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| function varargout = cadcUNITS(varargin)
% CADCUNITS M-file for cadcUNITS.fig
% CADCUNITS, by itself, creates a new CADCUNITS or raises the existing
% singleton*.
%
% H = CADCUNITS returns the handle to a new CADCUNITS or the handle to
% the existing singleton*.
%
% CADCUNITS('CALLBACK',hObject,eventData,handles,...) calls the local
% function named CALLBACK in CADCUNITS.M with the given input arguments.
%
% CADCUNITS('Property','Value',...) creates a new CADCUNITS or raises the
% existing singleton*. Starting from the left, property value pairs are
% applied to the GUI before cadcUNITS_OpeningFunction gets called. An
% unrecognized property name or invalid value makes property application
% stop. All inputs are passed to cadcUNITS_OpeningFcn via varargin.
%
% *See GUI Options on GUIDE's Tools menu. Choose "GUI allows only one
% instance to run (singleton)".
%
% See also: GUIDE, GUIDATA, GUIHANDLES
% Edit the above text to modify the response to help cadcUNITS
% Last Modified by GUIDE v2.5 10-Apr-2007 15:03:59
% Begin initialization code - DO NOT EDIT
gui_Singleton = 1;
gui_State = struct('gui_Name', mfilename, ...
'gui_Singleton', gui_Singleton, ...
'gui_OpeningFcn', @cadcUNITS_OpeningFcn, ...
'gui_OutputFcn', @cadcUNITS_OutputFcn, ...
'gui_LayoutFcn', [] , ...
'gui_Callback', []);
if nargin && ischar(varargin{1})
gui_State.gui_Callback = str2func(varargin{1});
end
if nargout
[varargout{1:nargout}] = gui_mainfcn(gui_State, varargin{:});
else
gui_mainfcn(gui_State, varargin{:});
end
% End initialization code - DO NOT EDIT
% --- Executes just before cadcUNITS is made visible.
function cadcUNITS_OpeningFcn(hObject, eventdata, handles, varargin)
% This function has no output args, see OutputFcn.
% hObject handle to figure
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% varargin command line arguments to cadcUNITS (see VARARGIN)
% Choose default command line output for cadcUNITS
handles.output = hObject;
% Update handles structure
guidata(hObject, handles);
% UIWAIT makes cadcUNITS wait for user response (see UIRESUME)
% uiwait(handles.figure1);
% --- Outputs from this function are returned to the command line.
function varargout = cadcUNITS_OutputFcn(hObject, eventdata, handles)
% varargout cell array for returning output args (see VARARGOUT);
% hObject handle to figure
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Get default command line output from handles structure
varargout{1} = handles.output;
%-----------------------------------------------------------
% Callback for Altitude Value
%-----------------------------------------------------------
% --- Executes on slider movement.
function AltSlider_Callback(hObject, eventdata, handles)
% hObject handle to AltSlider (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hints: get(hObject,'Value') returns position of slider
% get(hObject,'Min') and get(hObject,'Max') to determine range of slider
NewVal = get(hObject,'Value');
set(handles.AltValue,'String',NewVal);
To = 288.15; % Temp at seal level in Kelvin
L = 0.0065; % Temperature Lapse rate K/m
Pso = 1013.25; %Pressure at sealevel in mbar
g = 9.80665; % Gravity m/s²
R = 287; % constant
a = g/(L*R);
Pst = 226.258; % Pressure at 11 km end of troposphere
Tst = 216.7; % Temperature at 11 km
Ht = 11000; % Height of the end of troposphere
rho0 = 1.225; % Sea level density in kg/m^3
rhos = 0.363817; %11km density
gam = 1.4;
% Get the altitude value from the slider
altitude = get(handles.AltSlider,'Value');
% Get the aircraft speed value
speed = get(handles.SpeedSlider,'Value');
% Calculation of the temperature
temp(altitude<=11000) = To - (L*altitude);
temp(altitude>11000) = Tst;
set(handles.temp, 'String', temp);
% Calculation of the static pressure
pressure(altitude<=11000) = Pso*(1-(L/To)*altitude).^(a);
pressure(altitude>11000) = Pst*exp(-((g/(R*Tst))*(altitude-Ht)));
set(handles.pressure, 'String', pressure);
% Calculation of the density with respect to the altitude
rho(altitude<=11000) = rho0*(1-((L/To)*altitude)).^((g/(L*R))-1);
rho(altitude>11000) = rhos*exp((g*(Ht-altitude))/(R*Tst));
set(handles.rho, 'String', rho);
% Calculation of the speed of sound
sound(altitude<=11000) = sqrt(gam*R*(To - (L*altitude)));
sound(altitude>11000) = sqrt(gam*R*Tst);
set(handles.sound, 'String', sound);
% Calculation of MAch number
mach(altitude<=11000) = speed/(sqrt(gam*R*(To - (L*altitude))));
mach(altitude>11000) = speed/sqrt(gam*R*Tst);
set(handles.mach, 'String', mach);
%------------------------------------------------------------
% Callback for speed slider
%------------------------------------------------------------
% --- Executes on slider movement.
function SpeedSlider_Callback(hObject, eventdata, handles)
% hObject handle to SpeedSlider (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hints: get(hObject,'Value') returns position of slider
% get(hObject,'Min') and get(hObject,'Max') to determine range of slider
NewVal = get(hObject,'Value');
set(handles.SpeedVAlue,'String',NewVal);
To = 288.15; % Temp at seal level in Kelvin
L = 0.0065; % Temperature Lapse rate K/m
Pso = 1013.25; %Pressure at sealevel in mbar
g = 9.80665; % Gravity m/s²
R = 287; % constant
a = g/(L*R);
Pst = 226.258; % Pressure at 11 km end of troposphere
Tst = 216.7; % Temperature at 11 km
Ht = 11000; % Height of the end of troposphere
rho0 = 1.225; % Sea level density in kg/m^3
rhos = 0.363817; %11km density
gam = 1.4;
% Get the altitude value from the slider
altitude = get(handles.AltSlider,'Value');
% Get the aircraft speed value
speed = get(handles.SpeedSlider,'Value');
% Calculation of the temperature
temp(altitude<=11000) = To - (L*altitude);
temp(altitude>11000) = Tst;
set(handles.temp, 'String', temp);
% Calculation of the static pressure
pressure(altitude<=11000) = Pso*(1-(L/To)*altitude).^(a);
pressure(altitude>11000) = Pst*exp(-((g/(R*Tst))*(altitude-Ht)));
set(handles.pressure, 'String', pressure);
% Calculation of the density with respect to the altitude
rho(altitude<=11000) = rho0*(1-((L/To)*altitude)).^((g/(L*R))-1);
rho(altitude>11000) = rhos*exp((g*(Ht-altitude))/(R*Tst));
set(handles.rho, 'String', rho);
% Calculation of the speed of sound
sound(altitude<=11000) = sqrt(gam*R*(To - (L*altitude)));
sound(altitude>11000) = sqrt(gam*R*Tst);
set(handles.sound, 'String', sound);
% Calculation of MAch number
mach(altitude<=11000) = speed/(sqrt(gam*R*(To - (L*altitude))));
mach(altitude>11000) = speed/sqrt(gam*R*Tst);
set(handles.mach, 'String', mach);
function AltValue_Callback(hObject, eventdata, handles)
% hObject handle to AltValue (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hints: get(hObject,'String') returns contents of AltValue as text
% str2double(get(hObject,'String')) returns contents of AltValue as a double
function SpeedVAlue_Callback(hObject, eventdata, handles)
% hObject handle to SpeedVAlue (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hints: get(hObject,'String') returns contents of SpeedVAlue as text
% str2double(get(hObject,'String')) returns contents of SpeedVAlue as a double
% --- Executes on button press in si.
function si_Callback(hObject, eventdata, handles)
% hObject handle to si (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hint: get(hObject,'Value') returns toggle state of si
set(handles.text1, 'String', 'Temp (K)');
set(handles.AltSlider, 'Max', 20000,...
'Value', 0);
set(handles.SpeedSlider, 'Max', 340,...
'Value', 0);
set(handles.AltValue, 'String', '0');
set(handles.SpeedVAlue, 'String', '0');
% --- Executes on button press in uk.
function uk_Callback(hObject, eventdata, handles)
% hObject handle to uk (see GCBO)
% eventdata reserved - to be defined in a future version of MATLAB
% handles structure with handles and user data (see GUIDATA)
% Hint: get(hObject,'Value') returns toggle state of uk
set(handles.text1, 'String', 'Temp (F)');
set(handles.AltSlider, 'Max', 60000,...
'Value', 0);
set(handles.SpeedSlider, 'Max', 940,...
'Value', 0);
set(handles.SpeedVAlue, 'String', '0');
set(handles.AltValue, 'String', '0');
To = 288.15; % Temp at seal level in Kelvin
L = 0.0065; % Temperature Lapse rate K/m
Pso = 1013.25; %Pressure at sealevel in mbar
g = 9.80665; % Gravity m/s²
R = 287; % constant
a = g/(L*R);
Pst = 226.258; % Pressure at 11 km end of troposphere
Tst = 216.7; % Temperature at 11 km
Ht = 11000; % Height of the end of troposphere
rho0 = 1.225; % Sea level density in kg/m^3
rhos = 0.363817; %11km density
gam = 1.4;
% Get the altitude value from the slider
altitude = get(handles.AltSlider,'Value');
% Get the aircraft speed value
speed = get(handles.SpeedSlider,'Value');
% Calculation of the temperature
temp(altitude<=11000) = (To - (L*altitude))*2;
temp(altitude>11000) = Tst*2;
set(handles.temp, 'String', temp); |
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