 ;
Vtail.symWing = 0 ;

% parameters with characters
Vtail.orientation = 'xy' ;
Vtail.wingAfoil.airfoilName = '0008' ;
Vtail.type = 'liftingSurface';


%% DEFINE THE FUSELAGE %%
%%%%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Fuselage.Length = 150;

% parameters with characters
Fuselage.type = 'bluntBody';
Fuselage.Style = fullfile("+VisualizationPkg","+GeometrySpecsPkg","SUSANFuselage.dat");


%% DEFINE THE ENGINES %%
%%%%%%%%%%%%%%%%%%%%%%%%

% parameters with numerical values
Engine.Length = 8.5/2 ;
Engine.EngineInletRadii = 6.25 ;
Engine.EngineOutletRadii = 5.75;

% parameters with characters
Engine.type = 'Engine';
Engine.Filename = fullfile("+VisualizationPkg","+GeometrySpecsPkg","SUSANEngines.dat");

% %% DEFINE THE RIGHT CASING %%
% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%
% % parameters with numerical values
% CasingR.Length = 200;
%
% % parameters with characters
% CasingR.type = 'bluntBody';
% CasingR.Style = fullfile("+VisualizationPkg","+GeometrySpecsPkg","SUSANCasingR.dat");
%
% %% DEFINE THE LEFT CASING %%
% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%
%
% % parameters with numerical values
% CasingL.Length = 200;
%
% % parameters with characters
% CasingL.type = 'bluntBody';
% CasingL.Style = fullfile("+VisualizationPkg","+GeometrySpecsPkg","SUSANCasingL.dat");
%

%% REMEMBER THE GEOMETRY PARAMETERS %%
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% save as one structure %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% remember the wing
Aircraft.Geometry.Wing = Wing;

% remember the htail
Aircraft.Geometry.Htail = Htail;

% remember the vtail
Aircraft.Geometry.Vtail = Vtail;

%remember the fuselage
Aircraft.Geometry.Fuselage = Fuselage;

%remember the engines
Aircraft.Geometry.Engine = Engine;

% %remember the right casing
% Aircraft.Geometry.CasingR = CasingR;
%
% %remember the left casing
% Aircraft.Geometry.CasingL = CasingL;

% ----------------------------------------------------------

end
70 changes: 70 additions & 0 deletions +VisualizationPkg/+GeometrySpecsPkg/SUSANEngines.dat
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NumberOfEngines=17

engine_1
141 0 0
4 1
TURBOFAN
engine_2
110 -16 -12
5 0.25
TURBOPROP
engine_3
111 -20 -11.8
0.5 0.25
TURBOPROP
engine_4
113 -24 -11.6
0.5 0.25
TURBOPROP
engine_5
114 -28 -11.4
0.5 0.25
TURBOPROP
engine_6
115.7 -32 -11.2
0.5 0.25
TURBOPROP
engine_7
117 -36 -11
0.5 0.25
TURBOPROP
engine_8
118.5 -40 -10.8
0.5 0.25
TURBOPROP
engine_9
120 -44 -10.6
0.5 0.25
TURBOPROP
engine_10
110 16 -12
0.5 0.25
TURBOPROP
engine_11
111 20 -11.8
0.5 0.25
TURBOPROP
engine_12
113 24 -11.6
0.5 0.25
TURBOPROP
engine_13
114 28 -11.4
0.5 0.25
TURBOPROP
engine_14
115.7 32 -11.2
0.5 0.25
TURBOPROP
engine_15
117 36 -11
0.5 0.25
TURBOPROP
engine_16
118.5 40 -10.8
0.5 0.25
TURBOPROP
engine_17
120 44 -10.6
0.5 0.25
TURBOPROP
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